TABLE NR. 2.1.1.1 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 0.1003 0.1016 0.0762 0.0355 0.0398 0.0463 0.0663 0.950 -0.0004 0.0034 -0.0255 -0.0495 -0.0357 -0.0270 -0.0061 0.900 -0.1135 -0.1117 -0.1306 -0.1533 -0.1271 -0.1659 -0.0947 0.800 -0.2810 -0.2802 -0.3091 -0.3693 -0.3186 -0.3048 -0.2681 0.700 -0.3975 -0.4082 -0.4615 -0.5298 -0.4817 -0.4622 -0.4213 0.650 -0.4423 -0.4571 -0.5250 -0.5982 -0.5557 -0.5286 -0.4858 0.600 -0.4607 -0.4817 -0.5457 -0.6107 -0.5749 -0.5580 -0.5091 0.550 -0.4791 -0.4981 -0.5595 -0.6125 -0.5864 -0.5590 -0.5081 0.500 -0.4871 -0.5032 -0.5601 -0.6123 -0.5892 -0.5583 -0.5083 0.450 -0.5098 -0.5286 -0.5740 -0.6145 -0.6050 -0.5722 -0.5199 0.425 -0.5316 -0.5549 -0.6003 -0.6308 -0.6223 -0.5890 -0.5407 0.400 -0.5506 -0.5783 -0.6235 -0.6560 -0.6322 -0.6099 -0.5507 0.350 -0.5759 -0.5980 -0.6403 -0.6736 -0.6492 -0.6182 -0.5743 0.300 -0.6049 -0.6332 -0.6747 -0.7019 -0.6840 -0.6514 -0.5940 0.250 -0.6590 -0.6987 -0.7308 -0.7400 -0.7010 -0.6874 -0.6235 0.200 -0.7150 -0.7591 -0.7788 -0.7731 -0.7508 -0.7155 -0.6439 0.150 -0.7762 -0.8333 -0.8629 -0.8790 -0.8250 -0.7809 -0.7316 0.100 -0.8754 -0.9724 -0.9060 -0.9299 -0.9890 -0.9641 -0.8556 0.050 -1.2649 -1.3787 -1.5155 -1.4286 -1.4276 -1.3850 -1.1386 0.030 -1.4234 -1.6290 -1.6493 -1.3501 -1.3039 -1.2597 -1.0420 0.020 -1.4661 -1.6154 -1.3257 -1.1817 -1.1776 -1.0913 -0.8489 0.010 -0.7527 -0.6341 -0.6870 -0.7602 -0.6199 -0.6280 -0.4234 0.000 0.6410 0.5739 0.4593 0.5401 0.4136 0.5688 0.6533 0.010 0.6371 0.6530 0.6304 0.6007 0.5971 0.5958 0.5510 0.030 0.3586 0.3657 0.3304 0.3050 0.3268 0.3400 0.2607 0.050 0.1458 0.1446 0.1638 0.2068 0.2161 0.2270 0.1616 0.100 -0.0594 -0.0562 -0.0049 0.0480 0.0503 0.0737 0.0365 0.200 -0.1712 -0.1751 -0.1406 -0.0787 -0.0533 -0.0561 -0.0886 0.300 -0.2108 -0.2234 -0.2108 -0.1756 -0.1718 -0.1669 -0.2040 0.400 -0.2417 -0.2554 -0.2316 -0.2036 -0.1677 -0.1647 -0.1898 0.500 -0.2709 -0.2586 -0.2141 -0.1713 -0.1372 -0.1329 -0.1469 0.600 -0.1588 -0.1616 -0.1426 -0.0601 -0.0933 -0.0883 -0.1030 0.700 0.0346 0.0452 0.0510 0.0510 0.0717 0.0678 0.0579 0.800 0.1977 0.2124 0.2367 0.2306 0.2380 0.2397 0.2183 0.900 0.2379 0.2677 0.3037 0.3138 0.3043 0.3009 0.2791 0.950 0.2267 0.1846 0.2999 0.3068 0.2986 0.2868 0.2641 1 TABLE NR. 2.1.1.1 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0526 -0.1256 -.484 -0.0308 -0.1042 -.406 -0.0111 -0.0920 -.327 0.0055 -0.0834 -.248 0.0207 -0.0904 -.168 0.0230 -0.0960 -.089 0.0325 -0.0832 -.010 0.0293 -0.1071 0.069 0.0205 -0.1159 0.148 0.0168 -0.1303 0.227 0.0057 -0.1415 0.306 -0.0061 -0.1489 0.386 -0.0149 -0.1563 0.465 -0.0144 -0.1536 0.544 -0.0110 -0.1507 0.623 -0.0049 -0.1487 0.702 0.0028 -0.1406 0.781 0.0098 -0.1318 0.860 0.0187 -0.1181 0.941 0.0228 -0.1111 1.019 0.0151 -0.1000 1.098 0.0024 -0.0920 1 TABLE NR. 2.1.1.2 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 0.0958 0.1048 0.0797 0.0289 0.0299 0.0391 0.0624 0.950 0.0103 0.0165 -0.0107 -0.0395 -0.0247 -0.0166 0.0078 0.900 -0.1020 -0.0992 -0.1139 -0.1325 -0.1024 -0.1535 -0.0703 0.800 -0.2868 -0.2873 -0.3102 -0.3664 -0.3003 -0.2904 -0.2524 0.700 -0.4272 -0.4402 -0.4953 -0.5634 -0.4960 -0.4746 -0.4319 0.650 -0.4807 -0.5009 -0.5760 -0.6563 -0.5927 -0.5592 -0.5149 0.600 -0.5034 -0.5265 -0.6005 -0.6768 -0.6192 -0.6035 -0.5425 0.550 -0.5209 -0.5439 -0.6142 -0.6756 -0.6349 -0.6066 -0.5443 0.500 -0.5256 -0.5432 -0.6061 -0.6655 -0.6433 -0.6014 -0.5466 0.450 -0.5458 -0.5672 -0.6177 -0.6648 -0.6567 -0.6215 -0.5600 0.425 -0.5702 -0.5970 -0.6486 -0.6822 -0.6777 -0.6387 -0.5837 0.400 -0.5912 -0.6232 -0.6750 -0.7142 -0.6922 -0.6609 -0.5989 0.350 -0.6148 -0.6339 -0.6830 -0.7226 -0.7005 -0.6703 -0.6199 0.300 -0.6436 -0.6666 -0.7101 -0.7488 -0.7356 -0.7040 -0.6425 0.250 -0.7027 -0.7415 -0.7611 -0.7732 -0.7406 -0.7300 -0.6705 0.200 -0.7561 -0.7962 -0.7652 -0.7565 -0.7438 -0.7246 -0.6822 0.150 -0.8053 -0.8651 -0.6886 -0.7233 -0.7151 -0.6996 -0.7383 0.100 -0.8632 -0.9909 -1.4500 -1.3896 -1.3393 -1.3014 -1.0416 0.050 -1.2082 -1.4472 -1.5950 -1.4696 -1.4253 -1.3659 -1.2777 0.030 -1.3759 -1.5241 -1.3617 -1.0475 -1.0411 -1.0393 -0.8856 0.020 -1.2576 -1.3083 -0.9654 -0.8952 -0.8915 -0.8185 -0.6517 0.010 -0.4581 -0.3473 -0.3816 -0.4445 -0.3337 -0.3493 -0.2108 0.000 0.7318 0.6811 0.6040 0.6683 0.5904 0.6928 0.7427 0.010 0.6234 0.6314 0.5905 0.5414 0.5355 0.5406 0.5094 0.030 0.3305 0.3297 0.2735 0.2411 0.2634 0.2876 0.2177 0.050 0.1174 0.1039 0.1084 0.1487 0.1594 0.1814 0.1225 0.100 -0.0916 -0.0975 -0.0544 -0.0062 -0.0045 0.0318 -0.0042 0.200 -0.2045 -0.2186 -0.1909 -0.1277 -0.0949 -0.0924 -0.1236 0.300 -0.2462 -0.2663 -0.2667 -0.2381 -0.2248 -0.2109 -0.2530 0.400 -0.2839 -0.3023 -0.2871 -0.2609 -0.2170 -0.2126 -0.2346 0.500 -0.3193 -0.3071 -0.2622 -0.2170 -0.1765 -0.1699 -0.1823 0.600 -0.1846 -0.1891 -0.1721 -0.0867 -0.1185 -0.1128 -0.1271 0.700 0.0332 0.0437 0.0484 0.0436 0.0658 0.0630 0.0523 0.800 0.2052 0.2197 0.2440 0.2321 0.2366 0.2395 0.2178 0.900 0.2484 0.2801 0.3159 0.3204 0.3053 0.3034 0.2805 0.950 0.2356 0.1924 0.3128 0.3158 0.3009 0.2891 0.2679 1 TABLE NR. 2.1.1.2 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0553 -0.1207 -.484 -0.0311 -0.0976 -.406 -0.0086 -0.0837 -.327 0.0078 -0.0744 -.248 0.0271 -0.0817 -.168 0.0297 -0.0876 -.089 0.0383 -0.0757 -.010 0.0333 -0.1039 0.069 0.0230 -0.1185 0.148 0.0134 -0.1388 0.227 0.0002 -0.1573 0.306 -0.0173 -0.1687 0.386 -0.0292 -0.1797 0.465 -0.0294 -0.1783 0.544 -0.0260 -0.1758 0.623 -0.0148 -0.1712 0.702 -0.0043 -0.1612 0.781 0.0077 -0.1482 0.860 0.0189 -0.1312 0.941 0.0255 -0.1184 1.019 0.0195 -0.1051 1.098 0.0061 -0.0940 1 TABLE NR. 2.1.1.3 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 0.0880 0.1070 0.0768 0.0271 0.0324 0.0417 0.0737 0.950 0.0148 0.0253 0.0028 -0.0305 -0.0152 -0.0059 0.0196 0.900 -0.0881 -0.0855 -0.0951 -0.1149 -0.0861 -0.1414 -0.0587 0.800 -0.2832 -0.2819 -0.2990 -0.3494 -0.2827 -0.2770 -0.2445 0.700 -0.4473 -0.4591 -0.5112 -0.5758 -0.4961 -0.4807 -0.4423 0.650 -0.5156 -0.5361 -0.6285 -0.7317 -0.6171 -0.5797 -0.5445 0.600 -0.5411 -0.5672 -0.6542 -0.7555 -0.6643 -0.6407 -0.5791 0.550 -0.5556 -0.5826 -0.6619 -0.7320 -0.6809 -0.6406 -0.5807 0.500 -0.5557 -0.5720 -0.6319 -0.6847 -0.6904 -0.6300 -0.5729 0.450 -0.5762 -0.5941 -0.6423 -0.6827 -0.7026 -0.6421 -0.5863 0.425 -0.6041 -0.6329 -0.6817 -0.7160 -0.7193 -0.6625 -0.6183 0.400 -0.6240 -0.6572 -0.7158 -0.7411 -0.7240 -0.6805 -0.6467 0.350 -0.6460 -0.6486 -0.6765 -0.6942 -0.6794 -0.6494 -0.6517 0.300 -0.6877 -0.6814 -0.6820 -0.6590 -0.6558 -0.6349 -0.6560 0.250 -0.8055 -0.8527 -0.7381 -0.9446 -0.8806 -0.7121 -0.6275 0.200 -0.8338 -0.9155 -1.0594 -1.1841 -1.1730 -1.1721 -0.6005 0.150 -0.7921 -0.8739 -1.2866 -1.2252 -1.2081 -1.1939 -1.0615 0.100 -0.8927 -1.1707 -1.3178 -1.3191 -1.3084 -1.3066 -1.2110 0.050 -1.0699 -1.3220 -1.3465 -1.2277 -1.1882 -1.1467 -1.1330 0.030 -1.1903 -1.2787 -1.1174 -0.8262 -0.8258 -0.8215 -0.7252 0.020 -1.0321 -1.0625 -0.7470 -0.6670 -0.6661 -0.6080 -0.4976 0.010 -0.2953 -0.1908 -0.2123 -0.2584 -0.1487 -0.1723 -0.0723 0.000 0.7889 0.7346 0.6736 0.7400 0.6851 0.7615 0.7835 0.010 0.6110 0.6132 0.5495 0.4811 0.4821 0.4800 0.4691 0.030 0.3129 0.2993 0.2289 0.1818 0.2046 0.2361 0.1787 0.050 0.0948 0.0713 0.0615 0.0962 0.1070 0.1353 0.0830 0.100 -0.1194 -0.1299 -0.0966 -0.0524 -0.0527 -0.0067 -0.0389 0.200 -0.2320 -0.2487 -0.2312 -0.1701 -0.1397 -0.1292 -0.1586 0.300 -0.2721 -0.3010 -0.3110 -0.2937 -0.2755 -0.2544 -0.2950 0.400 -0.3187 -0.3450 -0.3330 -0.3097 -0.2588 -0.2487 -0.2699 0.500 -0.3584 -0.3502 -0.2974 -0.2541 -0.2058 -0.1956 -0.2078 0.600 -0.2045 -0.2098 -0.1907 -0.1066 -0.1347 -0.1282 -0.1403 0.700 0.0304 0.0431 0.0468 0.0410 0.0655 0.0625 0.0539 0.800 0.2082 0.2229 0.2477 0.2343 0.2397 0.2408 0.2216 0.900 0.2544 0.2861 0.3232 0.3256 0.3078 0.3076 0.2849 0.950 0.2394 0.1965 0.3205 0.3219 0.3048 0.2925 0.2754 1 TABLE NR. 2.1.1.3 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0556 -0.1167 -.484 -0.0269 -0.0926 -.406 -0.0065 -0.0776 -.327 0.0103 -0.0657 -.248 0.0307 -0.0725 -.168 0.0350 -0.0794 -.089 0.0418 -0.0671 -.010 0.0377 -0.0995 0.069 0.0231 -0.1177 0.148 0.0101 -0.1443 0.227 -0.0078 -0.1681 0.306 -0.0282 -0.1860 0.386 -0.0429 -0.2013 0.465 -0.0431 -0.2014 0.544 -0.0390 -0.1983 0.623 -0.0259 -0.1928 0.702 -0.0110 -0.1783 0.781 0.0041 -0.1632 0.860 0.0191 -0.1414 0.941 0.0253 -0.1267 1.019 0.0216 -0.1088 1.098 0.0086 -0.0960 1 TABLE NR. 2.1.1.5 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 0.0799 0.1040 0.0765 0.0260 0.0316 0.0463 0.0721 0.950 0.0128 0.0291 0.0061 -0.0287 -0.0117 -0.0012 0.0232 0.900 -0.0831 -0.0782 -0.0847 -0.1056 -0.0766 -0.1319 -0.0503 0.800 -0.2766 -0.2758 -0.2840 -0.3281 -0.2630 -0.2626 -0.2311 0.700 -0.4528 -0.4643 -0.5113 -0.5677 -0.4755 -0.4656 -0.4328 0.650 -0.5327 -0.5561 -0.6739 -0.8114 -0.6049 -0.5695 -0.5417 0.600 -0.5605 -0.5938 -0.6829 -0.7768 -0.6644 -0.6296 -0.5858 0.550 -0.5751 -0.6014 -0.6727 -0.7109 -0.6844 -0.6173 -0.5870 0.500 -0.5646 -0.5769 -0.6296 -0.6580 -0.6648 -0.5850 -0.5806 0.450 -0.5902 -0.5937 -0.6446 -0.6531 -0.6460 -0.5669 -0.5955 0.425 -0.6213 -0.6207 -0.6700 -0.6760 -0.6514 -0.5815 -0.6254 0.400 -0.6566 -0.6601 -0.6718 -0.6793 -0.7143 -0.5951 -0.6263 0.350 -0.7042 -0.7048 -0.7296 -0.7919 -0.9542 -0.8869 -0.5939 0.300 -0.7945 -0.8543 -0.8828 -1.0854 -1.0592 -1.0530 -0.5598 0.250 -0.8077 -0.8865 -0.9311 -1.0998 -1.0755 -1.0719 -0.8513 0.200 -0.8239 -0.9007 -1.1268 -1.1264 -1.1176 -1.1252 -1.0533 0.150 -0.7969 -0.8716 -1.2202 -1.1570 -1.1336 -1.1202 -1.0729 0.100 -0.8808 -1.1052 -1.2349 -1.2311 -1.2211 -1.2227 -1.1638 0.050 -1.0021 -1.2345 -1.2467 -1.1358 -1.0973 -1.0534 -1.0538 0.030 -1.1066 -1.1810 -1.0284 -0.7444 -0.7390 -0.7348 -0.6535 0.020 -0.9470 -0.9671 -0.6677 -0.5797 -0.5780 -0.5208 -0.4228 0.010 -0.2338 -0.1271 -0.1561 -0.1749 -0.0763 -0.1034 -0.0136 0.000 0.8066 0.7583 0.6940 0.7665 0.7159 0.7869 0.8066 0.010 0.6058 0.6037 0.5366 0.4530 0.4549 0.4528 0.4450 0.030 0.3048 0.2851 0.2080 0.1538 0.1775 0.2064 0.1553 0.050 0.0823 0.0581 0.0424 0.0723 0.0828 0.1110 0.0599 0.100 -0.1264 -0.1437 -0.1155 -0.0747 -0.0768 -0.0293 -0.0567 0.200 -0.2422 -0.2644 -0.2502 -0.1913 -0.1587 -0.1496 -0.1775 0.300 -0.2860 -0.3226 -0.3337 -0.3209 -0.2999 -0.2760 -0.3169 0.400 -0.3358 -0.3667 -0.3608 -0.3348 -0.2794 -0.2678 -0.2886 0.500 -0.3802 -0.3732 -0.3173 -0.2700 -0.2208 -0.2088 -0.2180 0.600 -0.2148 -0.2187 -0.1992 -0.1155 -0.1447 -0.1364 -0.1477 0.700 0.0283 0.0425 0.0466 0.0390 0.0641 0.0622 0.0519 0.800 0.2076 0.2235 0.2491 0.2320 0.2394 0.2406 0.2200 0.900 0.2554 0.2878 0.3241 0.3230 0.3100 0.3081 0.2836 0.950 0.2410 0.1959 0.3219 0.3204 0.3082 0.2923 0.2746 1 TABLE NR. 2.1.1.5 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0560 -0.1136 -.484 -0.0267 -0.0912 -.406 -0.0059 -0.0734 -.327 0.0104 -0.0607 -.248 0.0321 -0.0672 -.168 0.0370 -0.0730 -.089 0.0440 -0.0616 -.010 0.0385 -0.0940 0.069 0.0230 -0.1150 0.148 0.0084 -0.1439 0.227 -0.0124 -0.1720 0.306 -0.0352 -0.1955 0.386 -0.0497 -0.2124 0.465 -0.0526 -0.2140 0.544 -0.0457 -0.2106 0.623 -0.0326 -0.2037 0.702 -0.0142 -0.1888 0.781 0.0017 -0.1701 0.860 0.0189 -0.1471 0.941 0.0258 -0.1290 1.019 0.0222 -0.1086 1.098 0.0098 -0.0947 1 TABLE NR. 2.1.1.6 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 0.0793 0.1032 0.0722 0.0156 0.0266 0.0455 0.0740 0.950 0.0150 0.0305 0.0069 -0.0327 -0.0127 -0.0019 0.0273 0.900 -0.0794 -0.0735 -0.0789 -0.0993 -0.0705 -0.1254 -0.0456 0.800 -0.2744 -0.2699 -0.2730 -0.3065 -0.2440 -0.2488 -0.2241 0.700 -0.4588 -0.4647 -0.5105 -0.5906 -0.4507 -0.4436 -0.4255 0.650 -0.5476 -0.5713 -0.6979 -0.8273 -0.5645 -0.5411 -0.5381 0.600 -0.5756 -0.6103 -0.6914 -0.7470 -0.6172 -0.5675 -0.5855 0.550 -0.5862 -0.6042 -0.6687 -0.6792 -0.6261 -0.5316 -0.5774 0.500 -0.5791 -0.5657 -0.6135 -0.6354 -0.6825 -0.5310 -0.5501 0.450 -0.6195 -0.6157 -0.6545 -0.7560 -0.9574 -0.7101 -0.5218 0.425 -0.6849 -0.7265 -0.7068 -0.8245 -0.9818 -0.9430 -0.5409 0.400 -0.7357 -0.7794 -0.8263 -0.8356 -0.9885 -0.9738 -0.5380 0.350 -0.7163 -0.7612 -0.8594 -1.0096 -1.0195 -1.0118 -0.5948 0.300 -0.8080 -0.8671 -0.8783 -1.0676 -1.0443 -1.0398 -0.8841 0.250 -0.8014 -0.8926 -1.0465 -1.0709 -1.0473 -1.0441 -0.9579 0.200 -0.7851 -0.8772 -1.1004 -1.0946 -1.0818 -1.0884 -1.0332 0.150 -0.7805 -0.8928 -1.1832 -1.1074 -1.0892 -1.0781 -1.0390 0.100 -0.8706 -1.0748 -1.1898 -1.1840 -1.1753 -1.1757 -1.1218 0.050 -0.9678 -1.1865 -1.1955 -1.0855 -1.0472 -1.0036 -1.0122 0.030 -1.0616 -1.1317 -0.9764 -0.7036 -0.6901 -0.6790 -0.6128 0.020 -0.8986 -0.9179 -0.6272 -0.5326 -0.5252 -0.4751 -0.3790 0.010 -0.1992 -0.0957 -0.1175 -0.1435 -0.0344 -0.0588 0.0159 0.000 0.8156 0.7711 0.7042 0.7770 0.7383 0.7990 0.8194 0.010 0.6018 0.6000 0.5242 0.4390 0.4342 0.4326 0.4301 0.030 0.2975 0.2789 0.1952 0.1381 0.1609 0.1907 0.1396 0.050 0.0799 0.0501 0.0313 0.0577 0.0659 0.0963 0.0476 0.100 -0.1330 -0.1515 -0.1258 -0.0884 -0.0935 -0.0419 -0.0701 0.200 -0.2497 -0.2734 -0.2601 -0.2035 -0.1735 -0.1620 -0.1899 0.300 -0.2954 -0.3305 -0.3485 -0.3342 -0.3182 -0.2936 -0.3268 0.400 -0.3458 -0.3788 -0.3747 -0.3510 -0.2923 -0.2802 -0.2977 0.500 -0.3955 -0.3869 -0.3304 -0.2816 -0.2298 -0.2158 -0.2254 0.600 -0.2190 -0.2181 -0.2040 -0.1225 -0.1496 -0.1400 -0.1510 0.700 0.0282 0.0425 0.0464 0.0366 0.0640 0.0613 0.0526 0.800 0.2082 0.2240 0.2485 0.2311 0.2366 0.2389 0.2205 0.900 0.2571 0.2887 0.3233 0.3228 0.3062 0.3051 0.2830 0.950 0.2425 0.1960 0.3208 0.3209 0.3056 0.2925 0.2743 1 TABLE NR. 2.1.1.6 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0569 -0.1105 -.484 -0.0253 -0.0897 -.406 -0.0052 -0.0721 -.327 0.0110 -0.0596 -.248 0.0346 -0.0636 -.168 0.0385 -0.0696 -.089 0.0458 -0.0582 -.010 0.0380 -0.0912 0.069 0.0227 -0.1123 0.148 0.0078 -0.1436 0.227 -0.0143 -0.1718 0.306 -0.0384 -0.1990 0.386 -0.0548 -0.2203 0.465 -0.0570 -0.2240 0.544 -0.0514 -0.2220 0.623 -0.0355 -0.2150 0.702 -0.0175 -0.1972 0.781 0.0010 -0.1763 0.860 0.0179 -0.1517 0.941 0.0265 -0.1318 1.019 0.0220 -0.1110 1.098 0.0107 -0.0948 1 TABLE NR. 2.1.1.7 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 0.0733 0.0998 0.0680 0.0024 0.0209 0.0313 0.0770 0.950 0.0122 0.0312 0.0065 -0.0431 -0.0274 -0.0052 0.0305 0.900 -0.0757 -0.0675 -0.0717 -0.0979 -0.0725 -0.1108 -0.0407 0.800 -0.2686 -0.2622 -0.2587 -0.2879 -0.2209 -0.2163 -0.2163 0.700 -0.4586 -0.4642 -0.4902 -0.5564 -0.3902 -0.3932 -0.4125 0.650 -0.5584 -0.5913 -0.7060 -0.7435 -0.4807 -0.4626 -0.5182 0.600 -0.5820 -0.6152 -0.6823 -0.7354 -0.5464 -0.4954 -0.5419 0.550 -0.6160 -0.5957 -0.6661 -0.8798 -1.0044 -0.6080 -0.4966 0.500 -0.6319 -0.6168 -0.7475 -0.8715 -1.0310 -0.9674 -0.4783 0.450 -0.7047 -0.7680 -0.8353 -0.8515 -1.0050 -0.9865 -0.5769 0.425 -0.7591 -0.8045 -0.8859 -0.8867 -1.0108 -1.0149 -0.7159 0.400 -0.7641 -0.7888 -0.8812 -1.0291 -1.0074 -1.0230 -0.8408 0.350 -0.7421 -0.7877 -0.8641 -0.9983 -1.0124 -1.0072 -0.8872 0.300 -0.8096 -0.8725 -0.8751 -1.0553 -1.0294 -1.0204 -0.9587 0.250 -0.7981 -0.8849 -1.0499 -1.0515 -1.0201 -1.0222 -0.9518 0.200 -0.7838 -0.8762 -1.0843 -1.0750 -1.0516 -1.0617 -1.0109 0.150 -0.7605 -0.9262 -1.1554 -1.0799 -1.0536 -1.0407 -1.0036 0.100 -0.8774 -1.0633 -1.1594 -1.1469 -1.1360 -1.1348 -1.0859 0.050 -0.9411 -1.1521 -1.1578 -1.0472 -1.0093 -0.9625 -0.9709 0.030 -1.0270 -1.0936 -0.9395 -0.6626 -0.6468 -0.6303 -0.5748 0.020 -0.8629 -0.8758 -0.5824 -0.4930 -0.4862 -0.4278 -0.3364 0.010 -0.1762 -0.0735 -0.0920 -0.1057 0.0029 -0.0250 0.0509 0.000 0.8287 0.7825 0.7329 0.7876 0.7516 0.8160 0.8366 0.010 0.6040 0.5970 0.5204 0.4307 0.4180 0.4180 0.4167 0.030 0.3016 0.2784 0.1902 0.1284 0.1464 0.1747 0.1217 0.050 0.0764 0.0498 0.0264 0.0478 0.0543 0.0827 0.0309 0.100 -0.1352 -0.1539 -0.1317 -0.0971 -0.1036 -0.0550 -0.0836 0.200 -0.2546 -0.2817 -0.2717 -0.2142 -0.1839 -0.1716 -0.2103 0.300 -0.3015 -0.3330 -0.3688 -0.3529 -0.3414 -0.3094 -0.3443 0.400 -0.3546 -0.3887 -0.3894 -0.3651 -0.2994 -0.2968 -0.3078 0.500 -0.4068 -0.3974 -0.3389 -0.2909 -0.2407 -0.2277 -0.2325 0.600 -0.2255 -0.2241 -0.2108 -0.1275 -0.1576 -0.1446 -0.1544 0.700 0.0298 0.0474 0.0460 0.0360 0.0624 0.0598 0.0534 0.800 0.2110 0.2258 0.2459 0.2290 0.2333 0.2381 0.2221 0.900 0.2578 0.2902 0.3211 0.3217 0.3054 0.3046 0.2849 0.950 0.2427 0.1950 0.3179 0.3195 0.3042 0.2934 0.2768 1 TABLE NR. 2.1.1.7 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0569 -0.1107 -.484 -0.0258 -0.0874 -.406 -0.0034 -0.0703 -.327 0.0131 -0.0566 -.248 0.0350 -0.0608 -.168 0.0402 -0.0660 -.089 0.0481 -0.0553 -.010 0.0402 -0.0884 0.069 0.0240 -0.1104 0.148 0.0076 -0.1430 0.227 -0.0164 -0.1730 0.306 -0.0411 -0.2038 0.386 -0.0597 -0.2295 0.465 -0.0622 -0.2358 0.544 -0.0558 -0.2346 0.623 -0.0390 -0.2248 0.702 -0.0198 -0.2051 0.781 -0.0001 -0.1825 0.860 0.0168 -0.1540 0.941 0.0253 -0.1330 1.019 0.0225 -0.1113 1.098 0.0109 -0.0948 1 TABLE NR. 2.1.1.8 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 0.0641 0.0916 0.0563 -0.0236 -0.0475 -0.0174 0.0733 0.950 0.0058 0.0299 -0.0001 -0.0768 -0.0844 -0.0491 0.0318 0.900 -0.0699 -0.0628 -0.0697 -0.1240 -0.1246 -0.1156 -0.0319 0.800 -0.2562 -0.2485 -0.2418 -0.2714 -0.2153 -0.1820 -0.1939 0.700 -0.4508 -0.4455 -0.4544 -0.4653 -0.3511 -0.3157 -0.3765 0.650 -0.5491 -0.5665 -0.6557 -0.7887 -0.4397 -0.3820 -0.4569 0.600 -0.6292 -0.6553 -0.7773 -0.9582 -0.5964 -0.4769 -0.4488 0.550 -0.6998 -0.6772 -0.8063 -0.9164 -1.0444 -0.7690 -0.4585 0.500 -0.6691 -0.7332 -0.8395 -0.8856 -1.0256 -0.9722 -0.6869 0.450 -0.7621 -0.8130 -0.8681 -1.0107 -1.0169 -1.0179 -0.9204 0.425 -0.7817 -0.8183 -0.8974 -1.0393 -1.0306 -1.0298 -0.9218 0.400 -0.7813 -0.8211 -0.9047 -1.0317 -1.0167 -1.0208 -0.9131 0.350 -0.7536 -0.8027 -0.8617 -1.0276 -1.0123 -0.9947 -0.9404 0.300 -0.8094 -0.8813 -0.9652 -1.0442 -1.0155 -1.0052 -0.9523 0.250 -0.8003 -0.8839 -1.0284 -1.0367 -1.0030 -1.0000 -0.9406 0.200 -0.7820 -0.8711 -1.0710 -1.0557 -1.0256 -1.0348 -0.9871 0.150 -0.7656 -0.9830 -1.1341 -1.0545 -1.0256 -1.0079 -0.9814 0.100 -0.8795 -1.0770 -1.1296 -1.1140 -1.0995 -1.0975 -1.0521 0.050 -0.9293 -1.1232 -1.1240 -1.0103 -0.9690 -0.9260 -0.9305 0.030 -1.0023 -1.0641 -0.9068 -0.6333 -0.6200 -0.5964 -0.5423 0.020 -0.8370 -0.8514 -0.5599 -0.4662 -0.4553 -0.4053 -0.3080 0.010 -0.1571 -0.0576 -0.0720 -0.0829 0.0184 -0.0001 0.0762 0.000 0.8363 0.7862 0.7298 0.7931 0.7668 0.8140 0.8424 0.010 0.6095 0.6023 0.5195 0.4243 0.4148 0.4051 0.4059 0.030 0.3055 0.2829 0.1909 0.1242 0.1386 0.1663 0.1138 0.050 0.0846 0.0519 0.0261 0.0452 0.0482 0.0724 0.0279 0.100 -0.1313 -0.1531 -0.1328 -0.1018 -0.1097 -0.0656 -0.0936 0.200 -0.2568 -0.2806 -0.2744 -0.2191 -0.1946 -0.1789 -0.2207 0.300 -0.3047 -0.3378 -0.3812 -0.3679 -0.3558 -0.3290 -0.3613 0.400 -0.3639 -0.4043 -0.4057 -0.3851 -0.3264 -0.3167 -0.3304 0.500 -0.4246 -0.4140 -0.3557 -0.3067 -0.2549 -0.2521 -0.2405 0.600 -0.2304 -0.2301 -0.2159 -0.1377 -0.1694 -0.1663 -0.1600 0.700 0.0270 0.0451 0.0441 0.0313 0.0520 0.0442 0.0498 0.800 0.2091 0.2231 0.2434 0.2238 0.2226 0.2245 0.2194 0.900 0.2575 0.2892 0.3184 0.3162 0.2913 0.2895 0.2829 0.950 0.2407 0.1904 0.3149 0.3125 0.2881 0.2734 0.2740 1 TABLE NR. 2.1.1.8 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0550 -0.1103 -.484 -0.0243 -0.0851 -.406 -0.0024 -0.0672 -.327 0.0159 -0.0529 -.248 0.0385 -0.0570 -.168 0.0431 -0.0628 -.089 0.0512 -0.0507 -.010 0.0431 -0.0844 0.069 0.0260 -0.1075 0.148 0.0078 -0.1408 0.227 -0.0160 -0.1738 0.306 -0.0435 -0.2087 0.386 -0.0628 -0.2377 0.465 -0.0667 -0.2491 0.544 -0.0594 -0.2506 0.623 -0.0426 -0.2389 0.702 -0.0218 -0.2166 0.781 -0.0013 -0.1891 0.860 0.0166 -0.1593 0.941 0.0263 -0.1352 1.019 0.0224 -0.1115 1.098 0.0112 -0.0941 1 TABLE NR. 2.1.1.9 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 0.0475 0.0778 0.0368 -0.0765 -0.1539 -0.1040 0.0581 0.950 -0.0056 0.0214 -0.0247 -0.1679 -0.2119 -0.1414 0.0210 0.900 -0.0718 -0.0596 -0.0895 -0.2116 -0.2394 -0.1772 -0.0269 0.800 -0.2389 -0.2267 -0.2355 -0.3200 -0.2832 -0.2130 -0.1638 0.700 -0.4239 -0.4079 -0.4270 -0.4458 -0.3469 -0.2834 -0.3223 0.650 -0.6113 -0.6592 -0.7737 -0.6240 -0.3890 -0.3310 -0.3851 0.600 -0.7491 -0.7460 -0.8752 -0.9719 -0.4420 -0.3929 -0.4254 0.550 -0.7296 -0.7636 -0.8810 -0.9801 -0.5836 -0.4767 -0.5535 0.500 -0.7262 -0.7973 -0.8819 -1.0595 -1.0097 -0.7291 -0.8552 0.450 -0.7905 -0.8307 -0.9106 -1.0463 -1.0529 -1.0392 -0.9723 0.425 -0.8068 -0.8485 -0.9286 -1.0537 -1.0541 -1.0426 -0.9877 0.400 -0.7972 -0.8424 -0.9112 -1.0543 -1.0369 -1.0287 -0.9815 0.350 -0.7661 -0.8279 -0.8657 -1.0569 -1.0236 -1.0071 -0.9625 0.300 -0.8138 -0.8916 -1.0594 -1.0551 -1.0220 -1.0114 -0.9585 0.250 -0.8154 -0.8922 -1.0735 -1.0402 -1.0091 -0.9997 -0.9474 0.200 -0.7934 -0.8802 -1.0830 -1.0532 -1.0262 -1.0258 -0.9802 0.150 -0.7779 -1.0162 -1.1353 -1.0468 -1.0163 -0.9964 -0.9706 0.100 -0.9119 -1.1127 -1.1246 -1.0984 -1.0857 -1.0789 -1.0352 0.050 -0.9578 -1.1193 -1.1142 -0.9943 -0.9507 -0.9066 -0.9098 0.030 -1.0082 -1.0538 -0.8935 -0.6208 -0.6073 -0.5835 -0.5233 0.020 -0.8470 -0.8498 -0.5569 -0.4627 -0.4461 -0.3895 -0.2985 0.010 -0.1648 -0.0537 -0.0689 -0.0819 0.0202 0.0085 0.0883 0.000 0.8298 0.7818 0.7230 0.7918 0.7629 0.8218 0.8306 0.010 0.6267 0.6168 0.5340 0.4396 0.4255 0.4130 0.4118 0.030 0.3289 0.3037 0.2083 0.1422 0.1507 0.1713 0.1194 0.050 0.1071 0.0746 0.0445 0.0604 0.0592 0.0778 0.0298 0.100 -0.1101 -0.1346 -0.1182 -0.0905 -0.1018 -0.0655 -0.0924 0.200 -0.2396 -0.2672 -0.2630 -0.2120 -0.1949 -0.1878 -0.2157 0.300 -0.2909 -0.3348 -0.3799 -0.3723 -0.3689 -0.3493 -0.3844 0.400 -0.3677 -0.4095 -0.4133 -0.3939 -0.3403 -0.3420 -0.3483 0.500 -0.4403 -0.4286 -0.3667 -0.3220 -0.2747 -0.2804 -0.2607 0.600 -0.2356 -0.2374 -0.2223 -0.1498 -0.1939 -0.2014 -0.1735 0.700 0.0251 0.0433 0.0391 0.0224 0.0280 0.0125 0.0410 0.800 0.2073 0.2212 0.2380 0.2130 0.1974 0.1989 0.2114 0.900 0.2560 0.2868 0.3142 0.3046 0.2623 0.2631 0.2764 0.950 0.2373 0.1823 0.3096 0.2982 0.2510 0.2430 0.2697 1 TABLE NR. 2.1.1.9 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0535 -0.1073 -.484 -0.0222 -0.0820 -.406 0.0006 -0.0639 -.327 0.0199 -0.0498 -.248 0.0433 -0.0534 -.168 0.0487 -0.0591 -.089 0.0555 -0.0475 -.010 0.0499 -0.0815 0.069 0.0322 -0.1074 0.148 0.0136 -0.1424 0.227 -0.0120 -0.1789 0.306 -0.0405 -0.2186 0.386 -0.0622 -0.2533 0.465 -0.0676 -0.2702 0.544 -0.0605 -0.2758 0.623 -0.0448 -0.2637 0.702 -0.0225 -0.2350 0.781 -0.0016 -0.2020 0.860 0.0168 -0.1652 0.941 0.0265 -0.1386 1.019 0.0234 -0.1127 1.098 0.0121 -0.0943 1 TABLE NR. 2.1.1.10 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 0.0322 0.0540 -0.0021 -0.1498 -0.2232 -0.1580 0.0260 0.950 -0.0244 0.0019 -0.0730 -0.2519 -0.2796 -0.1953 -0.0032 0.900 -0.0824 -0.0655 -0.1304 -0.2883 -0.2872 -0.2239 -0.0489 0.800 -0.2267 -0.2157 -0.2598 -0.3837 -0.3149 -0.2524 -0.1480 0.700 -0.4314 -0.4145 -0.4335 -0.4740 -0.3548 -0.3017 -0.2830 0.650 -0.7260 -0.7861 -0.7773 -0.5393 -0.3799 -0.3357 -0.3519 0.600 -0.7961 -0.7799 -0.9158 -0.8565 -0.4085 -0.3727 -0.4256 0.550 -0.7473 -0.8246 -0.9044 -1.0889 -0.4457 -0.4251 -0.5760 0.500 -0.7701 -0.8187 -0.9017 -1.0599 -0.6225 -0.5235 -0.9487 0.450 -0.8044 -0.8440 -0.9239 -1.0612 -1.0480 -0.8576 -0.9818 0.425 -0.8148 -0.8609 -0.9245 -1.0601 -1.0494 -1.0071 -0.9934 0.400 -0.7937 -0.8557 -0.9022 -1.0624 -1.0340 -1.0174 -0.9794 0.350 -0.7750 -0.8381 -1.0104 -1.0540 -1.0161 -0.9991 -0.9578 0.300 -0.8257 -0.9028 -1.0463 -1.0513 -1.0159 -1.0077 -0.9525 0.250 -0.8128 -0.8935 -1.0833 -1.0314 -0.9993 -0.9880 -0.9338 0.200 -0.7989 -0.8794 -1.0780 -1.0420 -1.0120 -1.0104 -0.9611 0.150 -0.7799 -0.9982 -1.1230 -1.0310 -0.9966 -0.9776 -0.9480 0.100 -0.9184 -1.1076 -1.1076 -1.0776 -1.0598 -1.0547 -1.0049 0.050 -0.9737 -1.1036 -1.0906 -0.9670 -0.9228 -0.8786 -0.8805 0.030 -0.9934 -1.0345 -0.8746 -0.6001 -0.5860 -0.5670 -0.5064 0.020 -0.8360 -0.8336 -0.5418 -0.4536 -0.4331 -0.3697 -0.2724 0.010 -0.1487 -0.0422 -0.0638 -0.0748 0.0380 0.0190 0.0948 0.000 0.8335 0.7863 0.7280 0.7922 0.7589 0.8201 0.8520 0.010 0.6410 0.6259 0.5449 0.4451 0.4257 0.4103 0.4049 0.030 0.3450 0.3174 0.2205 0.1481 0.1530 0.1693 0.1111 0.050 0.1255 0.0870 0.0541 0.0663 0.0590 0.0760 0.0210 0.100 -0.0992 -0.1226 -0.1092 -0.0855 -0.1038 -0.0675 -0.1021 0.200 -0.2340 -0.2619 -0.2597 -0.2116 -0.1997 -0.1957 -0.2354 0.300 -0.2957 -0.3299 -0.3841 -0.3844 -0.3929 -0.3693 -0.3996 0.400 -0.3774 -0.4216 -0.4426 -0.4216 -0.3650 -0.3721 -0.3771 0.500 -0.4669 -0.4647 -0.3933 -0.3441 -0.3049 -0.3087 -0.2863 0.600 -0.2444 -0.2477 -0.2341 -0.1671 -0.2224 -0.2276 -0.1936 0.700 0.0219 0.0389 0.0319 0.0100 0.0051 -0.0047 0.0262 0.800 0.2047 0.2184 0.2315 0.2008 0.1776 0.1822 0.1977 0.900 0.2533 0.2846 0.3061 0.2891 0.2414 0.2467 0.2663 0.950 0.2327 0.1693 0.2983 0.2776 0.2265 0.2242 0.2559 1 TABLE NR. 2.1.1.10 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0521 -0.1060 -.484 -0.0201 -0.0793 -.406 0.0033 -0.0601 -.327 0.0231 -0.0453 -.248 0.0454 -0.0486 -.168 0.0529 -0.0541 -.089 0.0605 -0.0426 -.010 0.0532 -0.0774 0.069 0.0366 -0.1041 0.148 0.0180 -0.1400 0.227 -0.0096 -0.1784 0.306 -0.0424 -0.2220 0.386 -0.0656 -0.2616 0.465 -0.0728 -0.2860 0.544 -0.0670 -0.2973 0.623 -0.0503 -0.2882 0.702 -0.0268 -0.2537 0.781 -0.0044 -0.2130 0.860 0.0146 -0.1713 0.941 0.0242 -0.1409 1.019 0.0223 -0.1134 1.098 0.0117 -0.0940 1 TABLE NR. 3.1.1.1 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 0.1107 0.1199 0.0952 0.0506 0.0581 0.0668 0.0937 0.950 0.0163 0.0278 0.0050 -0.0207 -0.0055 0.0023 0.0251 0.900 -0.0977 -0.0909 -0.1000 -0.1192 -0.0911 -0.1416 -0.0641 0.800 -0.2879 -0.2826 -0.3012 -0.3590 -0.2940 -0.2856 -0.2502 0.700 -0.4320 -0.4440 -0.4978 -0.5652 -0.4952 -0.4709 -0.4303 0.650 -0.4857 -0.5079 -0.5951 -0.6909 -0.6025 -0.5589 -0.5204 0.600 -0.4989 -0.5260 -0.6063 -0.6863 -0.6256 -0.5998 -0.5327 0.550 -0.5031 -0.5281 -0.5983 -0.6584 -0.6273 -0.5818 -0.5203 0.500 -0.4930 -0.5114 -0.5679 -0.6227 -0.6108 -0.5637 -0.5087 0.450 -0.4999 -0.5216 -0.5650 -0.5971 -0.6102 -0.5636 -0.5083 0.425 -0.5216 -0.5500 -0.5949 -0.6122 -0.6304 -0.5743 -0.5236 0.400 -0.5352 -0.5697 -0.6195 -0.6422 -0.6314 -0.5923 -0.5348 0.350 -0.5422 -0.5638 -0.6025 -0.6282 -0.6195 -0.5779 -0.5300 0.300 -0.5530 -0.5795 -0.6107 -0.6372 -0.6338 -0.5893 -0.5290 0.250 -0.5929 -0.6384 -0.6517 -0.6466 -0.6006 -0.5972 -0.5243 0.200 -0.6084 -0.6624 -0.6573 -0.6273 -0.6050 -0.5668 -0.5141 0.150 -0.6101 -0.6873 -0.6667 -0.6830 -0.6659 -0.5973 -0.5394 0.100 -0.6251 -0.7293 -0.7924 -0.7079 -0.6791 -0.6466 -0.5463 0.050 -0.6817 -0.8250 -1.0147 -0.8958 -0.8198 -0.7769 -0.6063 0.030 -0.7417 -0.8619 -0.7696 -0.5325 -0.4944 -0.4430 -0.3372 0.020 -0.6153 -0.6671 -0.4683 -0.3217 -0.2978 -0.2339 -0.0926 0.010 -0.0524 0.0268 0.0186 0.0573 0.1699 0.1633 0.2770 0.000 0.8574 0.8179 0.7735 0.8341 0.8231 0.8614 0.8717 0.010 0.4631 0.4679 0.3713 0.2256 0.2044 0.1689 0.1371 0.030 0.1220 0.1037 0.0091 -0.0733 -0.0635 -0.0465 -0.1428 0.050 -0.0964 -0.1277 -0.1544 -0.1316 -0.1295 -0.1112 -0.2054 0.100 -0.2766 -0.3043 -0.2795 -0.2463 -0.2545 -0.2091 -0.2612 0.200 -0.3560 -0.3885 -0.3790 -0.3246 -0.2932 -0.2921 -0.3284 0.300 -0.3703 -0.4118 -0.4330 -0.4370 -0.4203 -0.3963 -0.4469 0.400 -0.4024 -0.4380 -0.4393 -0.4232 -0.3677 -0.3563 -0.3709 0.500 -0.4285 -0.4241 -0.3699 -0.3325 -0.2809 -0.2696 -0.2743 0.600 -0.2435 -0.2499 -0.2359 -0.1600 -0.1841 -0.1738 -0.1790 0.700 0.0070 0.0203 0.0228 0.0125 0.0406 0.0392 0.0360 0.800 0.1896 0.2051 0.2288 0.2101 0.2171 0.2183 0.2031 0.900 0.2430 0.2752 0.3092 0.3061 0.2916 0.2877 0.2685 0.950 0.2354 0.1976 0.3101 0.3103 0.2923 0.2821 0.2665 1 TABLE NR. 3.1.1.1 RE=3*10E6 CL=0.30 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0678 -0.1070 -.484 -0.0415 -0.0819 -.406 -0.0207 -0.0645 -.327 -0.0059 -0.0516 -.248 0.0105 -0.0550 -.168 0.0118 -0.0574 -.089 0.0140 -0.0406 -.010 0.0035 -0.0654 0.069 -0.0148 -0.0781 0.148 -0.0328 -0.0978 0.227 -0.0556 -0.1169 0.306 -0.0757 -0.1323 0.386 -0.0876 -0.1486 0.465 -0.0867 -0.1516 0.544 -0.0766 -0.1532 0.623 -0.0583 -0.1536 0.702 -0.0381 -0.1454 0.781 -0.0177 -0.1338 0.860 0.0001 -0.1182 0.941 0.0093 -0.1061 1.019 0.0069 -0.0923 1.098 -0.0032 -0.0813 1 TABLE NR. 3.1.1.2 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 0.0985 0.1115 0.0851 0.0348 0.0424 0.0516 0.0821 0.950 0.0153 0.0266 0.0026 -0.0267 -0.0111 -0.0030 0.0221 0.900 -0.0938 -0.0878 -0.0987 -0.1158 -0.0880 -0.1422 -0.0616 0.800 -0.2853 -0.2830 -0.3020 -0.3554 -0.2891 -0.2813 -0.2485 0.700 -0.4393 -0.4528 -0.5083 -0.5758 -0.5005 -0.4789 -0.4389 0.650 -0.5019 -0.5256 -0.6166 -0.7198 -0.6140 -0.5780 -0.5332 0.600 -0.5198 -0.5495 -0.6355 -0.7303 -0.6512 -0.6220 -0.5617 0.550 -0.5315 -0.5562 -0.6343 -0.6973 -0.6565 -0.6201 -0.5541 0.500 -0.5259 -0.5445 -0.6050 -0.6621 -0.6636 -0.6048 -0.5424 0.450 -0.5394 -0.5616 -0.6134 -0.6492 -0.6736 -0.6204 -0.5519 0.425 -0.5641 -0.5944 -0.6488 -0.6779 -0.6933 -0.6378 -0.5765 0.400 -0.5815 -0.6203 -0.6828 -0.7226 -0.6987 -0.6665 -0.5919 0.350 -0.5947 -0.6125 -0.6625 -0.7021 -0.6951 -0.6443 -0.6065 0.300 -0.6155 -0.6333 -0.6687 -0.7120 -0.7060 -0.6747 -0.6147 0.250 -0.6720 -0.7097 -0.7457 -0.7256 -0.6989 -0.7035 -0.6137 0.200 -0.7041 -0.7603 -0.6878 -0.6668 -0.6685 -0.6535 -0.6007 0.150 -0.7032 -0.7830 -0.9375 -0.8525 -0.8443 -0.6616 -0.6608 0.100 -0.7289 -0.9984 -1.0955 -1.0598 -0.9838 -0.9911 -0.7714 0.050 -0.8581 -1.0345 -1.1973 -1.1088 -1.0577 -1.0019 -0.8950 0.030 -0.9885 -1.1406 -0.9877 -0.6998 -0.6792 -0.6462 -0.5596 0.020 -0.8160 -0.8658 -0.6282 -0.5090 -0.4983 -0.4379 -0.3068 0.010 -0.1876 -0.0926 -0.1101 -0.1135 -0.0035 -0.0167 0.0985 0.000 0.8220 0.7808 0.7224 0.7889 0.7635 0.8204 0.8374 0.010 0.5425 0.5457 0.4710 0.3728 0.3635 0.3463 0.3269 0.030 0.2231 0.2085 0.1282 0.0699 0.0845 0.1126 0.0272 0.050 0.0034 -0.0210 -0.0369 -0.0056 0.0010 0.0241 -0.0504 0.100 -0.1942 -0.2109 -0.1815 -0.1422 -0.1459 -0.0984 -0.1409 0.200 -0.2908 -0.3150 -0.2994 -0.2416 -0.2112 -0.2043 -0.2374 0.300 -0.3187 -0.3526 -0.3647 -0.3556 -0.3404 -0.3196 -0.3668 0.400 -0.3618 -0.3869 -0.3842 -0.3624 -0.3097 -0.2988 -0.3203 0.500 -0.3921 -0.3853 -0.3330 -0.2926 -0.2413 -0.2331 -0.2397 0.600 -0.2235 -0.2296 -0.2137 -0.1337 -0.1602 -0.1519 -0.1600 0.700 0.0182 0.0318 0.0349 0.0251 0.0532 0.0498 0.0421 0.800 0.1987 0.2139 0.2388 0.2221 0.2298 0.2305 0.2116 0.900 0.2488 0.2796 0.3158 0.3159 0.3010 0.2970 0.2778 0.950 0.2374 0.1956 0.3164 0.3170 0.2973 0.2894 0.2695 1 TABLE NR. 3.1.1.2 RE=3*10E6 CL=0.40 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0630 -0.1124 -.484 -0.0346 -0.0887 -.406 -0.0142 -0.0714 -.327 0.0022 -0.0590 -.248 0.0205 -0.0643 -.168 0.0230 -0.0678 -.089 0.0275 -0.0534 -.010 0.0208 -0.0821 0.069 0.0043 -0.0974 0.148 -0.0100 -0.1201 0.227 -0.0321 -0.1412 0.306 -0.0506 -0.1583 0.386 -0.0648 -0.1727 0.465 -0.0651 -0.1760 0.544 -0.0565 -0.1756 0.623 -0.0423 -0.1723 0.702 -0.0249 -0.1628 0.781 -0.0069 -0.1486 0.860 0.0088 -0.1299 0.941 0.0169 -0.1168 1.019 0.0139 -0.1010 1.098 0.0025 -0.0891 1 TABLE NR. 3.1.1.3 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 0.0805 0.1019 0.0851 0.0372 0.0430 0.0531 0.0722 0.950 0.0126 0.0259 0.0013 -0.0282 -0.0109 -0.0035 0.0181 0.900 -0.0854 -0.0834 -0.0978 -0.1174 -0.0874 -0.1397 -0.0614 0.800 -0.2820 -0.2801 -0.2986 -0.3514 -0.2818 -0.2758 -0.2440 0.700 -0.4498 -0.4603 -0.5083 -0.5688 -0.4852 -0.4641 -0.4373 0.650 -0.5215 -0.5401 -0.6182 -0.6940 -0.5893 -0.5475 -0.5336 0.600 -0.5513 -0.5781 -0.6503 -0.7132 -0.6144 -0.5937 -0.5650 0.550 -0.5747 -0.5965 -0.6570 -0.6879 -0.6174 -0.5671 -0.5608 0.500 -0.5790 -0.5893 -0.6311 -0.6497 -0.5999 -0.5545 -0.5465 0.450 -0.6039 -0.6120 -0.6372 -0.6310 -0.6133 -0.5520 -0.5429 0.425 -0.6377 -0.6474 -0.6630 -0.6434 -0.6419 -0.5803 -0.5499 0.400 -0.6624 -0.6743 -0.6855 -0.6800 -0.7058 -0.6783 -0.5424 0.350 -0.7143 -0.6871 -0.6701 -1.0548 -1.2197 -1.0006 -0.5426 0.300 -0.8448 -0.8662 -0.8209 -1.2983 -1.2752 -1.2719 -0.8019 0.250 -0.8910 -0.9771 -1.3134 -1.3017 -1.2833 -1.2814 -1.2114 0.200 -0.8985 -0.9945 -1.3486 -1.3272 -1.3186 -1.3250 -1.2770 0.150 -0.9084 -1.1504 -1.4302 -1.3559 -1.3345 -1.3267 -1.2877 0.100 -1.0690 -1.4152 -1.4422 -1.4250 -1.4173 -1.4160 -1.3714 0.050 -1.2813 -1.4431 -1.4461 -1.3023 -1.2611 -1.2457 -1.2555 0.030 -1.3332 -1.3894 -1.1968 -0.9666 -0.9808 -0.9653 -0.8626 0.020 -1.1672 -1.1736 -0.8472 -0.8009 -0.8069 -0.7667 -0.6383 0.010 -0.3817 -0.2664 -0.3023 -0.3684 -0.2688 -0.2956 -0.2221 0.000 0.7492 0.6929 0.6167 0.6862 0.6063 0.6897 0.7256 0.010 0.6627 0.6632 0.6052 0.5620 0.5663 0.5708 0.5655 0.030 0.3831 0.3701 0.3071 0.2679 0.2936 0.3280 0.2774 0.050 0.1668 0.1454 0.1406 0.1755 0.1903 0.2189 0.1737 0.100 -0.0490 -0.0604 -0.0276 0.0198 0.0224 0.0631 0.0385 0.200 -0.1814 -0.1950 -0.1737 -0.1103 -0.0758 -0.0670 -0.1014 0.300 -0.2308 -0.2558 -0.2589 -0.2348 -0.2153 -0.1977 -0.2358 0.400 -0.2772 -0.3052 -0.2875 -0.2621 -0.2136 -0.1993 -0.2211 0.500 -0.3302 -0.3181 -0.2633 -0.2156 -0.1695 -0.1594 -0.1723 0.600 -0.1852 -0.1883 -0.1691 -0.0787 -0.1088 -0.1002 -0.1173 0.700 0.0417 0.0558 0.0620 0.0582 0.0818 0.0796 0.0656 0.800 0.2178 0.2342 0.2610 0.2490 0.2539 0.2550 0.2324 0.900 0.2614 0.2942 0.3329 0.3360 0.3223 0.3206 0.2948 0.950 0.2444 0.1981 0.3300 0.3310 0.3179 0.3075 0.2816 1 TABLE NR. 3.1.1.3 RE=3*10E6 CL=0.60 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0502 -0.1188 -.484 -0.0212 -0.0971 -.406 0.0003 -0.0820 -.327 0.0180 -0.0718 -.248 0.0405 -0.0800 -.168 0.0449 -0.0883 -.089 0.0552 -0.0796 -.010 0.0514 -0.1141 0.069 0.0394 -0.1369 0.148 0.0288 -0.1670 0.227 0.0117 -0.1940 0.306 -0.0081 -0.2131 0.386 -0.0234 -0.2276 0.465 -0.0254 -0.2268 0.544 -0.0210 -0.2212 0.623 -0.0107 -0.2120 0.702 0.0015 -0.1945 0.781 0.0146 -0.1745 0.860 0.0275 -0.1518 0.941 0.0341 -0.1340 1.019 0.0279 -0.1151 1.098 0.0139 -0.1014