XFOIL Version 6.96 Calculated polar for: RAE 104 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.000 -0.7922 0.06179 0.05998 -0.0378 1.0000 0.0070 -11.750 -0.8221 0.05450 0.05254 -0.0421 1.0000 0.0067 -11.500 -0.8529 0.04824 0.04606 -0.0432 1.0000 0.0068 -11.250 -0.8859 0.04314 0.04074 -0.0416 1.0000 0.0065 -11.000 -0.9094 0.03936 0.03671 -0.0380 1.0000 0.0066 -10.750 -0.9379 0.03562 0.03270 -0.0319 1.0000 0.0065 -10.500 -0.9511 0.03250 0.02928 -0.0271 1.0000 0.0067 -10.250 -0.9548 0.02977 0.02624 -0.0232 1.0000 0.0068 -10.000 -0.9513 0.02765 0.02387 -0.0200 1.0000 0.0069 -9.750 -0.9409 0.02633 0.02236 -0.0176 1.0000 0.0071 -9.500 -0.9276 0.02535 0.02123 -0.0155 1.0000 0.0072 -9.250 -0.9232 0.02270 0.01825 -0.0121 1.0000 0.0074 -9.000 -0.9169 0.02010 0.01535 -0.0088 1.0000 0.0076 -8.750 -0.9053 0.01854 0.01361 -0.0062 1.0000 0.0078 -8.500 -0.8911 0.01757 0.01255 -0.0039 1.0000 0.0081 -8.250 -0.8764 0.01683 0.01174 -0.0017 1.0000 0.0083 -8.000 -0.8624 0.01616 0.01101 0.0007 1.0000 0.0086 -7.750 -0.8325 0.01539 0.01015 -0.0003 0.9985 0.0090 -7.500 -0.8001 0.01475 0.00945 -0.0017 0.9962 0.0096 -7.250 -0.7681 0.01415 0.00878 -0.0031 0.9936 0.0103 -7.000 -0.7368 0.01370 0.00828 -0.0041 0.9901 0.0107 -6.750 -0.7087 0.01238 0.00681 -0.0048 0.9860 0.0115 -6.500 -0.6767 0.01164 0.00602 -0.0061 0.9833 0.0128 -6.250 -0.6470 0.01122 0.00557 -0.0069 0.9775 0.0139 -6.000 -0.6133 0.01083 0.00515 -0.0084 0.9734 0.0152 -5.750 -0.5797 0.01031 0.00457 -0.0100 0.9689 0.0168 -5.500 -0.5491 0.00982 0.00407 -0.0109 0.9601 0.0201 -5.250 -0.5167 0.00955 0.00376 -0.0121 0.9514 0.0225 -5.000 -0.4882 0.00913 0.00330 -0.0124 0.9396 0.0283 -4.750 -0.4613 0.00890 0.00303 -0.0123 0.9268 0.0341 -4.500 -0.4369 0.00861 0.00276 -0.0117 0.9138 0.0473 -4.250 -0.4131 0.00833 0.00252 -0.0110 0.9016 0.0677 -4.000 -0.3900 0.00800 0.00230 -0.0102 0.8905 0.1023 -3.750 -0.3681 0.00758 0.00208 -0.0092 0.8806 0.1599 -3.500 -0.3468 0.00712 0.00186 -0.0081 0.8714 0.2336 -3.250 -0.3269 0.00654 0.00163 -0.0069 0.8627 0.3347 -3.000 -0.3083 0.00590 0.00141 -0.0053 0.8550 0.4553 -2.750 -0.2905 0.00527 0.00123 -0.0035 0.8472 0.5794 -2.500 -0.2681 0.00505 0.00120 -0.0023 0.8411 0.6547 -2.250 -0.2423 0.00497 0.00117 -0.0019 0.8352 0.6832 -2.000 -0.2159 0.00495 0.00114 -0.0016 0.8297 0.7018 -1.750 -0.1892 0.00493 0.00113 -0.0013 0.8244 0.7167 -1.500 -0.1624 0.00491 0.00111 -0.0011 0.8190 0.7299 -1.250 -0.1354 0.00493 0.00109 -0.0009 0.8139 0.7411 -1.000 -0.1084 0.00490 0.00110 -0.0007 0.8084 0.7511 -0.750 -0.0813 0.00490 0.00108 -0.0005 0.8025 0.7598 -0.500 -0.0542 0.00492 0.00108 -0.0004 0.7966 0.7684 -0.250 -0.0271 0.00490 0.00108 -0.0002 0.7898 0.7758 0.000 0.0000 0.00493 0.00108 0.0000 0.7832 0.7831 0.250 0.0271 0.00490 0.00108 0.0002 0.7757 0.7898 0.500 0.0542 0.00492 0.00108 0.0004 0.7684 0.7965 0.750 0.0813 0.00490 0.00109 0.0005 0.7599 0.8025 1.000 0.1084 0.00490 0.00110 0.0007 0.7509 0.8084 1.250 0.1354 0.00493 0.00109 0.0009 0.7411 0.8139 1.500 0.1624 0.00491 0.00111 0.0011 0.7300 0.8190 1.750 0.1892 0.00493 0.00113 0.0013 0.7167 0.8244 2.000 0.2159 0.00495 0.00114 0.0016 0.7017 0.8297 2.250 0.2423 0.00497 0.00117 0.0019 0.6834 0.8352 2.500 0.2681 0.00505 0.00120 0.0023 0.6542 0.8411 2.750 0.2906 0.00527 0.00123 0.0035 0.5804 0.8472 3.000 0.3083 0.00590 0.00141 0.0053 0.4550 0.8550 3.250 0.3268 0.00655 0.00163 0.0069 0.3336 0.8627 3.500 0.3468 0.00712 0.00186 0.0081 0.2339 0.8714 3.750 0.3681 0.00758 0.00208 0.0092 0.1601 0.8806 4.000 0.3901 0.00800 0.00230 0.0102 0.1028 0.8905 4.250 0.4131 0.00833 0.00252 0.0110 0.0676 0.9016 4.500 0.4368 0.00862 0.00276 0.0117 0.0469 0.9138 4.750 0.4614 0.00889 0.00302 0.0123 0.0345 0.9269 5.000 0.4882 0.00913 0.00330 0.0124 0.0285 0.9397 5.250 0.5166 0.00957 0.00377 0.0121 0.0226 0.9515 5.500 0.5491 0.00981 0.00404 0.0109 0.0202 0.9602 5.750 0.5799 0.01027 0.00452 0.0099 0.0168 0.9687 6.000 0.6133 0.01081 0.00513 0.0084 0.0152 0.9733 6.250 0.6469 0.01122 0.00558 0.0069 0.0140 0.9775 6.500 0.6766 0.01164 0.00602 0.0062 0.0128 0.9834 6.750 0.7086 0.01237 0.00681 0.0048 0.0115 0.9860 7.000 0.7368 0.01367 0.00825 0.0041 0.0107 0.9901 7.250 0.7679 0.01417 0.00881 0.0031 0.0102 0.9936 7.500 0.8000 0.01476 0.00946 0.0018 0.0096 0.9961 7.750 0.8324 0.01540 0.01016 0.0003 0.0089 0.9984 8.000 0.8623 0.01619 0.01105 -0.0007 0.0086 1.0000 8.250 0.8764 0.01685 0.01176 0.0017 0.0083 1.0000 8.500 0.8912 0.01759 0.01257 0.0039 0.0081 1.0000 8.750 0.9051 0.01861 0.01370 0.0063 0.0079 1.0000 9.000 0.9165 0.02019 0.01545 0.0089 0.0076 1.0000 9.250 0.9253 0.02233 0.01783 0.0118 0.0075 1.0000 9.500 0.9220 0.02631 0.02228 0.0162 0.0073 1.0000 9.750 0.9348 0.02727 0.02339 0.0183 0.0072 1.0000 10.000 0.9489 0.02799 0.02424 0.0203 0.0070 1.0000 10.250 0.9456 0.03092 0.02749 0.0242 0.0070 1.0000 10.500 0.9491 0.03272 0.02952 0.0273 0.0068 1.0000 10.750 0.9367 0.03572 0.03280 0.0321 0.0066 1.0000 11.000 0.9133 0.03894 0.03627 0.0376 0.0067 1.0000 11.250 0.8892 0.04276 0.04033 0.0414 0.0066 1.0000 11.500 0.8534 0.04842 0.04627 0.0432 0.0066 1.0000 11.750 0.8247 0.05431 0.05236 0.0421 0.0066 1.0000 12.000 0.7928 0.06212 0.06034 0.0376 0.0068 1.0000