XFOIL Version 6.96 Calculated polar for: 74-130 WP2 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.1699 0.08809 0.08444 -0.0959 0.7486 0.0091 -9.750 -0.1661 0.08486 0.08123 -0.0975 0.7477 0.0101 -9.500 -0.1641 0.08125 0.07765 -0.0993 0.7468 0.0105 -9.250 -0.1636 0.07753 0.07396 -0.1011 0.7459 0.0097 -9.000 -0.1594 0.07303 0.06949 -0.1051 0.7448 0.0118 -8.750 -0.1599 0.06869 0.06518 -0.1083 0.7437 0.0119 -8.500 -0.1657 0.06378 0.06029 -0.1123 0.7425 0.0119 -8.250 -0.1746 0.05972 0.05620 -0.1140 0.7412 0.0119 -7.750 -0.1856 0.05306 0.04938 -0.1137 0.7388 0.0119 -6.750 -0.1878 0.03505 0.03060 -0.1095 0.7350 0.0075 -6.500 -0.1790 0.03146 0.02675 -0.1083 0.7341 0.0073 -6.250 -0.1657 0.02820 0.02320 -0.1071 0.7332 0.0071 -6.000 -0.1498 0.02495 0.01958 -0.1058 0.7321 0.0069 -5.750 -0.1309 0.02216 0.01642 -0.1047 0.7311 0.0068 -5.500 -0.1097 0.01959 0.01347 -0.1037 0.7300 0.0067 -5.250 -0.0861 0.01777 0.01133 -0.1031 0.7290 0.0068 -5.000 -0.0612 0.01637 0.00969 -0.1026 0.7281 0.0069 -4.750 -0.0358 0.01531 0.00844 -0.1023 0.7273 0.0071 -4.500 -0.0100 0.01453 0.00752 -0.1021 0.7265 0.0075 -4.250 0.0161 0.01394 0.00683 -0.1019 0.7257 0.0077 -4.000 0.0404 0.01302 0.00582 -0.1015 0.7250 0.0083 -3.750 0.0663 0.01256 0.00531 -0.1015 0.7242 0.0087 -3.500 0.0929 0.01225 0.00497 -0.1015 0.7235 0.0095 -3.250 0.1198 0.01201 0.00469 -0.1017 0.7227 0.0106 -3.000 0.1464 0.01168 0.00431 -0.1017 0.7218 0.0111 -2.750 0.1731 0.01139 0.00398 -0.1017 0.7208 0.0116 -2.500 0.2002 0.01114 0.00368 -0.1018 0.7199 0.0126 -2.250 0.2274 0.01092 0.00345 -0.1019 0.7190 0.0162 -2.000 0.2546 0.01069 0.00328 -0.1021 0.7180 0.0384 -1.750 0.2812 0.01034 0.00318 -0.1023 0.7170 0.1102 -1.500 0.3028 0.00876 0.00299 -0.1027 0.7159 0.5253 -1.250 0.3252 0.00826 0.00326 -0.1017 0.7148 0.7516 -1.000 0.3529 0.00843 0.00339 -0.1017 0.7138 0.7913 -0.750 0.3790 0.00861 0.00359 -0.1012 0.7130 0.8118 -0.500 0.4061 0.00873 0.00369 -0.1010 0.7122 0.8231 -0.250 0.4338 0.00883 0.00375 -0.1011 0.7114 0.8307 0.000 0.4616 0.00889 0.00377 -0.1012 0.7105 0.8356 0.250 0.4896 0.00893 0.00380 -0.1013 0.7097 0.8389 0.500 0.5183 0.00899 0.00381 -0.1017 0.7089 0.8414 0.750 0.5466 0.00904 0.00387 -0.1021 0.7079 0.8435 1.000 0.5750 0.00910 0.00393 -0.1026 0.7068 0.8454 1.250 0.6035 0.00915 0.00399 -0.1031 0.7054 0.8470 1.500 0.6315 0.00919 0.00404 -0.1034 0.7041 0.8481 1.750 0.6595 0.00924 0.00411 -0.1037 0.7028 0.8491 2.000 0.6877 0.00927 0.00417 -0.1041 0.7015 0.8502 2.250 0.7162 0.00928 0.00419 -0.1045 0.6998 0.8511 2.500 0.7449 0.00926 0.00418 -0.1049 0.6980 0.8521 2.750 0.7739 0.00925 0.00418 -0.1054 0.6964 0.8532 3.000 0.8026 0.00926 0.00421 -0.1058 0.6948 0.8543 3.250 0.8295 0.00929 0.00431 -0.1060 0.6916 0.8554 3.500 0.8572 0.00926 0.00433 -0.1062 0.6881 0.8564 3.750 0.8859 0.00918 0.00430 -0.1066 0.6846 0.8574 4.000 0.9146 0.00910 0.00424 -0.1070 0.6810 0.8585 4.250 0.9410 0.00907 0.00430 -0.1070 0.6746 0.8598 4.500 0.9693 0.00893 0.00416 -0.1072 0.6679 0.8608 4.750 0.9953 0.00886 0.00418 -0.1071 0.6568 0.8617 5.000 1.0212 0.00878 0.00414 -0.1068 0.6424 0.8626 5.250 1.0456 0.00875 0.00411 -0.1063 0.6171 0.8636 5.500 1.0573 0.00921 0.00418 -0.1033 0.5382 0.8651 5.750 1.0548 0.01044 0.00493 -0.0981 0.4505 0.8673 6.000 1.0539 0.01152 0.00570 -0.0933 0.3850 0.8701 6.250 1.0528 0.01238 0.00638 -0.0885 0.3390 0.8727 6.500 1.0498 0.01333 0.00715 -0.0835 0.2976 0.8753 6.750 1.0464 0.01443 0.00810 -0.0789 0.2573 0.8780 7.000 1.0448 0.01568 0.00917 -0.0750 0.2165 0.8810 7.250 1.0451 0.01700 0.01031 -0.0717 0.1747 0.8840 7.500 1.0489 0.01825 0.01139 -0.0690 0.1382 0.8870 7.750 1.0553 0.01940 0.01240 -0.0667 0.1079 0.8899 8.000 1.0628 0.02047 0.01339 -0.0646 0.0827 0.8932 8.250 1.0705 0.02160 0.01441 -0.0625 0.0584 0.8967 8.500 1.0805 0.02263 0.01539 -0.0608 0.0429 0.9003 8.750 1.0918 0.02359 0.01632 -0.0593 0.0317 0.9041 9.000 1.1027 0.02454 0.01726 -0.0577 0.0230 0.9089 9.250 1.1161 0.02536 0.01812 -0.0564 0.0192 0.9146 9.500 1.1277 0.02626 0.01905 -0.0549 0.0154 0.9227 9.750 1.1424 0.02706 0.01995 -0.0538 0.0130 0.9362 10.000 1.1577 0.02808 0.02101 -0.0534 0.0098 0.9925 10.500 1.1819 0.03028 0.02330 -0.0512 0.0062 1.0000 10.750 1.1944 0.03140 0.02449 -0.0501 0.0057 1.0000 11.000 1.2063 0.03259 0.02576 -0.0491 0.0050 1.0000 11.250 1.2178 0.03384 0.02708 -0.0480 0.0045 1.0000 11.500 1.2284 0.03517 0.02848 -0.0470 0.0043 1.0000 11.750 1.2378 0.03666 0.03004 -0.0459 0.0040 1.0000 12.000 1.2453 0.03834 0.03182 -0.0447 0.0038 1.0000 12.250 1.2517 0.04017 0.03376 -0.0434 0.0037 1.0000 12.500 1.2621 0.04164 0.03532 -0.0426 0.0035 1.0000 12.750 1.2709 0.04330 0.03708 -0.0417 0.0034 1.0000 13.000 1.2797 0.04499 0.03890 -0.0409 0.0032 1.0000 13.250 1.2878 0.04680 0.04081 -0.0401 0.0031 1.0000 13.500 1.2943 0.04878 0.04292 -0.0393 0.0030 1.0000 13.750 1.3006 0.05085 0.04510 -0.0385 0.0029 1.0000 14.000 1.3055 0.05313 0.04750 -0.0378 0.0028 1.0000 14.250 1.3106 0.05543 0.04993 -0.0372 0.0027 1.0000 14.500 1.3150 0.05787 0.05249 -0.0367 0.0027 1.0000 14.750 1.3177 0.06055 0.05531 -0.0362 0.0026 1.0000 15.000 1.3197 0.06340 0.05831 -0.0359 0.0026 1.0000 15.250 1.3216 0.06633 0.06138 -0.0357 0.0025 1.0000 15.500 1.3215 0.06961 0.06480 -0.0356 0.0025 1.0000 15.750 1.3209 0.07302 0.06837 -0.0358 0.0024 1.0000 16.000 1.3192 0.07668 0.07218 -0.0361 0.0024 1.0000 16.250 1.3160 0.08068 0.07633 -0.0367 0.0023 1.0000 16.500 1.3108 0.08513 0.08097 -0.0375 0.0023 1.0000 16.750 1.3050 0.08979 0.08579 -0.0386 0.0023 1.0000 17.000 1.2969 0.09497 0.09114 -0.0402 0.0022 1.0000 17.250 1.2878 0.10054 0.09689 -0.0420 0.0022 1.0000 17.500 1.2773 0.10654 0.10307 -0.0444 0.0022 1.0000 17.750 1.2659 0.11294 0.10965 -0.0472 0.0022 1.0000 18.000 1.2521 0.12004 0.11694 -0.0506 0.0022 1.0000 18.250 1.2386 0.12734 0.12442 -0.0545 0.0021 1.0000 18.500 1.2244 0.13512 0.13237 -0.0589 0.0021 1.0000 18.750 1.2103 0.14319 0.14061 -0.0636 0.0022 1.0000 19.000 1.1957 0.15174 0.14932 -0.0689 0.0022 1.0000