XFOIL Version 6.96 Calculated polar for: USA 27 mod. AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -10.250 -0.2066 0.09177 0.08926 -0.0760 0.9795 0.0218 -10.000 -0.2009 0.08699 0.08448 -0.0797 0.9766 0.0219 -9.500 -0.2039 0.07333 0.07082 -0.0914 0.9692 0.0224 -9.000 -0.3000 0.03821 0.03487 -0.1164 0.9371 0.0223 -8.750 -0.2932 0.03442 0.03079 -0.1168 0.9315 0.0224 -8.500 -0.2864 0.03204 0.02820 -0.1151 0.9232 0.0225 -8.250 -0.2709 0.02990 0.02585 -0.1147 0.9178 0.0226 -8.000 -0.2545 0.02830 0.02408 -0.1137 0.9106 0.0227 -7.750 -0.2352 0.02682 0.02244 -0.1131 0.9026 0.0229 -7.500 -0.2156 0.02560 0.02107 -0.1123 0.8935 0.0231 -7.250 -0.1938 0.02436 0.01964 -0.1118 0.8843 0.0234 -7.000 -0.1755 0.02312 0.01819 -0.1105 0.8741 0.0237 -6.750 -0.1552 0.02176 0.01657 -0.1094 0.8652 0.0239 -6.500 -0.1350 0.02058 0.01516 -0.1082 0.8555 0.0240 -6.250 -0.1133 0.01953 0.01390 -0.1072 0.8467 0.0242 -6.000 -0.0908 0.01859 0.01275 -0.1063 0.8365 0.0244 -5.750 -0.0684 0.01777 0.01173 -0.1052 0.8250 0.0246 -5.500 -0.0451 0.01703 0.01080 -0.1043 0.8134 0.0247 -5.250 -0.0214 0.01636 0.00996 -0.1034 0.8023 0.0249 -5.000 0.0023 0.01576 0.00922 -0.1026 0.7909 0.0251 -4.750 0.0262 0.01522 0.00854 -0.1017 0.7776 0.0252 -4.500 0.0499 0.01476 0.00794 -0.1007 0.7604 0.0254 -4.250 0.0728 0.01444 0.00744 -0.0996 0.7377 0.0257 -4.000 0.0946 0.01422 0.00702 -0.0981 0.7076 0.0260 -3.750 0.1154 0.01402 0.00662 -0.0965 0.6786 0.0261 -3.500 0.1368 0.01381 0.00624 -0.0951 0.6566 0.0262 -3.250 0.1587 0.01336 0.00570 -0.0938 0.6402 0.0264 -3.000 0.1812 0.01300 0.00527 -0.0927 0.6265 0.0266 -2.750 0.2039 0.01273 0.00494 -0.0916 0.6143 0.0269 -2.250 0.2503 0.01231 0.00442 -0.0896 0.5910 0.0274 -2.000 0.2737 0.01214 0.00420 -0.0886 0.5804 0.0277 -1.750 0.2971 0.01199 0.00401 -0.0877 0.5688 0.0281 -1.500 0.3208 0.01185 0.00383 -0.0868 0.5566 0.0284 -1.250 0.3439 0.01174 0.00367 -0.0857 0.5429 0.0287 -1.000 0.3668 0.01167 0.00353 -0.0846 0.5268 0.0291 -0.750 0.3890 0.01163 0.00341 -0.0834 0.5074 0.0295 -0.500 0.4104 0.01165 0.00333 -0.0821 0.4855 0.0301 -0.250 0.4319 0.01171 0.00328 -0.0807 0.4649 0.0306 0.000 0.4535 0.01172 0.00319 -0.0795 0.4475 0.0312 0.250 0.4753 0.01175 0.00314 -0.0782 0.4314 0.0318 0.750 0.5206 0.01187 0.00310 -0.0761 0.4051 0.0333 1.000 0.5439 0.01193 0.00310 -0.0752 0.3962 0.0342 1.250 0.5678 0.01197 0.00310 -0.0744 0.3888 0.0353 1.500 0.5911 0.01204 0.00313 -0.0735 0.3826 0.0369 1.750 0.6154 0.01206 0.00316 -0.0727 0.3771 0.0407 2.000 0.6360 0.01175 0.00324 -0.0715 0.3717 0.1870 2.250 0.6586 0.01176 0.00335 -0.0705 0.3664 0.2342 2.500 0.6823 0.01178 0.00345 -0.0697 0.3618 0.2680 2.750 0.7055 0.01182 0.00356 -0.0689 0.3563 0.3003 3.000 0.7277 0.01191 0.00367 -0.0678 0.3505 0.3265 3.250 0.7506 0.01193 0.00377 -0.0669 0.3454 0.3613 3.500 0.7653 0.01120 0.00386 -0.0646 0.3411 0.6854 4.000 0.8815 0.01153 0.00483 -0.0777 0.3306 0.9859 4.250 0.9229 0.01174 0.00503 -0.0809 0.3268 0.9914 4.500 0.9615 0.01195 0.00521 -0.0835 0.3227 0.9949 4.750 0.9992 0.01218 0.00539 -0.0860 0.3176 0.9977 5.000 1.0357 0.01239 0.00558 -0.0881 0.3128 1.0000 5.250 1.0528 0.01251 0.00571 -0.0861 0.3097 1.0000 5.500 1.0677 0.01264 0.00583 -0.0835 0.3065 1.0000 5.750 1.0805 0.01278 0.00597 -0.0805 0.3030 1.0000 6.000 1.0928 0.01294 0.00612 -0.0774 0.2995 1.0000 6.250 1.1078 0.01308 0.00627 -0.0749 0.2966 1.0000 6.500 1.1235 0.01322 0.00642 -0.0726 0.2922 1.0000 6.750 1.1383 0.01340 0.00660 -0.0701 0.2866 1.0000 7.000 1.1533 0.01362 0.00679 -0.0678 0.2808 1.0000 7.250 1.1697 0.01382 0.00699 -0.0657 0.2734 1.0000 7.500 1.1846 0.01409 0.00723 -0.0634 0.2641 1.0000 7.750 1.1994 0.01439 0.00748 -0.0612 0.2529 1.0000 8.000 1.2150 0.01470 0.00776 -0.0591 0.2413 1.0000 8.250 1.2285 0.01514 0.00811 -0.0568 0.2245 1.0000 8.500 1.2397 0.01573 0.00859 -0.0542 0.2021 1.0000 8.750 1.2512 0.01636 0.00911 -0.0517 0.1857 1.0000 9.000 1.2647 0.01693 0.00963 -0.0496 0.1762 1.0000 9.250 1.2779 0.01754 0.01020 -0.0476 0.1679 1.0000 9.500 1.2918 0.01812 0.01078 -0.0457 0.1597 1.0000 9.750 1.3040 0.01883 0.01145 -0.0436 0.1518 1.0000 10.000 1.3196 0.01937 0.01200 -0.0421 0.1451 1.0000 10.250 1.3315 0.02012 0.01272 -0.0401 0.1365 1.0000 10.500 1.3434 0.02091 0.01346 -0.0383 0.1244 1.0000 10.750 1.3420 0.02253 0.01484 -0.0349 0.0891 1.0000 11.000 1.3272 0.02509 0.01717 -0.0303 0.0474 1.0000 11.250 1.3178 0.02747 0.01946 -0.0267 0.0204 1.0000 11.500 1.3252 0.02878 0.02081 -0.0250 0.0177 1.0000 11.750 1.3340 0.03002 0.02212 -0.0236 0.0165 1.0000 12.000 1.3417 0.03139 0.02356 -0.0222 0.0157 1.0000 12.250 1.3480 0.03292 0.02517 -0.0208 0.0149 1.0000 12.500 1.3532 0.03461 0.02694 -0.0194 0.0143 1.0000 12.750 1.3599 0.03624 0.02866 -0.0184 0.0139 1.0000 13.000 1.3653 0.03804 0.03054 -0.0174 0.0135 1.0000 13.250 1.3696 0.04003 0.03263 -0.0165 0.0131 1.0000 13.500 1.3727 0.04224 0.03493 -0.0158 0.0127 1.0000 13.750 1.3745 0.04468 0.03745 -0.0152 0.0123 1.0000 14.000 1.3746 0.04739 0.04026 -0.0148 0.0120 1.0000 14.250 1.3723 0.05046 0.04343 -0.0145 0.0117 1.0000 14.500 1.3674 0.05393 0.04700 -0.0143 0.0114 1.0000 14.750 1.3619 0.05756 0.05075 -0.0144 0.0112 1.0000 15.000 1.3583 0.06101 0.05431 -0.0145 0.0111 1.0000 15.250 1.3533 0.06473 0.05814 -0.0148 0.0109 1.0000 15.500 1.3471 0.06869 0.06221 -0.0152 0.0108 1.0000 15.750 1.3396 0.07291 0.06655 -0.0158 0.0107 1.0000 16.000 1.3310 0.07735 0.07110 -0.0166 0.0105 1.0000 16.250 1.3218 0.08195 0.07581 -0.0175 0.0104 1.0000 16.500 1.3120 0.08672 0.08070 -0.0185 0.0103 1.0000 16.750 1.3018 0.09160 0.08569 -0.0196 0.0102 1.0000 17.000 1.2912 0.09654 0.09074 -0.0208 0.0101 1.0000