TABLE NR. 2.3.1.1 RE=3*10E6 CL=0.52 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 0.1111 0.1021 0.0753 0.0316 0.0417 0.0430 0.0635 0.950 -0.0056 -0.0052 -0.0228 -0.0538 -0.0295 -0.0301 -0.0075 0.900 -0.1204 -0.1172 -0.1284 -0.1576 -0.1213 -0.1249 -0.0919 0.800 -0.2842 -0.2870 -0.3097 -0.3707 -0.3187 -0.3093 -0.2698 0.700 -0.4016 -0.4189 -0.4699 -0.5361 -0.4866 -0.4685 -0.4285 0.650 -0.4411 -0.4669 -0.5428 -0.6014 -0.5610 -0.5405 -0.5082 0.600 -0.4784 -0.4960 -0.5619 -0.6220 -0.5853 -0.5715 -0.5319 0.550 -0.4926 -0.5186 -0.5661 -0.6251 -0.5940 100.0000 -0.5215 0.500 -0.5017 -0.5222 -0.5820 -0.6335 -0.6107 -0.5786 -0.5364 0.450 -0.5278 -0.5538 -0.5976 -0.6220 -0.6369 -0.6132 -0.5435 0.425 -0.5485 -0.5745 -0.6156 -0.6601 -0.6574 100.0000 -0.5638 0.400 -0.5765 -0.6006 -0.6021 -0.6839 -0.6714 -0.6307 100.0000 0.350 -0.5994 -0.6134 -0.6645 -0.6889 -0.6736 -0.6440 -0.6148 0.300 -0.6313 -0.6613 -0.7086 -0.6833 -0.7114 -0.6821 -0.6307 0.250 -0.6832 -0.7356 -0.7684 -0.7697 -0.7348 100.0009 -0.6579 0.200 -0.7475 -0.7957 -0.8205 -0.8105 -0.7907 -0.7609 100.0000 0.150 -0.8128 -0.8765 -0.9029 100.0000 -0.6225 100.0000 -0.6738 0.100 -0.9257 -0.9917 -0.9864 -0.9605 -0.9839 -0.9137 -0.8680 0.050 -1.3890 -1.4265 -1.6930 -1.5680 -1.5289 -1.4826 -1.2058 0.030 -1.5465 -1.8441 -1.8516 -1.5602 -1.4638 -1.3754 -1.1640 0.020 -1.5710 -1.6195 -1.4153 -1.3216 -1.2688 -1.1779 -1.0459 0.010 -0.8642 -0.6956 -0.8330 -0.9058 -0.7543 -0.6544 -0.6030 0.000 0.6354 0.5723 0.4497 0.5907 0.4110 0.6068 0.6870 0.010 0.6606 0.6725 0.6631 0.6415 0.6298 0.6347 0.6086 0.030 0.3840 0.3890 0.3593 0.3336 0.3553 0.3618 0.3495 0.050 0.1670 0.1661 0.1908 0.2517 0.2410 0.2419 0.2030 0.100 -0.0405 -0.0412 0.0134 0.0702 0.0679 0.1006 0.0568 0.200 -0.1554 -0.1562 -0.1185 -0.0694 -0.0437 -0.0207 -0.0531 0.300 -0.2064 -0.2173 -0.1877 -0.1698 -0.1365 -0.1348 100.0000 0.400 -0.2390 -0.2526 -0.2279 -0.2068 -0.1621 -0.1552 -0.1869 0.500 -0.2602 -0.2447 -0.2166 -0.1775 100.0000 -0.1317 -0.1476 0.600 -0.1691 -0.1706 -0.1459 -0.1408 -0.0922 -0.0896 -0.1040 0.700 0.0292 0.0437 0.0452 0.0426 0.0617 0.0591 0.0501 0.800 0.1956 0.2079 0.2343 0.2248 0.2307 0.2391 0.2125 0.900 0.2366 0.2610 0.2970 0.3114 0.3001 0.3006 0.2736 0.950 0.2292 0.2569 0.2918 0.3056 0.2757 0.2871 0.2561 1 TABLE NR. 2.3.1.1 RE=3*10E6 CL=0.52 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0332 -0.1057 -.485 -0.0163 -0.1043 -.406 0.0015 -0.0777 -.327 0.0113 -0.0903 -.248 0.0432 -0.0891 -.168 0.0477 -0.1033 -.089 0.0468 -0.0886 -.010 0.0390 -0.1001 0.069 0.0405 -0.1276 0.148 0.0224 -0.1283 0.227 0.0097 -0.1403 0.306 -0.0140 -0.1490 0.386 -0.0062 -0.1625 0.465 -0.0034 -0.1558 0.544 0.0072 -0.1463 0.623 0.0044 -0.1490 0.702 0.0077 -0.1413 0.781 0.0025 -0.1286 0.860 0.0268 -0.1177 0.940 0.0147 -0.1047 1.019 0.0085 -0.0985 1.098 0.0027 -0.0811 1 TABLE NR. 2.3.1.2 RE=3*10E6 CL=0.52 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 0.1127 0.1070 0.0863 0.0308 0.0372 0.0391 0.0549 0.950 0.0057 0.0125 -0.0078 -0.0376 -0.0176 -0.0221 0.0087 0.900 -0.1127 -0.1030 -0.1145 -0.1384 -0.0997 -0.1047 -0.0644 0.800 -0.2888 -0.2911 -0.3116 -0.3689 -0.3028 -0.2953 -0.2435 0.700 -0.4250 -0.4476 -0.5014 -0.5718 -0.5023 -0.4834 -0.4321 0.650 -0.4744 -0.5075 -0.5915 -0.6597 -0.5977 -0.5700 -0.5241 0.600 -0.5166 -0.5395 -0.6138 -0.6882 -0.6362 -0.6149 -0.5591 0.550 -0.5318 -0.5585 -0.6138 -0.6856 -0.6481 100.0000 -0.5519 0.500 -0.5389 -0.5569 -0.6224 -0.6838 -0.6632 -0.6276 -0.5715 0.450 -0.5647 -0.5874 -0.6348 -0.6658 -0.6908 -0.6642 -0.5809 0.425 -0.5893 -0.6141 -0.6554 -0.7129 -0.7169 100.0000 -0.6062 0.400 -0.6173 -0.6446 -0.6340 -0.7367 -0.7323 -0.6842 100.0000 0.350 -0.6351 -0.6448 -0.6952 -0.7255 -0.7234 -0.6925 -0.6614 0.300 -0.6725 -0.6878 -0.7250 -0.6903 -0.7528 -0.7282 -0.6798 0.250 -0.7301 -0.7740 -0.7603 -0.7554 -0.7439 100.0000 -0.7047 0.200 -0.8002 -0.8217 -0.7409 -0.6775 -0.7050 -0.7153 100.0000 0.150 -0.8381 -0.9309 -0.9513 100.0000 -1.1784 100.0000 -0.6115 0.100 -0.9224 -1.1867 -1.5580 -1.5520 -1.4970 -1.3615 -1.1707 0.050 -1.3532 -1.6179 -1.6171 -1.4850 -1.4339 -1.3727 -1.2995 0.030 -1.4566 -1.5267 -1.3722 -1.2005 -1.1418 -1.1021 -1.0289 0.020 -1.2157 -1.1908 -1.0026 -0.9400 -0.9078 -0.8430 -0.8135 0.010 -0.5362 -0.3684 -0.4722 -0.5268 -0.4090 -0.3529 -0.3479 0.000 0.7381 0.7020 0.6011 0.6951 0.5946 0.7187 0.7664 0.010 0.6471 0.6485 0.6167 0.5694 0.5650 0.5759 0.5659 0.030 0.3536 0.3486 0.2960 0.2608 0.2888 0.2978 0.2944 0.050 0.1342 0.1187 0.1282 0.1919 0.1797 0.1801 0.1555 0.100 -0.0765 -0.0840 -0.0440 0.0159 0.0173 0.0483 0.0147 0.200 -0.1898 -0.1990 -0.1699 -0.1212 -0.0930 -0.0706 -0.0965 0.300 -0.2454 -0.2653 -0.2477 -0.2334 -0.1956 -0.1944 100.0000 0.400 -0.2820 -0.3035 -0.2859 -0.2663 -0.2160 -0.2045 -0.2365 0.500 -0.3051 -0.2949 -0.2657 -0.2260 100.0000 -0.1720 -0.1875 0.600 -0.1960 -0.1959 -0.1748 -0.1741 -0.1187 -0.1168 -0.1327 0.700 0.0290 0.0433 0.0458 0.0358 0.0577 0.0533 0.0409 0.800 0.2042 0.2161 0.2428 0.2266 0.2319 0.2371 0.2078 0.900 0.2467 0.2734 0.3103 0.3180 0.3021 0.3021 0.2692 0.950 0.2394 0.2688 0.3065 0.3150 0.2805 0.2897 0.2499 1 TABLE NR. 2.3.1.2 RE=3*10E6 CL=0.52 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0365 -0.1018 -.485 -0.0150 -0.0983 -.406 0.0047 -0.0698 -.327 0.0148 -0.0802 -.248 0.0473 -0.0782 -.168 0.0539 -0.0947 -.089 0.0523 -0.0820 -.010 0.0436 -0.1001 0.069 0.0438 -0.1330 0.148 0.0205 -0.1400 0.227 0.0023 -0.1563 0.306 -0.0261 -0.1703 0.386 -0.0201 -0.1870 0.465 -0.0169 -0.1815 0.544 -0.0062 -0.1723 0.623 -0.0071 -0.1749 0.702 0.0020 -0.1617 0.781 0.0006 -0.1444 0.860 0.0279 -0.1324 0.940 0.0193 -0.1124 1.019 0.0133 -0.1048 1.098 0.0079 -0.0852 1 TABLE NR. 2.3.1.3 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 0.1128 0.1092 0.0861 0.0328 0.0411 0.0491 0.0728 0.950 0.0143 0.0233 0.0068 -0.0286 -0.0056 -0.0072 0.0200 0.900 -0.1040 -0.0877 -0.0917 -0.1182 -0.0782 -0.0886 -0.0555 0.800 -0.2877 -0.2847 -0.2948 -0.3518 -0.2772 -0.2804 -0.2396 0.700 -0.4407 -0.4609 -0.5138 -0.5786 -0.4952 -0.4852 -0.4425 0.650 -0.5012 -0.5368 -0.6338 -0.7064 -0.6107 -0.5886 -0.5501 0.600 -0.5506 -0.5771 -0.6697 -0.7736 -0.6652 -0.6477 -0.5952 0.550 -0.5638 -0.5931 -0.6576 -0.7385 -0.6769 100.0000 -0.5813 0.500 -0.5642 -0.5769 -0.6418 -0.6896 -0.6804 -0.6352 -0.6005 0.450 -0.5859 -0.6034 -0.6449 -0.6537 -0.7075 -0.6501 -0.6061 0.425 -0.6108 -0.6383 -0.6707 -0.7132 -0.7247 100.0000 -0.6363 0.400 -0.6406 -0.6692 -0.6557 -0.7119 -0.7073 -0.6499 100.0000 0.350 -0.6594 -0.6337 -0.6672 -0.6333 -0.6346 -0.6031 -0.6791 0.300 -0.7453 -0.7200 -0.6480 -0.6481 -0.7105 -0.6452 -0.6590 0.250 -0.8152 -0.9119 -0.8512 -1.1786 -1.1361 100.0000 -0.5992 0.200 -0.8410 -0.9145 -1.2059 -1.1855 -1.1516 -1.1616 100.0000 0.150 -0.8292 -0.8861 -1.3040 100.0000 -1.1835 100.0000 -1.0965 0.100 -0.9159 -1.2248 -1.3411 -1.3198 -1.3089 -1.1907 -1.2346 0.050 -1.1383 -1.3476 -1.3299 -1.2073 -1.1622 -1.1134 -1.0856 0.030 -1.1971 -1.2446 -1.1004 -0.9233 -0.8653 -0.8384 -0.8086 0.020 -0.9567 -0.9249 -0.7412 -0.6668 -0.6424 -0.5876 -0.5922 0.010 -0.3392 -0.1856 -0.2644 -0.2855 -0.1805 -0.1344 -0.1537 0.000 0.7949 0.7664 0.6893 0.7611 0.7113 0.7928 0.8157 0.010 0.6217 0.6172 0.5660 0.4931 0.4838 0.4991 0.4970 0.030 0.3163 0.2988 0.2287 0.1759 0.2079 0.2210 0.2256 0.050 0.0923 0.0676 0.0623 0.1286 0.1073 0.1118 0.0923 0.100 -0.1177 -0.1278 -0.1036 -0.0481 -0.0123 -0.0110 -0.0370 0.200 -0.2289 -0.2455 -0.2240 -0.1765 -0.1355 -0.1361 -0.1406 0.300 -0.2838 -0.3151 -0.3112 -0.3072 -0.2646 -0.2376 100.0000 0.400 -0.3269 -0.3546 -0.3455 -0.3262 -0.2685 -0.2507 -0.2777 0.500 -0.3514 -0.3422 -0.3124 -0.2727 100.0000 -0.2056 -0.2146 0.600 -0.2203 -0.2195 -0.2010 -0.2048 -0.1396 -0.1342 -0.1450 0.700 0.0251 0.0391 0.0415 0.0294 0.0555 0.0538 0.0435 0.800 0.2036 0.2157 0.2440 0.2243 0.2322 0.2377 0.2076 0.900 0.2514 0.2769 0.3122 0.3175 0.3013 0.3040 0.2701 0.950 0.2433 0.2737 0.3098 0.3165 0.2815 0.2963 0.2571 1 TABLE NR. 2.3.1.3 RE=3*10E6 CL=0.50 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0384 -0.0967 -.485 -0.0166 -0.0904 -.406 0.0028 -0.0609 -.327 0.0150 -0.0701 -.248 0.0500 -0.0664 -.168 0.0558 -0.0833 -.089 0.0533 -0.0716 -.010 0.0431 -0.0911 0.069 0.0394 -0.1287 0.148 0.0118 -0.1397 0.227 -0.0114 -0.1637 0.306 -0.0418 -0.1849 0.386 -0.0406 -0.2066 0.465 -0.0360 -0.2060 0.544 -0.0230 -0.1953 0.623 -0.0228 -0.1951 0.702 -0.0065 -0.1789 0.781 -0.0055 -0.1584 0.860 0.0249 -0.1429 0.940 0.0192 -0.1191 1.019 0.0140 -0.1079 1.098 0.0071 -0.0869 1 TABLE NR. 2.3.1.5 RE=3*10E6 CL=0.52 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 0.1096 0.1064 0.0829 0.0325 0.0405 0.0536 0.0775 0.950 0.0129 0.0283 0.0133 -0.0238 -0.0020 -0.0013 0.0271 0.900 -0.0989 -0.0800 -0.0809 -0.1053 -0.0676 -0.0792 -0.0461 0.800 -0.2834 -0.2790 -0.2808 -0.3251 -0.2554 -0.2639 -0.2279 0.700 -0.4464 -0.4651 -0.5044 -0.5408 -0.4583 -0.4551 -0.4332 0.650 -0.5183 -0.5541 -0.6686 -0.8040 -0.5586 -0.5439 -0.5411 0.600 -0.5717 -0.6008 -0.6985 -0.7628 -0.5948 -0.5684 -0.5856 0.550 -0.5823 -0.6132 -0.6631 -0.6979 -0.5937 100.0000 -0.5563 0.500 -0.5747 -0.5768 -0.6228 -0.6428 -0.6230 -0.5295 -0.5509 0.450 -0.5972 -0.5918 -0.6125 -0.6366 -0.9695 -0.9890 -0.5213 0.425 -0.7157 -0.7008 -0.6382 -0.7933 -1.0994 -0.9890 -0.5207 0.400 -0.7721 -0.7722 -0.7613 -0.9905 -1.0963 -1.0782 100.0000 0.350 -0.7731 -0.7860 -0.8723 -1.1087 -1.0988 -1.0805 -0.7966 0.300 -0.8296 -0.9072 -0.8978 -1.1029 -1.1078 -1.0956 -1.0222 0.250 -0.8318 -0.9277 -1.1023 -1.1524 -1.1183 100.0000 -1.0475 0.200 -0.8325 -0.9077 -1.1830 -1.1396 -1.1186 -1.1217 100.0000 0.150 -0.8253 -1.0387 -1.2466 100.0000 -1.1238 100.0000 -1.0735 0.100 -0.8993 -1.1932 -1.2697 -1.2417 -1.2335 -1.1373 -1.1834 0.050 -1.1010 -1.2707 -1.2439 -1.1231 -1.0821 -1.0352 -1.0202 0.030 -1.1291 -1.1642 -1.0168 -0.8417 -0.7865 -0.7649 -0.7504 0.020 -0.8885 -0.8502 -0.6708 -0.5899 -0.5701 -0.5212 -0.5362 0.010 -0.2857 -0.1395 -0.2060 -0.2179 -0.1142 -0.0849 -0.1091 0.000 0.8113 0.7852 0.7092 0.7737 0.7358 0.8063 0.8247 0.010 0.6224 0.6149 0.5566 0.4785 0.4635 0.4786 0.4896 0.030 0.3153 0.2969 0.2197 0.1621 0.1892 0.2052 0.2141 0.050 0.0907 0.0632 0.0537 0.1105 0.0890 0.0977 0.0807 0.100 -0.1206 -0.1317 -0.1097 -0.0612 -0.0249 -0.0269 -0.0487 0.200 -0.2362 -0.2526 -0.2359 -0.1897 -0.1458 -0.1491 -0.1500 0.300 -0.2918 -0.3289 -0.3291 -0.3302 -0.2901 -0.2575 100.0000 0.400 -0.3422 -0.3719 -0.3660 -0.3470 -0.2839 -0.2653 -0.2912 0.500 -0.3720 -0.3622 -0.3274 -0.2853 100.0000 -0.2167 -0.2241 0.600 -0.2306 -0.2251 -0.2070 -0.2113 -0.1460 -0.1398 -0.1493 0.700 0.0234 0.0397 0.0442 0.0305 0.0536 0.0553 0.0440 0.800 0.2040 0.2164 0.2446 0.2261 0.2308 0.2382 0.2066 0.900 0.2519 0.2795 0.3145 0.3198 0.3005 0.3048 0.2677 0.950 0.2443 0.2750 0.3115 0.3185 0.2816 0.2979 0.2587 1 TABLE NR. 2.3.1.5 RE=3*10E6 CL=0.52 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0394 -0.0969 -.485 -0.0157 -0.0878 -.406 0.0052 -0.0575 -.327 0.0186 -0.0653 -.248 0.0527 -0.0619 -.168 0.0604 -0.0788 -.089 0.0587 -0.0676 -.010 0.0456 -0.0883 0.069 0.0411 -0.1296 0.148 0.0133 -0.1446 0.227 -0.0115 -0.1728 0.306 -0.0444 -0.1995 0.386 -0.0437 -0.2275 0.465 -0.0418 -0.2261 0.544 -0.0277 -0.2153 0.623 -0.0251 -0.2143 0.702 -0.0077 -0.1941 0.781 -0.0042 -0.1691 0.860 0.0256 -0.1495 0.940 0.0197 -0.1232 1.019 0.0159 -0.1099 1.098 0.0106 -0.0869 1 TABLE NR. 2.3.1.6 RE=3*10E6 CL=0.52 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 0.1072 0.1063 0.0801 0.0170 0.0349 0.0456 0.0799 0.950 0.0169 0.0297 0.0133 -0.0304 -0.0082 -0.0092 0.0324 0.900 -0.0943 -0.0748 -0.0742 -0.0981 -0.0649 -0.0670 -0.0400 0.800 -0.2768 -0.2706 -0.2650 -0.2997 -0.2258 -0.2311 -0.2137 0.700 -0.4422 -0.4586 -0.4843 -0.5098 -0.3984 -0.3964 -0.4100 0.650 -0.5201 -0.5530 -0.6590 -0.7285 -0.4742 -0.4661 -0.5012 0.600 -0.5823 -0.5986 -0.6855 -0.7054 -0.5302 -0.4910 -0.5235 0.550 -0.5799 -0.5936 -0.6386 -0.7718 -0.7823 100.0000 -0.4814 0.500 -0.6028 -0.5834 -0.6852 -0.8579 -1.0609 -0.9840 -0.4700 0.450 -0.7629 -0.7900 -0.8472 -0.9911 -1.0969 -1.0769 -0.5653 0.425 -0.7952 -0.8183 -0.8965 -1.0615 -1.1027 100.0000 -0.8452 0.400 -0.7992 -0.8256 -0.8641 -1.0489 -1.0906 -1.0734 100.0000 0.350 -0.7814 -0.8133 -0.8762 -1.0974 -1.0813 -1.0644 -1.0260 0.300 -0.8305 -0.9180 -0.9667 -1.0845 -1.0837 -1.0725 -1.0168 0.250 -0.8337 -0.9173 -1.0921 -1.1235 -1.0881 100.0000 -1.0304 0.200 -0.8196 -0.9001 -1.1552 -1.1064 -1.0791 -1.0852 100.0000 0.150 -0.8159 -1.0532 -1.2092 100.0000 -1.0792 100.0000 -1.0402 0.100 -0.8828 -1.1637 -1.2250 -1.1956 -1.1846 -1.0787 -1.1403 0.050 -1.0666 -1.2271 -1.1964 -1.0777 -1.0338 -0.9865 -0.9788 0.030 -1.0846 -1.1174 -0.9712 -0.7965 -0.7414 -0.7185 -0.7073 0.020 -0.8494 -0.8091 -0.6297 -0.5455 -0.5247 -0.4758 -0.4979 0.010 -0.2546 -0.1127 -0.1744 -0.1831 -0.0735 -0.0463 -0.0693 0.000 0.8210 0.7944 0.7211 0.7821 0.7544 0.8164 0.8365 0.010 0.6240 0.6127 0.5514 0.4644 0.4518 0.4660 0.4765 0.030 0.3142 0.2936 0.2129 0.1478 0.1761 0.1876 0.2005 0.050 0.0876 0.0593 0.0452 0.1006 0.0792 0.0858 0.0708 0.100 -0.1227 -0.1344 -0.1157 -0.0704 -0.0361 -0.0391 -0.0555 0.200 -0.2399 -0.2589 -0.2425 -0.2003 -0.1551 -0.1601 -0.1565 0.300 -0.2989 -0.3401 -0.3434 -0.3432 -0.3074 -0.2712 100.0000 0.400 -0.3499 -0.3849 -0.3817 -0.3637 -0.2972 -0.2767 -0.3029 0.500 -0.3824 -0.3736 -0.3395 -0.2983 100.0000 -0.2247 -0.2300 0.600 -0.2341 -0.2297 -0.2114 -0.2186 -0.1513 -0.1440 -0.1513 0.700 0.0257 0.0404 0.0441 0.0277 0.0541 0.0516 0.0442 0.800 0.2047 0.2183 0.2434 0.2222 0.2291 0.2343 0.2050 0.900 0.2523 0.2798 0.3135 0.3151 0.2993 0.3023 0.2684 0.950 0.2460 0.2758 0.3097 0.3158 0.2793 0.2955 0.2583 1 TABLE NR. 2.3.1.6 RE=3*10E6 CL=0.52 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0385 -0.0942 -.485 -0.0149 -0.0840 -.406 0.0073 -0.0544 -.327 0.0192 -0.0630 -.248 0.0527 -0.0567 -.168 0.0617 -0.0748 -.089 0.0592 -0.0636 -.010 0.0488 -0.0840 0.069 0.0398 -0.1254 0.148 0.0125 -0.1444 0.227 -0.0141 -0.1758 0.306 -0.0480 -0.2051 0.386 -0.0471 -0.2357 0.465 -0.0475 -0.2371 0.544 -0.0300 -0.2288 0.623 -0.0265 -0.2242 0.702 -0.0098 -0.2031 0.781 -0.0060 -0.1771 0.860 0.0243 -0.1554 0.940 0.0225 -0.1269 1.019 0.0172 -0.1120 1.098 0.0121 -0.0863 1 TABLE NR. 2.3.1.7 RE=3*10E6 CL=0.52 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 0.0993 0.1005 0.0676 -0.0029 -0.0137 -0.0054 0.0746 0.950 0.0168 0.0288 0.0079 -0.0529 -0.0632 -0.0423 0.0321 0.900 -0.0894 -0.0706 -0.0716 -0.1111 -0.1064 -0.0786 -0.0317 0.800 -0.2699 -0.2624 -0.2505 -0.2746 -0.2185 -0.1868 -0.1908 0.700 -0.4319 -0.4473 -0.4548 -0.4564 -0.3666 -0.3308 -0.3673 0.650 -0.5072 -0.5433 -0.5864 -0.6690 -0.4561 -0.4068 -0.4410 0.600 -0.5792 -0.5813 -0.7598 -0.9607 -0.5949 -0.4953 -0.4494 0.550 -0.6920 -0.6779 -0.8160 -0.9195 -1.0851 100.0000 -0.4495 0.500 -0.6955 -0.7725 -0.8522 -0.9689 -1.0814 -1.0628 -0.6473 0.450 -0.8084 -0.8399 -0.9135 -1.0499 -1.0968 -1.0791 -0.9978 0.425 -0.8122 -0.8543 -0.9271 -1.0572 -1.0991 100.0000 -1.0096 0.400 -0.8070 -0.8545 -0.8775 -1.0837 -1.0879 -1.0646 100.0000 0.350 -0.7851 -0.8276 -0.8796 -1.0881 -1.0719 -1.0507 -1.0268 0.300 -0.8318 -0.9213 -1.0729 -1.0686 -1.0647 -1.0548 -1.0081 0.250 -0.8361 -0.9174 -1.1028 -1.1032 -1.0642 100.0000 -1.0154 0.200 -0.8187 -0.8955 -1.1386 -1.0842 -1.0533 -1.0538 100.0000 0.150 -0.8148 -1.0581 -1.1815 100.0000 -1.0445 100.0081 -1.0142 0.100 -0.8805 -1.1412 -1.1963 -1.1600 -1.1499 -1.0481 -1.1009 0.050 -1.0577 -1.1983 -1.1647 -1.0392 -0.9964 -0.9476 -0.9404 0.030 -1.0522 -1.0880 -0.9365 -0.7587 -0.7063 -0.6794 -0.6662 0.020 -0.8205 -0.7817 -0.6033 -0.5105 -0.4924 -0.4370 -0.4643 0.010 -0.2305 -0.0885 -0.1534 -0.1572 -0.0461 -0.0097 -0.0406 0.000 0.8263 0.7941 0.7280 0.7911 0.7601 0.8207 0.8412 0.010 0.6235 0.6123 0.5431 0.4584 0.4387 0.4522 0.4622 0.030 0.3170 0.2915 0.2058 0.1401 0.1636 0.1775 0.1853 0.050 0.0920 0.0581 0.0406 0.0884 0.0677 0.0759 0.0578 0.100 -0.1220 -0.1370 -0.1258 -0.0777 -0.0483 -0.0491 -0.0700 0.200 -0.2404 -0.2645 -0.2547 -0.2070 -0.1702 -0.1730 -0.1714 0.300 -0.3039 -0.3497 -0.3578 -0.3617 -0.3251 -0.2928 100.0000 0.400 -0.3607 -0.4001 -0.3999 -0.3813 -0.3167 -0.2982 -0.3214 0.500 -0.3971 -0.3919 -0.3574 -0.3117 100.0000 -0.2448 -0.2430 0.600 -0.2409 -0.2393 -0.2231 -0.2290 -0.1670 -0.1632 -0.1602 0.700 0.0235 0.0359 0.0381 0.0228 0.0422 0.0376 0.0404 0.800 0.2019 0.2127 0.2384 0.2173 0.2172 0.2222 0.2017 0.900 0.2514 0.2755 0.3105 0.3090 0.2849 0.2879 0.2646 0.950 0.2431 0.2715 0.3069 0.3095 0.2622 0.2779 0.2562 1 TABLE NR. 2.3.1.7 RE=3*10E6 CL=0.52 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0380 -0.0933 -.485 -0.0141 -0.0808 -.406 0.0094 -0.0524 -.327 0.0215 -0.0587 -.248 0.0557 -0.0544 -.168 0.0647 -0.0725 -.089 0.0621 -0.0589 -.010 0.0501 -0.0814 0.069 0.0412 -0.1242 0.148 0.0130 -0.1424 0.227 -0.0148 -0.1793 0.306 -0.0503 -0.2112 0.386 -0.0514 -0.2466 0.465 -0.0513 -0.2534 0.544 -0.0369 -0.2449 0.623 -0.0304 -0.2409 0.702 -0.0124 -0.2155 0.781 -0.0066 -0.1842 0.860 0.0251 -0.1589 0.940 0.0201 -0.1285 1.019 0.0169 -0.1117 1.098 0.0107 -0.0857 1 TABLE NR. 2.3.1.8 RE=3*10E6 CL=0.52 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 0.0928 0.0901 0.0530 -0.0447 -0.1421 -0.1012 0.0633 0.950 0.0156 0.0273 -0.0063 -0.1169 -0.2007 -0.1375 0.0274 0.900 -0.0825 -0.0631 -0.0760 -0.1715 -0.2293 -0.1553 -0.0258 0.800 -0.2523 -0.2402 -0.2330 -0.3070 -0.2939 -0.2094 -0.1619 0.700 -0.4036 -0.4071 -0.4120 -0.4529 -0.3686 -0.2865 -0.3212 0.650 -0.4959 -0.5312 -0.6567 -0.6120 -0.4127 -0.3399 -0.3824 0.600 -0.7497 -0.7459 -0.8983 -0.9728 -0.4658 -0.4024 -0.4218 0.550 -0.7383 -0.8116 -0.8981 -1.0812 -0.5739 100.0000 -0.5092 0.500 -0.7715 -0.8220 -0.9046 -1.0760 -1.0837 -0.7386 -0.9614 0.450 -0.8210 -0.8641 -0.9331 -1.0739 -1.0987 -1.0459 -1.0131 0.425 -0.8233 -0.8714 -0.9305 -1.1097 -1.0980 100.0000 -1.0228 0.400 -0.8174 -0.8657 -0.8803 -1.1017 -1.0830 -1.0616 100.0000 0.350 -0.7946 -0.8404 -0.9583 -1.0905 -1.0652 -1.0426 -1.0233 0.300 -0.8381 -0.9251 -1.0878 -1.0608 -1.0565 -1.0477 -0.9990 0.250 -0.8326 -0.9167 -1.1149 -1.0957 -1.0488 100.0000 -1.0020 0.200 -0.8170 -0.8931 -1.1327 -1.0728 -1.0380 -1.0369 100.0000 0.150 -0.8069 -1.0370 -1.1681 100.0000 -1.0219 100.0000 -0.9898 0.100 -0.9304 -1.1418 -1.1778 -1.1406 -1.1180 -1.0026 -1.0699 0.050 -1.0817 -1.1796 -1.1392 -1.0140 -0.9642 -0.9164 -0.9064 0.030 -1.0380 -1.0660 -0.9131 -0.7419 -0.6802 -0.6556 -0.6382 0.020 -0.8090 -0.7678 -0.5869 -0.4961 -0.4680 -0.4157 -0.4386 0.010 -0.2240 -0.0842 -0.1421 -0.1452 -0.0292 0.0041 -0.0173 0.000 0.8287 0.7980 0.7310 0.7909 0.7634 0.8258 0.8455 0.010 0.6374 0.6242 0.5554 0.4647 0.4448 0.4515 0.4604 0.030 0.3348 0.3057 0.2197 0.1515 0.1703 0.1773 0.1843 0.050 0.1103 0.0761 0.0530 0.0964 0.0720 0.0735 0.0550 0.100 -0.1070 -0.1246 -0.1138 -0.0696 -0.0408 -0.0525 -0.0736 0.200 -0.2312 -0.2545 -0.2460 -0.2045 -0.1697 -0.1831 -0.1789 0.300 -0.2981 -0.3478 -0.3597 -0.3720 -0.3405 -0.3205 100.0000 0.400 -0.3630 -0.4069 -0.4145 -0.3963 -0.3342 -0.3270 -0.3388 0.500 -0.4084 -0.4053 -0.3690 -0.3256 100.0000 -0.2776 -0.2576 0.600 -0.2444 -0.2417 -0.2286 -0.2407 -0.1876 -0.1970 -0.1703 0.700 0.0264 0.0358 0.0363 0.0137 0.0188 0.0070 0.0352 0.800 0.2038 0.2136 0.2371 0.2087 0.1944 0.1968 0.1979 0.900 0.2517 0.2766 0.3090 0.3024 0.2570 0.2607 0.2599 0.950 0.2431 0.2698 0.3031 0.2987 0.2202 0.2448 0.2531 1 TABLE NR. 2.3.1.8 RE=3*10E6 CL=0.52 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0391 -0.0934 -.485 -0.0094 -0.0794 -.406 0.0106 -0.0463 -.327 0.0249 -0.0553 -.248 0.0617 -0.0477 -.168 0.0674 -0.0666 -.089 0.0668 -0.0544 -.010 0.0574 -0.0764 0.069 0.0499 -0.1224 0.148 0.0176 -0.1447 0.227 -0.0108 -0.1804 0.306 -0.0463 -0.2194 0.386 -0.0498 -0.2581 0.465 -0.0521 -0.2712 0.544 -0.0384 -0.2692 0.623 -0.0323 -0.2602 0.702 -0.0108 -0.2294 0.781 -0.0089 -0.1942 0.860 0.0257 -0.1649 0.940 0.0230 -0.1316 1.019 0.0191 -0.1113 1.098 0.0149 -0.0859 1 TABLE NR. 2.3.1.9 RE=3*10E6 CL=0.52 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 0.0755 0.0736 0.0221 -0.1208 -0.2247 -0.1656 0.0298 0.950 0.0078 0.0124 -0.0450 -0.2332 -0.2873 -0.2040 -0.0035 0.900 -0.0806 -0.0617 -0.1093 -0.2983 -0.2994 -0.2235 -0.0395 0.800 -0.2428 -0.2188 -0.2471 -0.4112 -0.3250 -0.2659 -0.1379 0.700 -0.3998 -0.3933 -0.4205 -0.5026 -0.3725 -0.3155 -0.2770 0.650 -0.6609 -0.6962 -0.6994 -0.5550 -0.3975 -0.3496 -0.3458 0.600 -0.8100 -0.8154 -0.9403 -0.8264 -0.4307 -0.3884 -0.4236 0.550 -0.7753 -0.8647 -0.9268 -1.1120 -0.4606 100.0000 -0.5831 0.500 -0.8169 -0.8382 -0.9261 -1.0983 -0.5582 -0.5083 -1.0169 0.450 -0.8322 -0.8757 -0.9291 -1.1059 -1.0843 -0.9269 -1.0191 0.425 -0.8331 -0.8814 -0.9251 -1.1205 -1.1009 100.0000 -1.0219 0.400 -0.8324 -0.8838 -0.8976 -1.1082 -1.0835 -1.0513 100.0000 0.350 -0.8105 -0.8645 -1.0660 -1.0927 -1.0649 -1.0404 -1.0227 0.300 -0.8496 -0.9266 -1.1104 -1.0597 -1.0524 -1.0409 -0.9893 0.250 -0.8381 -0.9220 -1.1205 -1.0900 -1.0452 100.0000 -0.9915 0.200 -0.8248 -0.9281 -1.1307 -1.0673 -1.0314 -1.0246 100.0000 0.150 -0.8215 -1.0501 -1.1633 100.0000 -1.0082 100.0000 -0.9725 0.100 -0.9521 -1.1462 -1.1610 -1.1198 -1.1008 -0.9909 -1.0507 0.050 -1.1011 -1.1652 -1.1178 -0.9958 -0.9421 -0.8933 -0.8826 0.030 -1.0294 -1.0467 -0.8913 -0.7271 -0.6676 -0.6380 -0.6223 0.020 -0.8062 -0.7580 -0.5797 -0.4888 -0.4561 -0.3992 -0.4215 0.010 -0.2232 -0.0812 -0.1351 -0.1377 -0.0241 0.0151 -0.0022 0.000 0.8293 0.8009 0.7295 0.7921 0.7635 0.8279 0.8492 0.010 0.6556 0.6376 0.5685 0.4729 0.4506 0.4569 0.4597 0.030 0.3562 0.3292 0.2366 0.1652 0.1797 0.1813 0.1851 0.050 0.1308 0.0964 0.0683 0.1073 0.0776 0.0730 0.0537 0.100 -0.0891 -0.1090 -0.1013 -0.0611 -0.0381 -0.0531 -0.0771 0.200 -0.2206 -0.2418 -0.2371 -0.1984 -0.1706 -0.1880 -0.1869 0.300 -0.2941 -0.3426 -0.3630 -0.3829 -0.3572 -0.3476 100.0000 0.400 -0.3671 -0.4128 -0.4266 -0.4131 -0.3575 -0.3570 -0.3651 0.500 -0.4267 -0.4204 -0.3826 -0.3442 100.0000 -0.3106 -0.2815 0.600 -0.2520 -0.2468 -0.2374 -0.2577 -0.2187 -0.2299 -0.1906 0.700 0.0226 0.0362 0.0303 0.0012 -0.0097 -0.0170 0.0208 0.800 0.2018 0.2117 0.2299 0.1966 0.1696 0.1747 0.1853 0.900 0.2509 0.2756 0.3019 0.2856 0.2309 0.2416 0.2474 0.950 0.2384 0.2664 0.2949 0.2757 0.1889 0.2216 0.2386 1 TABLE NR. 2.3.1.9 RE=3*10E6 CL=0.52 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0374 -0.0916 -.485 -0.0124 -0.0771 -.406 0.0108 -0.0462 -.327 0.0296 -0.0545 -.248 0.0656 -0.0465 -.168 0.0714 -0.0628 -.089 0.0710 -0.0547 -.010 0.0603 -0.0769 0.069 0.0502 -0.1207 0.148 0.0208 -0.1435 0.227 -0.0084 -0.1838 0.306 -0.0502 -0.2274 0.386 -0.0548 -0.2731 0.465 -0.0541 -0.2908 0.544 -0.0423 -0.2990 0.623 -0.0374 -0.2892 0.702 -0.0183 -0.2539 0.781 -0.0114 -0.2090 0.860 0.0224 -0.1730 0.940 0.0175 -0.1341 1.019 0.0159 -0.1146 1.098 0.0110 -0.0849 1 TABLE NR. 2.3.1.10 RE=3*10E6 CL=0.52 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 0.0318 0.0397 -0.0346 -0.2368 -0.2855 -0.2185 -0.0485 0.950 -0.0273 -0.0175 -0.1192 -0.3697 -0.3346 -0.2604 -0.0831 0.900 -0.0969 -0.0852 -0.1762 -0.4276 -0.3415 -0.2736 -0.1145 0.800 -0.2454 -0.2309 -0.3035 -0.4955 -0.3558 -0.3062 -0.1772 0.700 -0.4251 -0.4173 -0.4375 -0.5355 -0.3813 -0.3462 -0.2684 0.650 -0.7341 -0.7956 -0.6246 -0.5562 -0.3965 -0.3724 -0.3210 0.600 -0.8233 -0.8811 -0.9707 -0.6094 -0.4181 -0.3973 -0.3863 0.550 -0.8035 -0.8862 -0.9526 -1.1170 -0.4407 100.0000 -0.4765 0.500 -0.8379 -0.8567 -0.9381 -1.1291 -0.4710 -0.4688 -0.7665 0.450 -0.8442 -0.8960 -0.9459 -1.1224 -0.5859 -0.6774 -1.0317 0.425 -0.8427 -0.9088 -1.0373 -1.1311 -0.9250 100.0000 -1.0352 0.400 -0.8481 -0.9064 -1.0531 -1.1181 -1.0818 -0.9411 100.0000 0.350 -0.8232 -0.8764 -1.1026 -1.0992 -1.0679 -1.0429 -1.0307 0.300 -0.8588 -0.9420 -1.1331 -1.0638 -1.0556 -1.0377 -0.9959 0.250 -0.8481 -0.9248 -1.1343 -1.0930 -1.0470 100.0000 -0.9956 0.200 -0.8336 -1.0205 -1.1400 -1.0660 -1.0315 -1.0221 100.0000 0.150 -0.8433 -1.1089 -1.1657 100.0000 -1.0045 100.0000 -0.9683 0.100 -0.9670 -1.1757 -1.1594 -1.1096 -1.0921 -0.9801 -1.0328 0.050 -1.1034 -1.1638 -1.1103 -0.9832 -0.9295 -0.8773 -0.8632 0.030 -1.0301 -1.0374 -0.8818 -0.7232 -0.6622 -0.6283 -0.6116 0.020 -0.8085 -0.7586 -0.5826 -0.4879 -0.4547 -0.3926 -0.4122 0.010 -0.2276 -0.0803 -0.1376 -0.1421 -0.0269 0.0182 0.0030 0.000 0.8269 0.8000 0.7233 0.7896 0.7571 0.8231 0.8481 0.010 0.6705 0.6521 0.5818 0.4902 0.4633 0.4638 0.4639 0.030 0.3777 0.3495 0.2562 0.1801 0.1901 0.1874 0.1865 0.050 0.1579 0.1171 0.0903 0.1523 0.0870 0.0813 0.0529 0.100 -0.0672 -0.0913 -0.0860 -0.0485 -0.0344 -0.0508 -0.0797 0.200 -0.2061 -0.2303 -0.2296 -0.1923 -0.1718 -0.1920 -0.1976 0.300 -0.2863 -0.3406 -0.3624 -0.3945 -0.3766 -0.3727 -0.1976 0.400 -0.3712 -0.4245 -0.4532 -0.4401 -0.3851 -0.3863 -0.4039 0.500 -0.4548 -0.4542 -0.4101 -0.3687 100.0000 -0.3417 -0.3161 0.600 -0.2627 -0.2620 -0.2571 -0.2817 -0.2483 -0.2578 -0.2228 0.700 0.0170 0.0241 0.0175 -0.0185 -0.0353 -0.0389 -0.0083 0.800 0.1966 0.2012 0.2174 0.1757 0.1468 0.1572 0.1579 0.900 0.2428 0.2630 0.2876 0.2639 0.2112 0.2219 0.2207 0.950 0.2256 0.2526 0.2754 0.2485 0.1650 0.2013 0.2054 1 TABLE NR. 2.3.1.10 RE=3*10E6 CL=0.52 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0353 -0.0882 -.485 -0.0088 -0.0762 -.406 0.0118 -0.0392 -.327 0.0310 -0.0519 -.248 0.0692 -0.0404 -.168 0.0794 -0.0584 -.089 0.0774 -0.0491 -.010 0.0657 -0.0769 0.069 0.0568 -0.1188 0.148 0.0271 -0.1430 0.227 -0.0052 -0.1847 0.306 -0.0514 -0.2336 0.386 -0.0530 -0.2866 0.465 -0.0607 -0.3105 0.544 -0.0477 -0.3229 0.623 -0.0419 -0.3251 0.702 -0.0194 -0.2758 0.781 -0.0142 -0.2238 0.860 0.0195 -0.1828 0.940 0.0171 -0.1408 1.019 0.0142 -0.1156 1.098 0.0055 -0.0873 1 TABLE NR. 3.3.1.1 RE=3*10E6 CL=0.31 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 0.1279 0.1198 0.0924 0.0414 0.0569 0.0614 0.0899 0.950 0.0158 0.0213 0.0071 -0.0262 -0.0010 -0.0024 0.0243 0.900 -0.1077 -0.0959 -0.0976 -0.1225 -0.0830 -0.0913 -0.0582 0.800 -0.2868 -0.2887 -0.2986 -0.3552 -0.2873 -0.2854 -0.2470 0.700 -0.4329 -0.4517 -0.5035 -0.5730 -0.4919 -0.4785 -0.4346 0.650 -0.4820 -0.5152 -0.6071 -0.6826 -0.5976 -0.5714 -0.5321 0.600 -0.5161 -0.5421 -0.6234 -0.7066 -0.6384 -0.6164 -0.5596 0.550 -0.5198 -0.5487 -0.6058 -0.6775 -0.6338 100.0000 -0.5334 0.500 -0.5080 -0.5285 -0.5927 -0.6443 -0.6339 -0.5886 -0.5396 0.450 -0.5205 -0.5470 -0.5917 -0.6107 -0.6502 -0.6091 -0.5318 0.425 -0.5398 -0.5731 -0.6110 -0.6571 -0.6768 100.0000 -0.5525 0.400 -0.5642 -0.5990 -0.5890 -0.6820 -0.6783 -0.6223 100.0000 0.350 -0.5639 -0.5732 -0.6258 -0.6438 -0.6424 -0.6088 -0.5764 0.300 -0.5800 -0.6011 -0.6309 -0.6155 -0.6555 -0.6270 -0.5700 0.250 -0.6162 -0.6801 -0.6864 -0.6725 -0.6313 100.0000 -0.5592 0.200 -0.6518 -0.6753 -0.7148 -0.6742 -0.6358 -0.6370 100.0000 0.150 -0.6369 -0.7415 -0.7081 100.0000 -0.4116 100.0000 -0.4716 0.100 -0.6603 -0.7103 -0.8871 -0.7958 -0.7478 -0.7376 -0.5961 0.050 -0.7576 -0.9259 -1.0809 -0.9465 -0.8541 -0.7910 -0.6534 0.030 -0.8134 -0.9452 -0.8215 -0.6440 -0.5582 -0.5069 -0.3982 0.020 -0.6485 -0.6702 -0.4972 -0.3753 -0.3411 -0.2758 -0.2137 0.010 -0.1082 0.0001 -0.0494 -0.0111 0.1146 0.1769 0.1907 0.000 0.8611 0.8221 0.7765 0.8261 0.8268 0.8621 0.8758 0.010 0.4870 0.4890 0.4064 0.2715 0.2368 0.2374 0.2041 0.030 0.1457 0.1214 0.0303 -0.0504 -0.0399 -0.0351 -0.0705 0.050 -0.0830 -0.1169 -0.1348 -0.0272 -0.1140 -0.1166 -0.1672 0.100 -0.2672 -0.2878 -0.2689 -0.2244 -0.2060 -0.2019 -0.2415 0.200 -0.3431 -0.3679 -0.3627 -0.3165 -0.2757 -0.2848 -0.2917 0.300 -0.3806 -0.4245 -0.4335 -0.4343 -0.4125 -0.3843 100.0000 0.400 -0.4053 -0.4418 -0.4428 -0.4358 -0.3711 -0.3532 -0.3748 0.500 -0.4150 -0.4119 -0.3847 -0.3486 100.0000 -0.2793 -0.2791 0.600 -0.2574 -0.2591 -0.2467 -0.2562 -0.1858 -0.1813 -0.1811 0.700 0.0031 0.0154 0.0152 -0.0006 0.0289 0.0288 0.0252 0.800 0.1852 0.1948 0.2185 0.1991 0.2044 0.2119 0.1827 0.900 0.2392 0.2635 0.2955 0.2980 0.2774 0.2806 0.2452 0.950 0.2380 0.2635 0.2940 0.3044 0.2645 0.2785 0.2436 1 TABLE NR. 3.3.1.1 RE=3*10E6 CL=0.31 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0510 -0.0899 -.485 -0.0296 -0.0799 -.406 -0.0118 -0.0481 -.327 0.0004 -0.0570 -.248 0.0299 -0.0494 -.168 0.0330 -0.0635 -.089 0.0268 -0.0444 -.010 0.0105 -0.0581 0.069 0.0011 -0.0901 0.148 -0.0286 -0.0977 0.227 -0.0552 -0.1162 0.306 -0.0853 -0.1342 0.386 -0.0815 -0.1549 0.465 -0.0757 -0.1559 0.544 -0.0575 -0.1503 0.623 -0.0502 -0.1572 0.702 -0.0308 -0.1478 0.781 -0.0250 -0.1342 0.860 0.0059 -0.1194 0.940 0.0034 -0.1007 1.019 0.0010 -0.0918 1.098 -0.0022 -0.0713 1 TABLE NR. 3.3.1.2 RE=3*10E6 CL=0.42 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 0.1189 0.1110 0.0849 0.0343 0.0444 0.0492 0.0693 0.950 0.0147 0.0214 0.0074 -0.0283 -0.0049 -0.0131 0.0217 0.900 -0.1050 -0.0918 -0.0963 -0.1199 -0.0816 -0.0889 -0.0511 0.800 -0.2885 -0.2892 -0.2992 -0.3530 -0.2847 -0.2836 -0.2326 0.700 -0.4422 -0.4597 -0.5114 -0.5794 -0.4997 -0.4860 -0.4311 0.650 -0.4975 -0.5314 -0.6274 -0.7014 -0.6123 -0.5864 -0.5326 0.600 -0.5391 -0.5671 -0.6586 -0.7656 -0.6647 -0.6427 -0.5721 0.550 -0.5490 -0.5804 -0.6429 -0.7389 -0.6757 100.0000 -0.5573 0.500 -0.5434 -0.5631 -0.6309 -0.6675 -0.6770 -0.6329 -0.5724 0.450 -0.5615 -0.5871 -0.6371 -0.6587 -0.7361 -0.6673 -0.5770 0.425 -0.5849 -0.6189 -0.6667 -0.7319 -0.7702 100.0000 -0.6044 0.400 -0.6100 -0.6479 -0.6432 -0.7685 -0.7401 -0.6971 100.0000 0.350 -0.6136 -0.6192 -0.6918 -0.7070 -0.7151 -0.6544 -0.6479 0.300 -0.6447 -0.6479 -0.6706 -0.6628 -0.7477 -0.7528 -0.6556 0.250 -0.7375 -0.7585 -0.7219 -0.6950 -0.6631 100.0000 -0.6628 0.200 -0.7463 -0.8484 -0.7358 -0.6066 -0.5958 -0.6083 100.0000 0.150 -0.7471 -0.8269 -1.0689 100.0000 -1.0281 100.0000 -0.5274 0.100 -0.7901 -1.0529 -1.2136 -1.2082 -1.1768 -1.0730 -0.8780 0.050 -0.9525 -1.2061 -1.2369 -1.1142 -1.0594 -1.0013 -0.9356 0.030 -1.0594 -1.1518 -1.0104 -0.8187 -0.7497 -0.7050 -0.6317 0.020 -0.8423 -0.8197 -0.6409 -0.5499 -0.5233 -0.4650 -0.4412 0.010 -0.2446 -0.1067 -0.1771 -0.1761 -0.0596 -0.0133 -0.0011 0.000 0.8251 0.7874 0.7266 0.7928 0.7654 0.8273 0.8546 0.010 0.5692 0.5658 0.5050 0.4116 0.3917 0.4008 0.3851 0.030 0.2465 0.2249 0.1511 0.0898 0.1117 0.1230 0.1048 0.050 0.0193 -0.0078 -0.0169 0.0460 0.0197 0.0235 -0.0105 0.100 -0.1816 -0.1909 -0.1693 -0.1175 -0.0907 -0.0905 -0.1220 0.200 -0.2801 -0.2982 -0.2838 -0.2355 -0.1903 -0.1982 -0.2075 0.300 -0.3251 -0.3634 -0.3613 -0.3581 -0.3281 -0.2955 100.0000 0.400 -0.3620 -0.3925 -0.3871 -0.3733 -0.3126 -0.2941 -0.3258 0.500 -0.3794 -0.3733 -0.3439 -0.3055 100.0000 -0.2379 -0.2457 0.600 -0.2380 -0.2384 -0.2220 -0.2259 -0.1614 -0.1562 -0.1654 0.700 0.0157 0.0290 0.0313 0.0165 0.0418 0.0402 0.0288 0.800 0.1938 0.2066 0.2337 0.2139 0.2202 0.2260 0.1932 0.900 0.2449 0.2699 0.3039 0.3107 0.2908 0.2928 0.2559 0.950 0.2403 0.2670 0.3019 0.3107 0.2722 0.2877 0.2463 1 TABLE NR. 3.3.1.2 RE=3*10E6 CL=0.42 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0444 -0.0939 -.485 -0.0221 -0.0843 -.406 -0.0029 -0.0551 -.327 0.0091 -0.0647 -.248 0.0402 -0.0583 -.168 0.0457 -0.0747 -.089 0.0420 -0.0593 -.010 0.0295 -0.0758 0.069 0.0233 -0.1097 0.148 -0.0027 -0.1205 0.227 -0.0291 -0.1414 0.306 -0.0596 -0.1601 0.386 -0.0581 -0.1825 0.465 -0.0518 -0.1818 0.544 -0.0363 -0.1732 0.623 -0.0337 -0.1766 0.702 -0.0184 -0.1646 0.781 -0.0143 -0.1473 0.860 0.0174 -0.1331 0.940 0.0135 -0.1114 1.019 0.0101 -0.1008 1.098 0.0052 -0.0794 1 TABLE NR. 3.3.1.3 RE=3*10E6 CL=0.57 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 0.1054 0.0897 0.0391 0.0466 0.0576 0.0714 0.950 0.0121 0.0219 0.0060 -0.0288 -0.0051 -0.0059 0.0180 0.900 -0.1035 -0.0901 -0.0955 -0.1213 -0.0819 -0.0920 -0.0580 0.800 -0.2867 -0.2859 -0.2974 -0.3528 -0.2809 -0.2815 -0.2423 0.700 -0.4431 -0.4635 -0.5130 -0.5767 -0.4871 -0.4735 -0.4441 0.650 -0.5053 -0.5401 -0.6286 -0.6907 -0.5875 -0.5643 -0.5459 0.600 -0.5564 -0.5827 -0.6628 -0.7275 -0.6242 -0.6026 -0.5878 0.550 -0.5763 -0.6034 -0.6534 -0.6991 -0.6176 100.0000 -0.5701 0.500 -0.5780 -0.5908 -0.6389 -0.6572 -0.6056 -0.5546 -0.5777 0.450 -0.6046 -0.6165 -0.6349 -0.6211 -0.6087 -0.5764 -0.5610 0.425 -0.6315 -0.6489 -0.6538 -0.6485 -0.6373 100.0000 -0.5691 0.400 -0.6689 -0.6719 -0.6381 -0.6778 -0.7276 -0.6352 100.0000 0.350 -0.7385 -0.6705 -0.6629 -1.0794 -1.2188 -1.1828 -0.5517 0.300 -0.8508 -0.9257 -0.8810 -1.2230 -1.2330 -1.2252 -0.8455 0.250 -0.8788 -0.9818 -1.2707 -1.2867 -1.2520 100.0000 -1.1817 0.200 -0.8938 -0.9656 -1.3290 -1.2828 -1.2557 -1.2627 100.0000 0.150 -0.9031 -1.1586 -1.3980 100.0000 -1.2724 100.0000 -1.2218 0.100 -1.0108 -1.3735 -1.4192 -1.3921 -1.3840 -1.2765 -1.3216 0.050 -1.2929 -1.4272 -1.3942 -1.2730 -1.2304 -1.1805 -1.1756 0.030 -1.2753 -1.3091 -1.1560 -1.0003 -0.9525 -0.9228 -0.9235 0.020 -1.0388 -1.0008 -0.8178 -0.7534 -0.7292 -0.6764 -0.6946 0.010 -0.4016 -0.2456 -0.3264 -0.3621 -0.2615 -0.2227 -0.2566 0.000 0.7751 0.7431 0.6531 0.7341 0.6608 0.7630 0.7841 0.010 0.6572 0.6480 0.6054 0.5466 0.5413 0.5595 0.5641 0.030 0.3657 0.3493 0.2802 0.2375 0.2646 0.2824 0.2985 0.050 0.1405 0.1175 0.1148 0.1922 0.1619 0.1702 0.1578 0.100 -0.0749 -0.0861 -0.0558 -0.0015 0.0114 0.0385 0.0161 0.200 -0.1967 -0.2092 -0.1871 -0.1369 -0.1066 -0.0836 -0.0998 0.300 -0.2539 -0.2854 -0.2752 -0.2658 -0.2221 -0.2083 100.0000 0.400 -0.3021 -0.3305 -0.3155 -0.2966 -0.2376 -0.2173 -0.2492 0.500 -0.3311 -0.3232 -0.2913 -0.2478 100.0000 -0.1796 -0.1921 0.600 -0.2084 -0.2083 -0.1874 -0.1863 -0.1238 -0.1167 -0.1304 0.700 0.0324 0.0465 0.0502 0.0400 0.0650 0.0643 0.0521 0.800 0.2083 0.2213 0.2509 0.2329 0.2406 0.2476 0.2156 0.900 0.2529 0.2810 0.3190 0.3264 0.3101 0.3104 0.2752 0.950 0.2443 0.2752 0.3136 0.3238 0.2881 0.3031 0.2628 1 TABLE NR. 3.3.1.3 RE=3*10E6 CL=0.57 DLR-F4 BODY LOWER UPPER X/CR CP CP -.564 -0.0339 -0.0983 -.485 -0.0112 -0.0917 -.406 0.0088 -0.0647 -.327 0.0219 -0.0748 -.248 0.0556 -0.0713 -.168 0.0626 -0.0900 -.089 0.0626 -0.0802 -.010 0.0533 -0.1014 0.069 0.0497 -0.1423 0.148 0.0256 -0.1564 0.227 0.0034 -0.1816 0.306 -0.0283 -0.2043 0.386 -0.0263 -0.2258 0.465 -0.0237 -0.2241 0.544 -0.0112 -0.2125 0.623 -0.0121 -0.2080 0.702 0.0011 -0.1909 0.781 0.0018 -0.1687 0.860 0.0314 -0.1504 0.940 0.0233 -0.1257 1.019 0.0180 -0.1138 1.098 0.0108 -0.0891