XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY RC-10(N)1 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.6850 0.08197 0.08004 0.0047 0.8040 0.0051 -9.250 -0.7119 0.07212 0.07010 -0.0052 0.7949 0.0051 -9.000 -0.7233 0.06629 0.06413 -0.0075 0.7878 0.0051 -8.750 -0.7251 0.06143 0.05914 -0.0087 0.7819 0.0052 -8.500 -0.7232 0.05680 0.05435 -0.0092 0.7761 0.0053 -8.250 -0.7172 0.05263 0.05000 -0.0092 0.7712 0.0054 -8.000 -0.7092 0.04840 0.04559 -0.0089 0.7663 0.0055 -7.750 -0.6996 0.04408 0.04104 -0.0082 0.7615 0.0057 -7.250 -0.7070 0.02148 0.01674 -0.0006 0.7545 0.0075 -7.000 -0.6884 0.01857 0.01338 0.0007 0.7501 0.0078 -6.750 -0.6661 0.01691 0.01147 0.0015 0.7458 0.0081 -6.500 -0.6411 0.01614 0.01058 0.0018 0.7417 0.0083 -6.250 -0.6155 0.01553 0.00988 0.0021 0.7374 0.0085 -6.000 -0.5898 0.01494 0.00919 0.0023 0.7332 0.0087 -5.750 -0.5637 0.01444 0.00860 0.0026 0.7293 0.0090 -5.500 -0.5374 0.01396 0.00805 0.0028 0.7251 0.0094 -5.250 -0.5115 0.01334 0.00733 0.0031 0.7209 0.0097 -5.000 -0.4856 0.01274 0.00662 0.0034 0.7168 0.0100 -4.750 -0.4594 0.01220 0.00601 0.0037 0.7129 0.0103 -4.500 -0.4332 0.01173 0.00546 0.0039 0.7086 0.0105 -4.250 -0.4069 0.01129 0.00495 0.0042 0.7045 0.0107 -4.000 -0.3805 0.01090 0.00450 0.0044 0.7006 0.0108 -3.750 -0.3538 0.01053 0.00408 0.0046 0.6964 0.0109 -3.500 -0.3271 0.01019 0.00370 0.0048 0.6921 0.0110 -3.250 -0.3013 0.00970 0.00311 0.0052 0.6880 0.0114 -3.000 -0.2744 0.00938 0.00276 0.0054 0.6840 0.0120 -2.750 -0.2471 0.00912 0.00247 0.0055 0.6795 0.0123 -2.500 -0.2197 0.00892 0.00223 0.0055 0.6752 0.0128 -2.250 -0.1921 0.00874 0.00202 0.0056 0.6710 0.0136 -2.000 -0.1643 0.00858 0.00184 0.0056 0.6659 0.0145 -1.750 -0.1364 0.00845 0.00168 0.0055 0.6607 0.0156 -1.500 -0.1086 0.00829 0.00152 0.0055 0.6556 0.0190 -1.250 -0.0806 0.00818 0.00141 0.0055 0.6501 0.0221 -1.000 -0.0527 0.00807 0.00131 0.0054 0.6444 0.0294 -0.750 -0.0246 0.00796 0.00123 0.0054 0.6376 0.0395 -0.250 0.0200 0.00601 0.00088 0.0066 0.6245 0.5484 0.000 0.0457 0.00573 0.00086 0.0070 0.6174 0.6354 0.250 0.0726 0.00559 0.00083 0.0071 0.6102 0.6781 0.750 0.1209 0.00499 0.00080 0.0088 0.5958 0.8337 1.000 0.1466 0.00490 0.00085 0.0095 0.5886 0.8949 1.250 0.1749 0.00490 0.00087 0.0094 0.5814 0.9128 1.500 0.2036 0.00494 0.00089 0.0093 0.5731 0.9263 1.750 0.2333 0.00498 0.00092 0.0089 0.5639 0.9372 2.000 0.2632 0.00503 0.00096 0.0084 0.5546 0.9462 2.250 0.2947 0.00514 0.00101 0.0076 0.5349 0.9538 2.500 0.3259 0.00532 0.00107 0.0067 0.5031 0.9608 2.750 0.3582 0.00549 0.00115 0.0056 0.4751 0.9658 3.000 0.3885 0.00570 0.00124 0.0049 0.4414 0.9710 3.250 0.4195 0.00602 0.00137 0.0039 0.3944 0.9746 3.500 0.4506 0.00634 0.00153 0.0028 0.3511 0.9777 3.750 0.4807 0.00661 0.00168 0.0021 0.3195 0.9812 4.000 0.5091 0.00700 0.00188 0.0016 0.2730 0.9848 4.250 0.5402 0.00749 0.00211 0.0004 0.2137 0.9865 4.500 0.5709 0.00787 0.00234 -0.0007 0.1745 0.9883 4.750 0.6011 0.00827 0.00259 -0.0016 0.1385 0.9905 5.000 0.6309 0.00865 0.00283 -0.0025 0.1098 0.9927 5.250 0.6609 0.00893 0.00305 -0.0033 0.0936 0.9946 5.500 0.6922 0.00923 0.00329 -0.0044 0.0773 0.9957 5.750 0.7229 0.00954 0.00354 -0.0054 0.0633 0.9969 6.000 0.7536 0.00984 0.00379 -0.0064 0.0526 0.9982 6.250 0.7845 0.01014 0.00406 -0.0074 0.0447 0.9994 6.500 0.8129 0.01044 0.00434 -0.0079 0.0384 1.0000 6.750 0.8366 0.01071 0.00461 -0.0074 0.0336 1.0000 7.000 0.8600 0.01102 0.00490 -0.0068 0.0292 1.0000 7.250 0.8834 0.01133 0.00521 -0.0062 0.0254 1.0000 7.500 0.9069 0.01162 0.00553 -0.0056 0.0232 1.0000 7.750 0.9298 0.01197 0.00587 -0.0050 0.0200 1.0000 8.000 0.9528 0.01233 0.00624 -0.0043 0.0177 1.0000 8.250 0.9759 0.01265 0.00660 -0.0037 0.0165 1.0000 8.500 0.9986 0.01302 0.00698 -0.0031 0.0150 1.0000 8.750 1.0208 0.01345 0.00742 -0.0024 0.0133 1.0000 9.000 1.0427 0.01389 0.00790 -0.0016 0.0121 1.0000 9.250 1.0651 0.01427 0.00832 -0.0010 0.0114 1.0000 9.500 1.0870 0.01469 0.00879 -0.0003 0.0106 1.0000 9.750 1.1084 0.01516 0.00928 0.0005 0.0098 1.0000 10.000 1.1293 0.01570 0.00984 0.0012 0.0089 1.0000 10.250 1.1495 0.01631 0.01050 0.0021 0.0081 1.0000 10.500 1.1709 0.01677 0.01104 0.0027 0.0078 1.0000 10.750 1.1918 0.01729 0.01161 0.0034 0.0073 1.0000 11.000 1.2120 0.01785 0.01223 0.0041 0.0068 1.0000 11.250 1.2316 0.01847 0.01288 0.0049 0.0063 1.0000 11.500 1.2501 0.01917 0.01362 0.0057 0.0057 1.0000 11.750 1.2673 0.01996 0.01449 0.0067 0.0053 1.0000 12.000 1.2853 0.02063 0.01522 0.0075 0.0051 1.0000 12.250 1.3022 0.02136 0.01604 0.0084 0.0048 1.0000 12.500 1.3170 0.02214 0.01690 0.0096 0.0046 1.0000 12.750 1.3287 0.02301 0.01785 0.0111 0.0043 1.0000 13.000 1.3396 0.02402 0.01893 0.0124 0.0041 1.0000 13.250 1.3500 0.02517 0.02015 0.0134 0.0039 1.0000 13.500 1.3595 0.02649 0.02155 0.0142 0.0037 1.0000 13.750 1.3673 0.02804 0.02319 0.0149 0.0035 1.0000 14.000 1.3722 0.02992 0.02519 0.0156 0.0033 1.0000 14.250 1.3799 0.03157 0.02694 0.0160 0.0033 1.0000 14.500 1.3861 0.03339 0.02887 0.0163 0.0032 1.0000 14.750 1.3909 0.03541 0.03099 0.0166 0.0031 1.0000 15.000 1.3943 0.03762 0.03331 0.0167 0.0030 1.0000 15.250 1.3960 0.04006 0.03588 0.0167 0.0030 1.0000 15.500 1.3963 0.04272 0.03866 0.0166 0.0029 1.0000 15.750 1.3948 0.04567 0.04173 0.0162 0.0028 1.0000 16.000 1.3913 0.04893 0.04512 0.0156 0.0027 1.0000 16.250 1.3861 0.05256 0.04886 0.0147 0.0027 1.0000 16.500 1.3787 0.05658 0.05301 0.0135 0.0026 1.0000 16.750 1.3696 0.06107 0.05763 0.0120 0.0026 1.0000 17.000 1.3583 0.06618 0.06287 0.0099 0.0026 1.0000 17.250 1.3441 0.07199 0.06883 0.0073 0.0025 1.0000 17.500 1.3267 0.07867 0.07565 0.0041 0.0025 1.0000 17.750 1.3049 0.08637 0.08350 0.0003 0.0025 1.0000 18.000 1.2784 0.09529 0.09258 -0.0042 0.0025 1.0000 18.250 1.2443 0.10600 0.10346 -0.0096 0.0026 1.0000 18.500 1.2027 0.11861 0.11625 -0.0160 0.0027 1.0000 18.750 1.1533 0.13340 0.13121 -0.0234 0.0028 1.0000 19.000 1.1030 0.14922 0.14717 -0.0315 0.0029 1.0000