TABLE NR. 2.2.1.1 RE=3*10E6 CL=0.50 DLR-F4 WING SECTION 1 2 3 4 5 6 7 ETA = 0.185 0.238 0.331 0.409 0.512 0.636 0.844 X/C CP CP CP CP CP CP CP 1.000 0.1167 0.1095 0.0837 0.0386 0.0473 0.0466 0.0644 0.950 -0.0002 0.0029 -0.0176 -0.0491 -0.0275 -0.0318 -0.0109 0.900 -0.1162 -0.1088 -0.1245 -0.1549 -0.1178 -0.1237 -0.0989 0.800 -0.2786 -0.2786 -0.3066 -0.3666 -0.3170 -0.3083 -0.2767 0.700 -0.3907 -0.4047 -0.4665 -0.5283 -0.4859 -0.4671 -0.4560 0.650 -0.4325 -0.4514 -0.5197 -0.5910 99.4460 -0.5444 -0.4970 0.600 -0.4564 -0.4832 -0.5464 -0.6107 -0.5811 100.0400 -0.5265 0.550 -0.4851 -0.4981 -0.5552 -0.6114 -0.5840 100.0400 -0.5141 0.500 -0.4884 -0.5074 -0.5666 -0.6139 -0.6051 -0.5679 -0.5317 0.450 -0.5132 -0.5386 -0.5835 -0.6219 -0.6252 -0.5666 -0.5471 0.425 -0.5361 -0.5559 -0.6109 -0.6454 -0.6357 -0.6129 -0.5669 0.400 -0.5557 -0.5816 -0.5875 -0.6642 -0.6441 -0.6296 -0.5761 0.350 -0.5862 -0.6024 -0.6525 -0.6864 -0.6618 -0.6321 -0.5861 0.300 -0.6178 -0.6434 -0.6935 -0.6833 -0.7053 -0.6812 -0.6137 0.250 -0.6613 -0.7132 -0.7526 -0.7537 -0.7259 -0.7058 -0.6407 0.200 -0.7374 -0.7763 -0.8061 -0.8056 -0.7713 -0.7364 -0.6705 0.150 -0.7969 -0.8486 -0.8798 -0.7782 -0.6873 -0.6963 -0.5724 0.100 -0.9136 -0.9855 -0.9534 -0.9311 -1.0725 -1.0439 -0.9194 0.050 -1.2942 -1.4046 -1.5752 -1.4588 -1.4524 -1.4190 -1.2125 0.030 -1.4735 -1.6960 -1.7085 -1.4456 -1.4126 -1.3045 -1.1066 0.020 -1.4990 -1.5563 -1.3167 -1.2430 -1.1999 -1.1580 -0.9596 0.010 -0.8023 -0.6531 -0.7397 -0.8274 -0.7179 -0.7025 -0.5735 0.000 0.6431 0.5873 0.4421 0.5267 0.4223 0.6093 0.6957 0.010 0.6341 0.6523 0.6332 0.6198 0.5944 0.5905 0.5612 0.030 0.3464 0.3814 0.3362 0.3120 0.3293 0.3306 0.2512 0.050 0.1463 0.1466 0.1641 0.2099 0.2263 0.2207 0.1618 0.100 -0.0590 -0.0534 -0.0023 0.0599 100.0600 0.0823 0.0288 0.200 -0.1617 -0.1629 -0.1174 -0.0619 -0.0506 -0.0373 -0.0686 0.300 -0.2101 -0.2253 -0.2138 -0.1963 -0.1557 -0.1445 100.0300 0.400 -0.2453 -0.2527 -0.2347 -0.2094 -0.1684 -0.1604 -0.1917 0.500 -0.2603 -0.2583 -0.2192 -0.1849 -0.1433 -0.1398 -0.1538 0.600 -0.1681 -0.1675 -0.1445 -0.1400 -0.0904 -0.0952 -0.1087 0.700 0.0293 0.0441 0.0442 0.0441 0.0596 100.0300 0.0503 0.800 0.1943 0.2100 0.2343 0.2261 0.2299 0.2382 0.2138 0.900 0.2360 0.2626 0.2959 0.3143 0.2986 0.2981 0.2770 0.950 0.2274 0.2615 0.2911 0.3110 0.2760 0.2879 0.2609 1 TABLE NR. 2.2.1.1 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0501 -0.1170 -.484 -0.0285 -0.1006 -.406 -0.0092 -0.0924 -.327 -0.0029 -0.0834 -.248 0.0276 -0.0889 -.168 0.0280 -0.0923 -.089 0.0284 -0.0859 -.010 0.0314 -0.1087 0.069 0.0232 -0.1145 0.148 0.0167 -0.1302 0.227 0.0066 -0.1425 0.306 -0.0075 -0.1490 0.386 -0.0131 -0.1550 0.465 -0.0133 -0.1560 0.544 -0.0114 -0.1510 0.623 -0.0024 -0.1464 0.702 0.0048 -0.1379 0.781 0.0095 -0.1293 0.860 0.0185 -0.1129 0.941 0.0259 -0.1051 1.019 0.0162 -0.0927 1.098 0.0023 -0.0834 1 TABLE NR. 2.2.1.2 RE=3*10E6 CL=0.50 DLR-F4 WING SECTION 1 2 3 4 5 6 7 ETA = 0.185 0.238 0.331 0.409 0.512 0.636 0.844 X/C CP CP CP CP CP CP CP 1.000 0.1151 0.1122 0.0843 0.0316 0.0344 0.0365 0.0622 0.950 0.0093 0.0170 -0.0050 -0.0386 -0.0184 -0.0226 0.0061 0.900 -0.1080 -0.0966 -0.1084 -0.1336 -0.0954 -0.1021 -0.0706 0.800 -0.2839 -0.2829 -0.3050 -0.3602 -0.2976 -0.2913 -0.2504 0.700 -0.4160 -0.4332 -0.4957 -0.5579 -0.4957 -0.4769 -0.4526 0.650 -0.4655 -0.4887 -0.5630 -0.6383 99.4150 -0.5674 -0.5112 0.600 -0.4930 -0.5231 -0.5951 -0.6660 -0.6206 100.0400 -0.5466 0.550 -0.5231 -0.5392 -0.6042 -0.6667 -0.6294 100.0400 -0.5433 0.500 -0.5213 -0.5397 -0.6059 -0.6581 -0.6489 -0.6050 -0.5632 0.450 -0.5448 -0.5692 -0.6186 -0.6627 -0.6688 -0.6054 -0.5786 0.425 -0.5760 -0.5975 -0.6557 -0.6973 -0.6932 -0.6607 -0.5985 0.400 -0.5959 -0.6249 -0.6285 -0.7151 -0.7010 -0.6768 -0.6083 0.350 -0.6233 -0.6376 -0.6909 -0.7303 -0.7097 -0.6771 -0.6193 0.300 -0.6582 -0.6755 -0.7248 -0.7196 -0.7556 -0.7299 -0.6549 0.250 -0.7072 -0.7558 -0.7738 -0.7694 -0.7496 -0.7395 -0.6788 0.200 -0.7918 -0.8058 -0.7764 -0.7636 -0.7506 -0.7300 -0.7174 0.150 -0.8339 -0.8594 -0.7398 -0.8093 -0.7599 -0.5669 -0.5292 0.100 -0.9401 -1.2597 -1.5178 -1.4677 -1.3995 -1.3676 -1.0828 0.050 -1.3336 -1.5933 -1.6053 -1.4868 -1.4458 -1.3928 -1.2482 0.030 -1.4349 -1.5333 -1.3574 -1.1631 -1.1449 -1.0710 -0.9494 0.020 -1.2276 -1.1937 -0.9653 -0.9311 -0.9043 -0.8878 -0.7398 0.010 -0.5162 -0.3630 -0.4289 -0.4894 -0.3993 -0.4045 -0.3271 0.000 0.7320 0.6868 0.5734 0.6668 0.5780 0.7164 0.7773 0.010 0.6227 0.6328 0.5913 0.5629 0.5290 0.5293 0.5142 0.030 0.3210 0.3425 0.2784 0.2432 0.2617 0.2667 0.1930 0.050 0.1206 0.1079 0.1063 0.1500 0.1706 0.1676 0.1090 0.100 -0.0866 -0.0929 -0.0532 0.0135 100.0300 0.0328 -0.0122 0.200 -0.1941 -0.2022 -0.1317 -0.1136 -0.0983 -0.0819 -0.1099 0.300 -0.2467 -0.2732 -0.2730 -0.2567 -0.2116 -0.1973 100.0400 0.400 -0.2864 -0.3012 -0.2897 -0.2647 -0.2161 -0.2051 -0.2350 0.500 -0.3042 -0.3040 -0.2647 -0.2296 -0.1784 -0.1771 -0.1884 0.600 -0.1959 -0.1948 -0.1741 -0.1740 -0.1182 -0.1216 -0.1306 0.700 0.0276 0.0421 0.0418 0.0372 0.0533 100.0300 0.0450 0.800 0.2011 0.2162 0.2403 0.2290 0.2323 0.2389 0.2142 0.900 0.2467 0.2743 0.3062 0.3208 0.3021 0.3005 0.2787 0.950 0.2374 0.2721 0.2999 0.3174 0.2783 0.2908 0.2650 1 TABLE NR. 2.2.1.2 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0552 -0.1139 -.484 -0.0290 -0.0945 -.406 -0.0103 -0.0866 -.327 -0.0019 -0.0775 -.248 0.0313 -0.0810 -.168 0.0328 -0.0869 -.089 0.0348 -0.0812 -.010 0.0357 -0.1078 0.069 0.0247 -0.1204 0.148 0.0150 -0.1422 0.227 -0.0015 -0.1601 0.306 -0.0187 -0.1715 0.386 -0.0260 -0.1800 0.465 -0.0257 -0.1816 0.544 -0.0246 -0.1722 0.623 -0.0106 -0.1679 0.702 0.0012 -0.1588 0.781 0.0088 -0.1451 0.860 0.0214 -0.1255 0.941 0.0296 -0.1148 1.019 0.0218 -0.0972 1.098 0.0079 -0.0861 1 TABLE NR. 2.2.1.3 RE=3*10E6 CL=0.50 DLR-F4 WING SECTION 1 2 3 4 5 6 7 ETA = 0.185 0.238 0.331 0.409 0.512 0.636 0.844 X/C CP CP CP CP CP CP CP 1.000 0.1101 0.1158 0.0921 0.0399 0.0513 0.0542 0.0785 0.950 0.0134 0.0288 0.0105 -0.0268 -0.0045 -0.0067 0.0192 0.900 -0.0995 -0.0843 -0.0914 -0.1178 -0.0841 -0.0891 -0.0590 0.800 -0.2780 -0.2786 -0.2959 -0.3505 -0.2899 -0.2872 -0.2481 0.700 -0.4275 -0.4484 -0.5145 -0.5760 -0.5050 -0.4898 -0.4660 0.650 -0.4903 -0.5183 -0.6092 -0.7015 99.3800 -0.6006 -0.5437 0.600 -0.5253 -0.5595 -0.6499 -0.7419 -0.6700 100.0400 -0.5871 0.550 -0.5568 -0.5748 -0.6503 -0.7217 -0.6707 100.0400 -0.5774 0.500 -0.5516 -0.5662 -0.6335 -0.6791 -0.6834 -0.6336 -0.5935 0.450 -0.5768 -0.5971 -0.6401 -0.6695 -0.6978 -0.6147 -0.6079 0.425 -0.6105 -0.6317 -0.6765 -0.7078 -0.7066 -0.6547 -0.6437 0.400 -0.6280 -0.6581 -0.6516 -0.7215 -0.7066 -0.6713 -0.6494 0.350 -0.6543 -0.6400 -0.6749 -0.6530 -0.6243 -0.5949 -0.6386 0.300 -0.7071 -0.6722 -0.6616 -0.6192 -0.6471 -0.6070 -0.6254 0.250 -0.8045 -0.8991 -0.7230 -1.1893 -1.1685 -1.1381 -0.5770 0.200 -0.8431 -0.9200 -1.2112 -1.2497 -1.2330 -1.1813 -0.9783 0.150 -0.8388 -0.8803 -1.3495 -1.2229 -1.2211 -1.2155 -1.1130 0.100 -0.9344 -1.2822 -1.3787 -1.3312 -1.3236 -1.3320 -1.2448 0.050 -1.1844 -1.3653 -1.3405 -1.2278 -1.1912 -1.1514 -1.1161 0.030 -1.2134 -1.2797 -1.1054 -0.9191 -0.9096 -0.8447 -0.7876 0.020 -0.9974 -0.9560 -0.7358 -0.6848 -0.6621 -0.6594 -0.5678 0.010 -0.3402 -0.1949 -0.2422 -0.2686 -0.1837 -0.2032 -0.1788 0.000 0.7866 0.7452 0.6569 0.7447 0.6805 0.7853 0.8124 0.010 0.6118 0.6165 0.5558 0.5079 0.4725 0.4773 0.4649 0.030 0.2987 0.3145 0.2305 0.1850 0.2012 0.2188 0.1489 0.050 0.0928 0.0707 0.0529 0.0916 0.1123 0.1153 0.0646 0.100 -0.1174 -0.1303 -0.0906 -0.0308 99.9960 -0.0099 -0.0458 0.200 -0.2206 -0.2355 -0.1780 -0.1569 -0.1285 -0.1166 -0.1423 0.300 -0.2760 -0.3116 -0.3212 -0.3083 -0.2634 -0.2382 100.0400 0.400 -0.3232 -0.3445 -0.3398 -0.3166 -0.2583 -0.2435 -0.2699 0.500 -0.3434 -0.3451 -0.3030 -0.2654 -0.2124 -0.2016 -0.2112 0.600 -0.2148 -0.2144 -0.1938 -0.1953 -0.1331 -0.1320 -0.1411 0.700 0.0251 0.0412 0.0422 0.0345 0.0560 100.0300 0.0505 0.800 0.1998 0.2168 0.2417 0.2296 0.2342 0.2409 0.2185 0.900 0.2479 0.2781 0.3106 0.3241 0.3037 0.3040 0.2837 0.950 0.2378 0.2778 0.3072 0.3246 0.2849 0.2984 0.2729 1 TABLE NR. 2.2.1.3 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0554 -0.1101 -.484 -0.0267 -0.0893 -.406 -0.0065 -0.0790 -.327 0.0029 -0.0683 -.248 0.0360 -0.0732 -.168 0.0369 -0.0772 -.089 0.0386 -0.0723 -.010 0.0392 -0.1026 0.069 0.0248 -0.1187 0.148 0.0108 -0.1475 0.227 -0.0091 -0.1723 0.306 -0.0314 -0.1906 0.386 -0.0431 -0.2019 0.465 -0.0431 -0.2096 0.544 -0.0382 -0.1990 0.623 -0.0219 -0.1912 0.702 -0.0066 -0.1777 0.781 0.0073 -0.1585 0.860 0.0211 -0.1354 0.941 0.0320 -0.1203 1.019 0.0234 -0.1002 1.098 0.0090 -0.0870 1 TABLE NR. 2.2.1.4 RE=3*10E6 CL=0.50 DLR-F4 WING SECTION 1 2 3 4 5 6 7 ETA = 0.185 0.238 0.331 0.409 0.512 0.636 0.844 X/C CP CP CP CP CP CP CP 1.000 0.1102 0.1159 0.0910 0.0411 0.0528 0.0572 0.0763 0.950 0.0132 0.0299 0.0131 -0.0232 -0.0013 -0.0028 0.0210 0.900 -0.0957 -0.0808 -0.0858 -0.1127 -0.0782 -0.0847 -0.0543 0.800 -0.2771 -0.2759 -0.2904 -0.3433 -0.2817 -0.2810 -0.2404 0.700 -0.4328 -0.4530 -0.5161 -0.5705 -0.4994 -0.4866 -0.4606 0.650 -0.5000 -0.5292 -0.6266 -0.7501 99.3810 -0.5999 -0.5457 0.600 -0.5369 -0.5735 -0.6663 -0.7610 -0.6681 100.0400 -0.5942 0.550 -0.5655 -0.5838 -0.6585 -0.7241 -0.6692 100.0400 -0.5832 0.500 -0.5590 -0.5727 -0.6334 -0.6620 -0.6749 -0.6068 -0.5996 0.450 -0.5821 -0.5989 -0.6366 -0.6568 -0.6638 -0.5720 -0.6079 0.425 -0.6136 -0.6289 -0.6738 -0.6753 -0.6464 -0.5819 -0.6430 0.400 -0.6417 -0.6571 -0.6557 -0.6671 -0.6300 -0.5797 -0.6469 0.350 -0.6842 -0.6366 -0.6473 -0.6320 -0.6467 -0.5951 -0.5979 0.300 -0.7999 -0.8416 -0.7535 -1.1010 -1.1215 -1.1016 -0.5495 0.250 -0.8200 -0.9232 -0.9656 -1.1653 -1.1471 -1.1254 -0.7705 0.200 -0.8491 -0.9126 -1.1910 -1.2323 -1.2042 -1.1523 -1.0839 0.150 -0.8387 -0.8866 -1.3121 -1.1955 -1.1824 -1.1759 -1.0808 0.100 -0.9193 -1.2582 -1.3351 -1.2849 -1.2787 -1.2862 -1.2105 0.050 -1.1682 -1.3187 -1.2905 -1.1788 -1.1412 -1.1040 -1.0701 0.030 -1.1597 -1.2253 -1.0492 -0.8634 -0.8541 -0.7946 -0.7500 0.020 -0.9497 -0.9087 -0.6892 -0.6395 -0.6130 -0.6116 -0.5319 0.010 -0.3323 -0.1601 -0.2027 -0.2319 -0.1422 -0.1636 -0.1382 0.000 0.7995 0.7577 0.6738 0.7574 0.7003 0.7974 0.8246 0.010 0.6065 0.6105 0.5446 0.4886 0.4476 0.4555 0.4512 0.030 0.2986 0.3119 0.2242 0.1754 0.1889 0.2073 0.1324 0.050 0.0872 0.0639 0.0423 0.0796 0.0994 0.1028 0.0498 0.100 -0.1216 -0.1361 -0.0994 -0.0395 99.9890 -0.0187 -0.0575 0.200 -0.2326 -0.2433 -0.1888 -0.1679 -0.1395 -0.1263 -0.1510 0.300 -0.2838 -0.3242 -0.3369 -0.3256 -0.2808 -0.2522 100.0400 0.400 -0.3331 -0.3562 -0.3529 -0.3289 -0.2692 -0.2527 -0.2837 0.500 -0.3551 -0.3565 -0.3138 -0.2751 -0.2165 -0.2082 -0.2185 0.600 -0.2222 -0.2204 -0.2006 -0.2025 -0.1368 -0.1358 -0.1449 0.700 0.0255 0.0416 0.0428 0.0352 0.0572 100.0300 0.0489 0.800 0.2027 0.2181 0.2432 0.2303 0.2351 0.2416 0.2181 0.900 0.2503 0.2804 0.3128 0.3259 0.3051 0.3059 0.2822 0.950 0.2415 0.2804 0.3107 0.3281 0.2875 0.3011 0.2731 1 TABLE NR. 2.2.1.4 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0569 -0.1089 -.484 -0.0284 -0.0878 -.406 -0.0069 -0.0764 -.327 0.0048 -0.0660 -.248 0.0375 -0.0694 -.168 0.0398 -0.0742 -.089 0.0405 -0.0697 -.010 0.0388 -0.1020 0.069 0.0246 -0.1185 0.148 0.0096 -0.1492 0.227 -0.0138 -0.1758 0.306 -0.0339 -0.1934 0.386 -0.0471 -0.2102 0.465 -0.0462 -0.2135 0.544 -0.0410 -0.2057 0.623 -0.0241 -0.1985 0.702 -0.0085 -0.1830 0.781 0.0048 -0.1644 0.860 0.0198 -0.1397 0.941 0.0302 -0.1222 1.019 0.0226 -0.1000 1.098 0.0098 -0.0874 1 TABLE NR. 2.2.1.5 RE=3*10E6 CL=0.50 DLR-F4 WING SECTION 1 2 3 4 5 6 7 ETA = 0.185 0.238 0.331 0.409 0.512 0.636 0.844 X/C CP CP CP CP CP CP CP 1.000 0.1094 0.1169 0.0913 0.0407 0.0560 0.0636 0.0813 0.950 0.0164 0.0347 0.0177 -0.0180 0.0048 0.0025 0.0260 0.900 -0.0910 -0.0744 -0.0787 -0.1035 -0.0710 -0.0787 -0.0485 0.800 -0.2710 -0.2704 -0.2804 -0.3286 -0.2690 -0.2707 -0.2343 0.700 -0.4331 -0.4531 -0.5112 -0.5540 -0.4807 -0.4705 -0.4553 0.650 -0.5042 -0.5361 -0.6433 -0.7917 99.4020 -0.5789 -0.5453 0.600 -0.5433 -0.5806 -0.6749 -0.7504 -0.6321 100.0400 -0.5917 0.550 -0.5701 -0.5892 -0.6595 -0.7053 -0.6255 100.0400 -0.5773 0.500 -0.5603 -0.5683 -0.6305 -0.6393 -0.6240 -0.5302 -0.5854 0.450 -0.5851 -0.5910 -0.6207 -0.6298 -0.6273 -0.5263 -0.5749 0.425 -0.6090 -0.6198 -0.6460 -0.6578 -0.6353 -0.5561 -0.5948 0.400 -0.7058 -0.6770 -0.6111 -0.6958 -1.0164 -0.9837 -0.5941 0.350 -0.7349 -0.7277 -0.8225 -1.0886 -1.0810 -1.0649 -0.5337 0.300 -0.8191 -0.8947 -0.8847 -1.1017 -1.1044 -1.0938 -0.7979 0.250 -0.8106 -0.9221 -1.0905 -1.1390 -1.1185 -1.1009 -1.0208 0.200 -0.8326 -0.9064 -1.1719 -1.2002 -1.1691 -1.1206 -1.0607 0.150 -0.8308 -0.9273 -1.2786 -1.1586 -1.1451 -1.1375 -1.0483 0.100 -0.9081 -1.2313 -1.2951 -1.2405 -1.2339 -1.2434 -1.1656 0.050 -1.1270 -1.2697 -1.2385 -1.1258 -1.0893 -1.0526 -1.0187 0.030 -1.1151 -1.1766 -1.0006 -0.8148 -0.8049 -0.7459 -0.6967 0.020 -0.9035 -0.8619 -0.6440 -0.5869 -0.5614 -0.5595 -0.4821 0.010 -0.2970 -0.1275 -0.1692 -0.1896 -0.1016 -0.1245 -0.1005 0.000 0.8110 0.7689 0.6900 0.7694 0.7211 0.8115 0.8335 0.010 0.6006 0.6099 0.5326 0.4682 0.4276 0.4352 0.4351 0.030 0.2865 0.2951 0.2037 0.1485 0.1644 0.1776 0.1162 0.050 0.0850 0.0592 0.0336 0.0659 0.0856 0.0919 0.0385 0.100 -0.1270 -0.1433 -0.1105 -0.0624 99.9760 -0.0306 -0.0706 0.200 -0.2364 -0.2498 -0.2014 -0.1768 -0.1493 -0.1356 -0.1644 0.300 -0.2881 -0.3298 -0.3460 -0.3356 -0.2901 -0.2594 100.0400 0.400 -0.3407 -0.3663 -0.3652 -0.3421 -0.2792 -0.2618 -0.2922 0.500 -0.3634 -0.3657 -0.3217 -0.2833 -0.2252 -0.2131 -0.2241 0.600 -0.2238 -0.2223 -0.2035 -0.2060 -0.1398 -0.1371 -0.1465 0.700 0.0263 0.0431 0.0438 0.0354 0.0585 100.0300 0.0496 0.800 0.2023 0.2186 0.2434 0.2308 0.2352 0.2428 0.2182 0.900 0.2514 0.2817 0.3148 0.3278 0.3058 0.3068 0.2828 0.950 0.2412 0.2809 0.3110 0.3293 0.2875 0.3014 0.2749 1 TABLE NR. 2.2.1.5 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0555 -0.1071 -.484 -0.0281 -0.0850 -.406 -0.0058 -0.0724 -.327 0.0047 -0.0619 -.248 0.0375 -0.0664 -.168 0.0408 -0.0712 -.089 0.0417 -0.0667 -.010 0.0408 -0.0983 0.069 0.0253 -0.1171 0.148 0.0095 -0.1479 0.227 -0.0134 -0.1758 0.306 -0.0365 -0.1992 0.386 -0.0495 -0.2184 0.465 -0.0494 -0.2175 0.544 -0.0449 -0.2151 0.623 -0.0270 -0.2056 0.702 -0.0097 -0.1874 0.781 0.0050 -0.1672 0.860 0.0210 -0.1421 0.941 0.0323 -0.1238 1.019 0.0241 -0.1008 1.098 0.0107 -0.0865 1 TABLE NR. 2.2.1.6 RE=3*10E6 CL=0.50 DLR-F4 WING SECTION 1 2 3 4 5 6 7 ETA = 0.185 0.238 0.331 0.409 0.512 0.636 0.844 X/C CP CP CP CP CP CP CP 1.000 0.1080 0.1166 0.0904 0.0369 0.0531 0.0643 0.0868 0.950 0.0185 0.0374 0.0195 -0.0180 0.0054 0.0052 0.0308 0.900 -0.0880 -0.0699 -0.0731 -0.0964 -0.0641 -0.0712 -0.0434 0.800 -0.2698 -0.2671 -0.2719 -0.3117 -0.2512 -0.2539 -0.2264 0.700 -0.4358 -0.4550 -0.5095 -0.5493 -0.4562 -0.4478 -0.4462 0.650 -0.5130 -0.5481 -0.6676 -0.8091 99.4530 -0.5277 -0.5344 0.600 -0.5539 -0.5921 -0.6848 -0.7351 -0.5721 100.0400 -0.5735 0.550 -0.5746 -0.5889 -0.6565 -0.6726 -0.5841 100.0400 -0.5369 0.500 -0.5652 -0.5559 -0.6029 -0.6398 -0.8126 -0.6076 -0.5189 0.450 -0.6358 -0.6344 -0.6400 -0.8121 -1.0675 -1.0278 -0.4981 0.425 -0.7365 -0.7500 -0.7792 -0.8627 -1.0641 -1.0727 -0.5123 0.400 -0.7694 -0.7772 -0.8419 -1.0057 -1.0695 -1.0809 -0.6028 0.350 -0.7693 -0.8034 -0.8752 -1.1044 -1.0776 -1.0576 -0.9254 0.300 -0.8239 -0.8986 -0.8903 -1.0822 -1.0841 -1.0732 -0.9846 0.250 -0.8103 -0.9071 -1.0968 -1.1073 -1.0858 -1.0692 -1.0089 0.200 -0.8257 -0.9021 -1.1485 -1.1710 -1.1398 -1.0924 -1.0319 0.150 -0.8131 -0.9520 -1.2360 -1.1169 -1.1018 -1.0995 -1.0136 0.100 -0.8839 -1.1995 -1.2538 -1.1980 -1.1904 -1.2014 -1.1308 0.050 -1.0856 -1.2273 -1.1936 -1.0811 -1.0413 -1.0072 -0.9764 0.030 -1.0714 -1.1304 -0.9536 -0.7670 -0.7584 -0.6983 -0.6562 0.020 -0.8628 -0.8182 -0.6025 -0.5435 -0.5156 -0.5145 -0.4411 0.010 -0.2427 -0.0999 -0.1374 -0.1526 -0.0640 -0.0900 -0.0589 0.000 0.8215 0.7795 0.7050 0.7811 0.7396 0.8229 0.8428 0.010 0.6007 0.6086 0.5268 0.4545 0.4121 0.4192 0.4229 0.030 0.2822 0.2896 0.1940 0.1334 0.1496 0.1591 0.1037 0.050 0.0767 0.0486 0.0181 0.0527 0.0668 0.0716 0.0215 0.100 -0.1356 -0.1536 -0.1223 -0.0784 99.9580 -0.0488 -0.0823 0.200 -0.2433 -0.2597 -0.2110 -0.2052 -0.1666 -0.1514 -0.1790 0.300 -0.2979 -0.3440 -0.3638 -0.3556 -0.3102 -0.2791 100.0400 0.400 -0.3538 -0.3815 -0.3826 -0.3611 -0.2943 -0.2742 -0.3016 0.500 -0.3786 -0.3819 -0.3360 -0.2970 -0.2337 -0.2232 -0.2301 0.600 -0.2312 -0.2288 -0.2103 -0.2160 -0.1511 -0.1423 -0.1495 0.700 0.0265 0.0427 0.0436 0.0333 0.0577 100.0300 0.0515 0.800 0.2025 0.2178 0.2423 0.2300 0.2344 0.2417 0.2186 0.900 0.2521 0.2815 0.3128 0.3266 0.3035 0.3053 0.2848 0.950 0.2416 0.2812 0.3109 0.3316 0.2872 0.3023 0.2763 1 TABLE NR. 2.2.1.6 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0564 -0.1068 -.484 -0.0277 -0.0839 -.406 -0.0056 -0.0700 -.327 0.0055 -0.0595 -.248 0.0377 -0.0630 -.168 0.0408 -0.0678 -.089 0.0420 -0.0639 -.010 0.0413 -0.0952 0.069 0.0244 -0.1164 0.148 0.0074 -0.1469 0.227 -0.0179 -0.1800 0.306 -0.0397 -0.2053 0.386 -0.0541 -0.2262 0.465 -0.0552 -0.2297 0.544 -0.0487 -0.2264 0.623 -0.0299 -0.2154 0.702 -0.0109 -0.1961 0.781 0.0040 -0.1747 0.860 0.0198 -0.1467 0.941 0.0324 -0.1261 1.019 0.0238 -0.1035 1.098 0.0106 -0.0871 1 TABLE NR. 2.2.1.7 RE=3*10E6 CL=0.50 DLR-F4 WING SECTION 1 2 3 4 5 6 7 ETA = 0.185 0.238 0.331 0.409 0.512 0.636 0.844 X/C CP CP CP CP CP CP CP 1.000 0.1042 0.1142 0.0849 0.0232 0.0454 0.0504 0.0883 0.950 0.0194 0.0393 0.0198 -0.0262 -0.0040 0.0037 0.0361 0.900 -0.0815 -0.0621 -0.0648 -0.0889 -0.0621 -0.0584 -0.0354 0.800 -0.2605 -0.2564 -0.2561 -0.2857 -0.2226 -0.2220 -0.2102 0.700 -0.4319 -0.4478 -0.4873 -0.5028 -0.3900 -0.3848 -0.4100 0.650 -0.5117 -0.5458 -0.6654 -0.7150 99.5300 -0.4506 -0.4913 0.600 -0.5570 -0.5823 -0.6656 -0.7187 -0.5594 100.0400 -0.4957 0.550 -0.5803 -0.5706 -0.6318 -0.9001 -1.0247 100.0400 -0.4505 0.500 -0.6207 -0.6184 -0.7436 -0.8550 -1.0507 -1.0207 -0.4825 0.450 -0.7559 -0.7990 -0.8645 -0.9667 -1.0662 -1.0350 -0.9009 0.425 -0.7862 -0.8075 -0.9045 -1.0244 -1.0604 -1.0699 -0.9798 0.400 -0.7818 -0.8055 -0.8575 -1.0021 -1.0440 -1.0551 -0.9304 0.350 -0.7732 -0.8078 -0.8668 -1.0695 -1.0393 -1.0237 -0.9584 0.300 -0.8163 -0.9018 -0.9277 -1.0556 -1.0576 -1.0451 -0.9775 0.250 -0.8103 -0.8942 -1.0902 -1.0821 -1.0577 -1.0388 -0.9832 0.200 -0.8122 -0.8752 -1.1088 -1.1242 -1.0973 -1.0475 -1.0005 0.150 -0.8008 -0.9944 -1.1999 -1.0775 -1.0618 -1.0569 -0.9847 0.100 -0.8627 -1.1636 -1.2110 -1.1523 -1.1422 -1.1508 -1.0820 0.050 -1.0577 -1.1865 -1.1521 -1.0374 -0.9974 -0.9604 -0.9318 0.030 -1.0359 -1.0908 -0.9136 -0.7272 -0.7157 -0.6556 -0.6135 0.020 -0.8270 -0.7808 -0.5656 -0.5025 -0.4747 -0.4717 -0.3970 0.010 -0.2156 -0.0740 -0.1084 -0.1171 -0.0254 -0.0511 -0.0325 0.000 0.8288 0.7871 0.7157 0.7903 0.7510 0.8306 0.8469 0.010 0.5982 0.6054 0.5186 0.4423 0.3990 0.4036 0.4029 0.030 0.2829 0.2887 0.1886 0.1247 0.1363 0.1467 0.0911 0.050 0.0746 0.0445 0.0098 0.0413 0.0537 0.0568 0.0111 0.100 -0.1373 -0.1580 -0.1296 -0.0899 99.9450 -0.0624 -0.0954 0.200 -0.2459 -0.2645 -0.2195 -0.2143 -0.1775 -0.1635 -0.1876 0.300 -0.3065 -0.3538 -0.3782 -0.3725 -0.3270 -0.2955 100.0500 0.400 -0.3633 -0.3942 -0.3989 -0.3781 -0.3077 -0.2881 -0.3161 0.500 -0.3919 -0.3957 -0.3490 -0.3098 -0.2467 -0.2348 -0.2404 0.600 -0.2337 -0.2307 -0.2132 -0.2201 -0.1569 -0.1480 -0.1549 0.700 0.0256 0.0422 0.0422 0.0302 0.0544 100.0300 0.0507 0.800 0.2012 0.2160 0.2397 0.2258 0.2301 0.2352 0.2183 0.900 0.2522 0.2815 0.3117 0.3233 0.3002 0.2999 0.2828 0.950 0.2404 0.2789 0.3088 0.3277 0.2818 0.2940 0.2766 1 TABLE NR. 2.2.1.7 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0553 -0.1067 -.484 -0.0261 -0.0813 -.406 -0.0030 -0.0683 -.327 0.0090 -0.0572 -.248 0.0408 -0.0593 -.168 0.0441 -0.0646 -.089 0.0446 -0.0595 -.010 0.0429 -0.0910 0.069 0.0261 -0.1118 0.148 0.0076 -0.1462 0.227 -0.0165 -0.1796 0.306 -0.0429 -0.2073 0.386 -0.0585 -0.2297 0.465 -0.0587 -0.2408 0.544 -0.0546 -0.2344 0.623 -0.0339 -0.2229 0.702 -0.0133 -0.2023 0.781 0.0038 -0.1757 0.860 0.0212 -0.1458 0.941 0.0328 -0.1242 1.019 0.0252 -0.0997 1.098 0.0128 -0.0847 1 TABLE NR. 2.2.1.8 RE=3*10E6 CL=0.50 DLR-F4 WING SECTION 1 2 3 4 5 6 7 ETA = 0.185 0.238 0.331 0.409 0.512 0.636 0.844 X/C CP CP CP CP CP CP CP 1.000 0.0973 0.1053 0.0744 -0.0075 -0.0342 -0.0260 0.0814 0.950 0.0202 0.0388 0.0142 -0.0647 -0.0807 -0.0522 0.0357 0.900 -0.0764 -0.0550 -0.0619 -0.1213 -0.1303 -0.0897 -0.0268 0.800 -0.2504 -0.2424 -0.2355 -0.2750 -0.2353 -0.1788 -0.1824 0.700 -0.4184 -0.4264 -0.4367 -0.4598 -0.3622 -0.3056 -0.3610 0.650 -0.4961 -0.5141 -0.5884 -0.8036 99.5490 -0.3852 -0.4115 0.600 -0.6269 -0.6406 -0.8372 -0.9624 -0.5814 100.0400 -0.4273 0.550 -0.7138 -0.7176 -0.8410 -0.9178 -1.0739 100.0400 -0.4825 0.500 -0.7052 -0.7670 -0.8481 -0.9291 -1.0595 -1.0323 -0.8906 0.450 -0.7941 -0.8289 -0.9091 -1.0323 -1.0670 -1.0336 -0.9771 0.425 -0.8037 -0.8398 -0.9275 -1.0516 -1.0680 -1.0687 -0.9786 0.400 -0.7956 -0.8403 -0.8659 -1.0514 -1.0452 -1.0512 -0.9544 0.350 -0.7824 -0.8228 -0.8574 -1.0668 -1.0332 -1.0110 -0.9589 0.300 -0.8247 -0.9039 -1.0491 -1.0437 -1.0410 -1.0288 -0.9541 0.250 -0.8009 -0.8926 -1.0755 -1.0549 -1.0281 -1.0085 -0.9613 0.200 -0.8000 -0.8660 -1.0913 -1.0967 -1.0686 -1.0257 -0.9726 0.150 -0.7947 -0.9956 -1.1660 -1.0401 -1.0221 -1.0168 -0.9438 0.100 -0.8453 -1.1394 -1.1753 -1.1134 -1.1023 -1.1085 -1.0478 0.050 -1.0399 -1.1507 -1.1118 -0.9972 -0.9559 -0.9156 -0.8929 0.030 -1.0001 -1.0508 -0.8745 -0.6888 -0.6750 -0.6127 -0.5725 0.020 -0.7950 -0.7490 -0.5319 -0.4710 -0.4393 -0.4335 -0.3589 0.010 -0.1908 -0.0498 -0.0820 -0.0860 0.0060 -0.0160 0.0051 0.000 0.8380 0.7963 0.7276 0.8018 0.7664 0.8401 0.8573 0.010 0.6040 0.6088 0.5188 0.4369 0.3898 0.3901 0.3878 0.030 0.2862 0.2897 0.1847 0.1162 0.1233 0.1317 0.0687 0.050 0.0788 0.0461 0.0070 0.0346 0.0459 0.0421 -0.0089 0.100 -0.1350 -0.1556 -0.1312 -0.0950 99.9460 -0.0784 -0.1150 0.200 -0.2483 -0.2682 -0.2267 -0.2239 -0.1909 -0.1802 -0.2067 0.300 -0.3100 -0.3606 -0.3916 -0.3915 -0.3497 -0.3197 100.0500 0.400 -0.3754 -0.4101 -0.4188 -0.3999 -0.3288 -0.3155 -0.3408 0.500 -0.4113 -0.4160 -0.3659 -0.3271 -0.2647 -0.2627 -0.2562 0.600 -0.2412 -0.2385 -0.2220 -0.2322 -0.1738 -0.1743 -0.1678 0.700 0.0237 0.0401 0.0393 0.0237 0.0404 100.0400 0.0445 0.800 0.2005 0.2146 0.2369 0.2188 0.2132 0.2148 0.2127 0.900 0.2526 0.2810 0.3094 0.3171 0.2816 0.2817 0.2788 0.950 0.2402 0.2789 0.3065 0.3210 0.2557 0.2710 0.2714 1 TABLE NR. 2.2.1.8 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0559 -0.1010 -.484 -0.0251 -0.0774 -.406 -0.0022 -0.0637 -.327 0.0092 -0.0518 -.248 0.0433 -0.0535 -.168 0.0466 -0.0583 -.089 0.0484 -0.0548 -.010 0.0459 -0.0866 0.069 0.0274 -0.1078 0.148 0.0078 -0.1434 0.227 -0.0192 -0.1822 0.306 -0.0465 -0.2151 0.386 -0.0631 -0.2441 0.465 -0.0644 -0.2605 0.544 -0.0592 -0.2539 0.623 -0.0384 -0.2397 0.702 -0.0171 -0.2172 0.781 0.0008 -0.1874 0.860 0.0189 -0.1530 0.941 0.0322 -0.1296 1.019 0.0242 -0.1024 1.098 0.0118 -0.0852 1 TABLE NR. 2.2.1.9 RE=3*10E6 CL=0.50 DLR-F4 WING SECTION 1 2 3 4 5 6 7 ETA = 0.185 0.238 0.331 0.409 0.512 0.636 0.844 X/C CP CP CP CP CP CP CP 1.000 0.0864 0.0971 0.0587 -0.0509 -0.1449 -0.0986 0.0683 0.950 0.0161 0.0355 -0.0029 -0.1336 -0.2158 -0.1375 0.0285 0.900 -0.0715 -0.0505 -0.0718 -0.1873 -0.2450 -0.1604 -0.0217 0.800 -0.2353 -0.2227 -0.2262 -0.3157 -0.2985 -0.2125 -0.1575 0.700 -0.3924 -0.3897 -0.4144 -0.4513 -0.3662 -0.2885 -0.3142 0.650 -0.5196 -0.5452 -0.7137 -0.6363 99.5920 -0.3370 -0.3724 0.600 -0.7520 -0.7529 -0.8948 -0.9591 -0.4500 100.0500 -0.4262 0.550 -0.7556 -0.8029 -0.8968 -1.0709 -0.5383 100.0500 -0.5966 0.500 -0.7621 -0.8094 -0.8992 -1.0402 -1.0729 -0.7811 -0.9738 0.450 -0.8091 -0.8447 -0.9240 -1.0823 -1.0815 -1.0416 -0.9996 0.425 -0.8188 -0.8630 -0.9329 -1.0949 -1.0813 -1.0788 -1.0025 0.400 -0.8009 -0.8535 -0.8640 -1.0741 -1.0501 -1.0592 -0.9700 0.350 -0.7951 -0.8381 -0.9282 -1.0780 -1.0439 -1.0126 -0.9690 0.300 -0.8321 -0.9221 -1.0940 -1.0566 -1.0513 -1.0378 -0.9638 0.250 -0.8245 -0.9015 -1.1083 -1.0669 -1.0400 -1.0169 -0.9636 0.200 -0.8175 -0.9063 -1.1057 -1.0989 -1.0717 -1.0311 -0.9689 0.150 -0.8331 -0.9981 -1.1678 -1.0409 -1.0217 -1.0128 -0.9381 0.100 -0.8721 -1.1529 -1.1697 -1.1046 -1.0916 -1.0951 -1.0331 0.050 -1.0657 -1.1468 -1.0989 -0.9849 -0.9412 -0.9026 -0.8769 0.030 -1.0060 -1.0432 -0.8699 -0.6846 -0.6666 -0.6036 -0.5630 0.020 -0.7952 -0.7457 -0.5291 -0.4698 -0.4365 -0.4263 -0.3506 0.010 -0.1956 -0.0526 -0.0826 -0.0886 0.0056 -0.0131 0.0133 0.000 0.8365 0.7954 0.7249 0.7973 0.7612 0.8404 0.8570 0.010 0.6210 0.6237 0.5330 0.4517 0.4015 0.3961 0.3938 0.030 0.3098 0.3113 0.2054 0.1342 0.1373 0.1392 0.0752 0.050 0.1003 0.0678 0.0264 0.0496 0.0562 0.0478 -0.0067 0.100 -0.1148 -0.1365 -0.1126 -0.0809 99.9560 -0.0776 -0.1101 0.200 -0.2354 -0.2538 -0.2151 -0.2140 -0.1864 -0.1820 -0.2091 0.300 -0.3008 -0.3542 -0.3891 -0.3925 -0.3574 -0.3342 100.0500 0.400 -0.3748 -0.4134 -0.4266 -0.4100 -0.3450 -0.3410 -0.3543 0.500 -0.4184 -0.4231 -0.3733 -0.3350 -0.2890 -0.2907 -0.2686 0.600 -0.2451 -0.2413 -0.2276 -0.2428 -0.1960 -0.2041 -0.1769 0.700 0.0233 0.0398 0.0361 0.0154 0.0145 100.0400 0.0410 0.800 0.2009 0.2145 0.2342 0.2122 0.1913 0.1950 0.2075 0.900 0.2523 0.2806 0.3062 0.3081 0.2516 0.2584 0.2750 0.950 0.2384 0.2772 0.3015 0.3083 0.2091 0.2433 0.2691 1 TABLE NR. 2.2.1.9 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0531 -0.1002 -.484 -0.0223 -0.0763 -.406 0.0017 -0.0617 -.327 0.0133 -0.0494 -.248 0.0469 -0.0522 -.168 0.0513 -0.0558 -.089 0.0534 -0.0523 -.010 0.0525 -0.0850 0.069 0.0338 -0.1098 0.148 0.0140 -0.1478 0.227 -0.0152 -0.1888 0.306 -0.0436 -0.2229 0.386 -0.0614 -0.2565 0.465 -0.0639 -0.2750 0.544 -0.0604 -0.2725 0.623 -0.0394 -0.2585 0.702 -0.0171 -0.2291 0.781 0.0027 -0.1952 0.860 0.0202 -0.1564 0.941 0.0332 -0.1308 1.019 0.0262 -0.1020 1.098 0.0135 -0.0840 1 TABLE NR. 2.2.1.10 RE=3*10E6 CL=0.50 DLR-F4 WING SECTION 1 2 3 4 5 6 7 ETA = 0.185 0.238 0.331 0.409 0.512 0.636 0.844 X/C CP CP CP CP CP CP CP 1.000 0.0612 0.0734 0.0146 -0.1468 -0.2320 -0.1649 0.0126 0.950 0.0022 0.0166 -0.0613 -0.2676 -0.2914 -0.2101 -0.0237 0.900 -0.0744 -0.0571 -0.1277 -0.3254 -0.3052 -0.2296 -0.0548 0.800 -0.2196 -0.2087 -0.2645 -0.4242 -0.3305 -0.2678 -0.1391 0.700 -0.3922 -0.3953 -0.4294 -0.4942 -0.3643 -0.3187 -0.2642 0.650 -0.7412 -0.7663 -0.7614 -0.5392 99.6150 -0.3455 -0.3376 0.600 -0.8026 -0.8282 -0.9337 -0.7895 -0.4118 100.0500 -0.4234 0.550 -0.7844 -0.8415 -0.9237 -1.0810 -0.4432 100.0500 -0.6284 0.500 -0.7926 -0.8248 -0.9168 -1.0712 -0.5390 -0.4965 -0.9894 0.450 -0.8190 -0.8718 -0.9173 -1.0967 -1.0584 -0.7525 -1.0022 0.425 -0.8277 -0.8780 -0.9228 -1.0951 -1.0685 -0.9865 -0.9970 0.400 -0.8109 -0.8709 -0.8895 -1.0759 -1.0422 -1.0437 -0.9698 0.350 -0.8074 -0.8563 -1.0389 -1.0751 -1.0372 -1.0052 -0.9632 0.300 -0.8357 -0.9152 -1.0947 -1.0398 -1.0332 -1.0170 -0.9499 0.250 -0.8206 -0.8946 -1.1033 -1.0527 -1.0202 -0.9955 -0.9476 0.200 -0.8126 -0.9021 -1.0942 -1.0777 -1.0485 -1.0058 -0.9425 0.150 -0.8251 -1.0250 -1.1459 -1.0193 -0.9966 -0.9862 -0.9061 0.100 -0.9484 -1.1501 -1.1490 -1.0801 -1.0631 -1.0631 -0.9965 0.050 -1.0757 -1.1297 -1.0733 -0.9589 -0.9135 -0.8721 -0.8397 0.030 -0.9906 -1.0171 -0.8474 -0.6622 -0.6409 -0.5734 -0.5262 0.020 -0.7805 -0.7268 -0.5122 -0.4484 -0.4111 -0.3979 -0.3229 0.010 -0.1860 -0.0423 -0.0710 -0.0754 0.0204 0.0072 0.0408 0.000 0.8398 0.7985 0.7262 0.8008 0.7681 0.8451 0.8637 0.010 0.6382 0.6372 0.5434 0.4591 0.3997 0.3945 0.3852 0.030 0.3315 0.3295 0.2202 0.1438 0.1411 0.1395 0.0678 0.050 0.1256 0.0896 0.0429 0.0616 0.0574 0.0493 -0.0103 0.100 -0.0964 -0.1204 -0.0989 -0.0734 99.9480 -0.0830 -0.1188 0.200 -0.2263 -0.2452 -0.2119 -0.2151 -0.1933 -0.1947 -0.2208 0.300 -0.2961 -0.3525 -0.3955 -0.4093 -0.3801 -0.3631 100.0500 0.400 -0.3861 -0.4309 -0.4601 -0.4504 -0.3780 -0.3802 -0.3991 0.500 -0.4471 -0.4578 -0.4005 -0.3610 -0.3099 -0.3248 -0.2992 0.600 -0.2547 -0.2502 -0.2411 -0.2646 -0.2285 -0.2352 -0.2018 0.700 0.0209 0.0358 0.0283 0.0002 -0.0100 100.0400 0.0206 0.800 0.1991 0.2100 0.2238 0.1945 0.1677 0.1747 0.1898 0.900 0.2507 0.2760 0.2965 0.2898 0.2290 0.2400 0.2565 0.950 0.2341 0.2705 0.2896 0.2849 0.1860 0.2216 0.2467 1 TABLE NR. 2.2.1.10 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0507 -0.0959 -.484 -0.0186 -0.0712 -.406 0.0071 -0.0565 -.327 0.0196 -0.0435 -.248 0.0544 -0.0452 -.168 0.0592 -0.0494 -.089 0.0604 -0.0460 -.010 0.0592 -0.0785 0.069 0.0398 -0.1037 0.148 0.0187 -0.1437 0.227 -0.0121 -0.1859 0.306 -0.0438 -0.2283 0.386 -0.0645 -0.2701 0.465 -0.0705 -0.2973 0.544 -0.0657 -0.3046 0.623 -0.0438 -0.2888 0.702 -0.0207 -0.2519 0.781 -0.0010 -0.2105 0.860 0.0185 -0.1646 0.941 0.0317 -0.1320 1.019 0.0250 -0.1030 1.098 0.0125 -0.0821 1 TABLE NR. 3.2.1.1 RE=3*10E6 CL=0.30 DLR-F4 WING SECTION 1 2 3 4 5 6 7 ETA = 0.185 0.238 0.331 0.409 0.512 0.636 0.844 X/C CP CP CP CP CP CP CP 1.000 0.1265 0.1283 0.0992 0.0513 0.0670 0.0716 0.0945 0.950 0.0155 0.0285 0.0120 -0.0199 0.0015 -0.0018 0.0212 0.900 -0.1037 -0.0890 -0.0928 -0.1198 -0.0866 -0.0939 -0.0649 0.800 -0.2800 -0.2788 -0.2951 -0.3534 -0.2961 -0.2926 -0.2535 0.700 -0.4148 -0.4347 -0.4992 -0.5659 -0.4992 -0.4817 -0.4591 0.650 -0.4644 -0.4912 -0.5766 -0.6686 99.3980 -0.5784 -0.5207 0.600 -0.4885 -0.5221 -0.6036 -0.6847 -0.6349 100.0400 -0.5494 0.550 -0.5071 -0.5254 -0.5929 -0.6572 -0.6236 100.0400 -0.5284 0.500 -0.4934 -0.5113 -0.5753 -0.6213 -0.6280 -0.5777 -0.5319 0.450 -0.5075 -0.5319 -0.5772 -0.6112 -0.6362 -0.5623 -0.5278 0.425 -0.5326 -0.5558 -0.6069 -0.6430 -0.6562 -0.6119 -0.5538 0.400 -0.5487 -0.5818 -0.5797 -0.6599 -0.6545 -0.6234 -0.5510 0.350 -0.5551 -0.5679 -0.6174 -0.6415 -0.6299 -0.5931 -0.5407 0.300 -0.5721 -0.5920 -0.6333 -0.6139 -0.6574 -0.6303 -0.5535 0.250 -0.6024 -0.6614 -0.6753 -0.6520 -0.6230 -0.6167 -0.5411 0.200 -0.6489 -0.6773 -0.7040 -0.6577 -0.5967 -0.5669 -0.5185 0.150 -0.6375 -0.7181 -0.7003 -0.5911 -0.6137 -0.5792 -0.4567 0.100 -0.6710 -0.7077 -0.8640 -0.7752 -0.7543 -0.7090 -0.6013 0.050 -0.7872 -0.9336 -1.0754 -0.9449 -0.8714 -0.8302 -0.6597 0.030 -0.8132 -0.9418 -0.8331 -0.6102 -0.5804 -0.4989 -0.3744 0.020 -0.6633 -0.6735 -0.4696 -0.3684 -0.3272 -0.3046 -0.1703 0.010 -0.0868 0.0203 -0.0050 0.0302 0.1314 0.1266 0.2071 0.000 0.8571 0.8157 0.7660 0.8316 0.8171 0.8662 0.8834 0.010 0.4690 0.4820 0.3829 0.2657 0.2006 0.1906 0.1445 0.030 0.1108 0.1264 0.0173 -0.0629 -0.0639 -0.0595 -0.1639 0.050 -0.0841 -0.1166 -0.1547 -0.1241 -0.1161 -0.1210 -0.2242 0.100 -0.2688 -0.2961 -0.2670 -0.2115 99.7880 -0.2001 -0.2679 0.200 -0.3436 -0.3659 -0.3233 -0.3061 -0.2842 -0.2759 -0.3026 0.300 -0.3725 -0.4212 -0.4463 -0.4491 -0.4046 -0.3763 100.0400 0.400 -0.4060 -0.4348 -0.4416 -0.4285 -0.3646 -0.3509 -0.3746 0.500 -0.4075 -0.4121 -0.3751 -0.3440 -0.2853 -0.2764 -0.2808 0.600 -0.2540 -0.2540 -0.2405 -0.2492 -0.1832 -0.1797 -0.1828 0.700 0.0033 0.0188 0.0169 0.0052 0.0314 100.0300 0.0281 0.800 0.1810 0.1958 0.2185 0.2024 0.2110 0.2144 0.1968 0.900 0.2356 0.2645 0.2932 0.3030 0.2843 0.2809 0.2643 0.950 0.2317 0.2674 0.2936 0.3134 0.2719 0.2813 0.2613 1 TABLE NR. 3.2.1.1 RE=3*10E6 CL=0.30 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0663 -0.1003 -.484 -0.0397 -0.0783 -.406 -0.0198 -0.0656 -.327 -0.0125 -0.0543 -.248 0.0158 -0.0566 -.168 0.0146 -0.0579 -.089 0.0111 -0.0459 -.010 0.0065 -0.0695 0.069 -0.0141 -0.0806 0.148 -0.0303 -0.1028 0.227 -0.0573 -0.1228 0.306 -0.0760 -0.1380 0.386 -0.0857 -0.1534 0.465 -0.0832 -0.1588 0.544 -0.0755 -0.1556 0.623 -0.0538 -0.1534 0.702 -0.0329 -0.1439 0.781 -0.0169 -0.1327 0.860 0.0007 -0.1130 0.941 0.0144 -0.1032 1.019 0.0087 -0.0839 1.098 -0.0035 -0.0739 1 TABLE NR. 3.2.1.2 RE=3*10E6 CL=0.40 DLR-F4 WING SECTION 1 2 3 4 5 6 7 ETA = 0.185 0.238 0.331 0.409 0.512 0.636 0.844 X/C CP CP CP CP CP CP CP 1.000 0.1180 0.1214 0.0975 0.0392 0.0485 0.0523 0.0813 0.950 0.0144 0.0278 0.0091 -0.0255 -0.0050 -0.0078 0.0209 0.900 -0.1019 -0.0866 -0.0944 -0.1178 -0.0824 -0.0893 -0.0580 0.800 -0.2810 -0.2801 -0.2992 -0.3511 -0.2893 -0.2853 -0.2482 0.700 -0.4253 -0.4464 -0.5133 -0.5755 -0.5035 -0.4861 -0.4603 0.650 -0.4829 -0.5118 -0.6035 -0.6990 99.3870 -0.5914 -0.5313 0.600 -0.5120 -0.5478 -0.6370 -0.7274 -0.6598 100.0400 -0.5675 0.550 -0.5369 -0.5561 -0.6315 -0.7082 -0.6604 100.0400 -0.5546 0.500 -0.5251 -0.5428 -0.6132 -0.6639 -0.6713 -0.6213 -0.5649 0.450 -0.5476 -0.5717 -0.6220 -0.6658 -0.6963 -0.6139 -0.5791 0.425 -0.5752 -0.6007 -0.6635 -0.7085 -0.7161 -0.6704 -0.6038 0.400 -0.5904 -0.6270 -0.6363 -0.7190 -0.7090 -0.6823 -0.6083 0.350 -0.6072 -0.6167 -0.6769 -0.7150 -0.7240 -0.6640 -0.6069 0.300 -0.6308 -0.6422 -0.6644 -0.6835 -0.7188 -0.7142 -0.6313 0.250 -0.6915 -0.7232 -0.7573 -0.6948 -0.6985 -0.7142 -0.6227 0.200 -0.7483 -0.8151 -0.6755 -0.6313 -0.6433 -0.6530 -0.6554 0.150 -0.7374 -0.8163 -1.0228 -1.0048 -0.9819 -0.8051 -0.5512 0.100 -0.7965 -1.0419 -1.2214 -1.1810 -1.1192 -1.0887 -0.8383 0.050 -0.9560 -1.1747 -1.2258 -1.1073 -1.0601 -1.0121 -0.9282 0.030 -1.0352 -1.1577 -0.9784 -0.7771 -0.7580 -0.6901 -0.5960 0.020 -0.8595 -0.8369 -0.6202 -0.5538 -0.5266 -0.5089 -0.3816 0.010 -0.2257 -0.0976 -0.1370 -0.1368 -0.0459 -0.0621 -0.0068 0.000 0.8255 0.7836 0.7155 0.7926 0.7567 0.8345 0.8583 0.010 0.5466 0.5564 0.4798 0.4025 0.3534 0.3522 0.3295 0.030 0.2097 0.2248 0.1301 0.0700 0.0802 0.0884 0.0072 0.050 0.0135 -0.0131 -0.0389 0.0025 0.0129 0.0128 -0.0580 0.100 -0.1847 -0.2064 -0.1701 -0.1115 99.9090 -0.0937 -0.1470 0.200 -0.2790 -0.2984 -0.2471 -0.2278 -0.2007 -0.1903 -0.2227 0.300 -0.3274 -0.3674 -0.3838 -0.3775 -0.3326 -0.3067 100.0400 0.400 -0.3644 -0.3894 -0.3894 -0.3709 -0.3109 -0.2973 -0.3232 0.500 -0.3737 -0.3779 -0.3386 -0.3034 -0.2551 -0.2387 -0.2480 0.600 -0.2340 -0.2346 -0.2180 -0.2236 -0.1612 -0.1587 -0.1648 0.700 0.0155 0.0312 0.0305 0.0204 0.0422 100.0300 0.0393 0.800 0.1903 0.2072 0.2314 0.2168 0.2220 0.2274 0.2078 0.900 0.2422 0.2721 0.3034 0.3144 0.2941 0.2927 0.2740 0.950 0.2342 0.2724 0.3019 0.3184 0.2768 0.2881 0.2664 1 TABLE NR. 3.2.1.2 RE=3*10E6 CL=0.40 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0630 -0.1048 -.484 -0.0349 -0.0840 -.406 -0.0145 -0.0730 -.327 -0.0072 -0.0613 -.248 0.0252 -0.0634 -.168 0.0249 -0.0661 -.089 0.0243 -0.0592 -.010 0.0210 -0.0858 0.069 0.0048 -0.1000 0.148 -0.0107 -0.1243 0.227 -0.0321 -0.1460 0.306 -0.0515 -0.1644 0.386 -0.0632 -0.1758 0.465 -0.0624 -0.1836 0.544 -0.0562 -0.1788 0.623 -0.0372 -0.1726 0.702 -0.0202 -0.1626 0.781 -0.0029 -0.1478 0.860 0.0109 -0.1273 0.941 0.0223 -0.1141 1.019 0.0156 -0.0940 1.098 0.0035 -0.0819 1 TABLE NR. 3.2.1.3 RE=3*10E6 CL=0.60 DLR-F4 WING SECTION 1 2 3 4 5 6 7 ETA = 0.185 0.238 0.331 0.409 0.512 0.636 0.844 X/C CP CP CP CP CP CP CP 1.000 0.1079 0.1146 0.1045 0.0536 0.0669 0.0681 0.0827 0.950 0.0131 0.0297 0.0108 -0.0216 0.0000 -0.0039 0.0191 0.900 -0.0954 -0.0802 -0.0937 -0.1192 -0.0852 -0.0914 -0.0610 0.800 -0.2747 -0.2760 -0.2969 -0.3502 -0.2882 -0.2839 -0.2473 0.700 -0.4288 -0.4503 -0.5124 -0.5668 -0.4884 -0.4702 -0.4585 0.650 -0.4942 -0.5222 -0.6005 -0.6659 99.4210 -0.5552 -0.5286 0.600 -0.5338 -0.5659 -0.6410 -0.6981 -0.6137 100.0400 -0.5632 0.550 -0.5717 -0.5845 -0.6388 -0.6646 -0.5885 100.0400 -0.5498 0.500 -0.5710 -0.5805 -0.6254 -0.6313 -0.5833 -0.5304 -0.5372 0.450 -0.6010 -0.6105 -0.6227 -0.6146 -0.6057 -0.5479 -0.5254 0.425 -0.6349 -0.6395 -0.6438 -0.6501 -0.6878 -0.6293 -0.5257 0.400 -0.6595 -0.6646 -0.6298 -0.6907 -0.8151 -0.7140 -0.5301 0.350 -0.7398 -0.6659 -0.6759 -1.2931 -1.2756 -1.2698 -0.5918 0.300 -0.8768 -0.9276 -0.9321 -1.2921 -1.3095 -1.3061 -1.1669 0.250 -0.9141 -0.9987 -1.3724 -1.3450 -1.3265 -1.3109 -1.2512 0.200 -0.9372 -0.9841 -1.3865 -1.3936 -1.3788 -1.3487 -1.2908 0.150 -0.9402 -1.2179 -1.4629 -1.3517 -1.3395 -1.3466 -1.2733 0.100 -1.1053 -1.4841 -1.4994 -1.4422 -1.4416 -1.4511 -1.3864 0.050 -1.4040 -1.4823 -1.4344 -1.3228 -1.2934 -1.2552 -1.2284 0.030 -1.3251 -1.3670 -1.1958 -1.0222 -1.0191 -0.9659 -0.9322 0.020 -1.1093 -1.0574 -0.8385 -0.8214 -0.7931 -0.7929 -0.7064 0.010 -0.4370 -0.2792 -0.3358 -0.3948 -0.3172 -0.3379 -0.3153 0.000 0.7541 0.7108 0.6044 0.6948 0.6122 0.7330 0.7728 0.010 0.6632 0.6642 0.6148 0.5839 0.5531 0.5630 0.5644 0.030 0.3734 0.3863 0.3119 0.2734 0.2954 0.3155 0.2550 0.050 0.1687 0.1486 0.1372 0.1735 0.1964 0.2035 0.1643 0.100 -0.0560 -0.0640 -0.0307 0.0299 100.0400 0.0607 0.0344 0.200 -0.1726 -0.1844 -0.1192 -0.0991 -0.0806 -0.0561 -0.0792 0.300 -0.2348 -0.2666 -0.2712 -0.2536 -0.2042 -0.1817 100.0400 0.400 -0.2859 -0.3043 -0.2940 -0.2663 -0.2094 -0.1937 -0.2227 0.500 -0.3127 -0.3128 -0.2678 -0.2270 -0.1723 -0.1619 -0.1762 0.600 -0.1948 -0.1928 -0.1694 -0.1657 -0.1048 -0.1018 -0.1169 0.700 0.0380 0.0544 0.0579 0.0540 0.0748 100.0300 0.0644 0.800 0.2123 0.2287 0.2559 0.2457 0.2511 0.2581 0.2298 0.900 0.2570 0.2878 0.3232 0.3385 0.3209 0.3207 0.2937 0.950 0.2436 0.2844 0.3184 0.3377 0.3006 0.3128 0.2820 1 TABLE NR. 3.2.1.3 RE=3*10E6 CL=0.60 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0496 -0.1132 -.484 -0.0208 -0.0917 -.406 0.0015 -0.0834 -.327 0.0110 -0.0738 -.248 0.0452 -0.0793 -.168 0.0483 -0.0862 -.089 0.0514 -0.0866 -.010 0.0534 -0.1184 0.069 0.0424 -0.1389 0.148 0.0303 -0.1730 0.227 0.0111 -0.1959 0.306 -0.0106 -0.2180 0.386 -0.0215 -0.2296 0.465 -0.0231 -0.2324 0.544 -0.0212 -0.2217 0.623 -0.0064 -0.2097 0.702 0.0071 -0.1923 0.781 0.0184 -0.1703 0.860 0.0310 -0.1459 0.941 0.0405 -0.1279 1.019 0.0304 -0.1061 1.098 0.0157 -0.0914