XFOIL Version 6.96 Calculated polar for: AH 85-L-120/17 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 ------ -------- --------- --------- -------- -------- -------- -14.250 -0.4327 0.11381 0.11163 -0.0300 0.9357 0.0068 -14.000 -0.4457 0.10857 0.10639 -0.0327 0.9362 0.0067 -13.500 -0.8066 0.07759 0.07526 -0.0304 1.0000 0.0051 -13.250 -0.8120 0.07176 0.06932 -0.0349 1.0000 0.0052 -13.000 -0.6875 0.10398 0.10189 -0.0181 1.0000 0.0061 -12.500 -0.8831 0.05066 0.04755 -0.0447 0.9693 0.0052 -12.250 -0.9044 0.04350 0.03996 -0.0483 0.9528 0.0055 -12.000 -0.9076 0.03848 0.03449 -0.0503 0.9418 0.0054 -11.750 -0.8992 0.03556 0.03128 -0.0516 0.9337 0.0055 -11.500 -0.8798 0.03470 0.03033 -0.0529 0.9275 0.0058 -11.250 -0.8707 0.03264 0.02805 -0.0526 0.9212 0.0059 -11.000 -0.8627 0.03011 0.02519 -0.0518 0.9160 0.0060 -10.750 -0.8480 0.02923 0.02418 -0.0511 0.9116 0.0064 -10.500 -0.8363 0.02736 0.02206 -0.0499 0.9074 0.0064 -10.250 -0.8219 0.02561 0.02005 -0.0488 0.9037 0.0066 -10.000 -0.8051 0.02424 0.01847 -0.0479 0.9008 0.0069 -9.750 -0.7884 0.02286 0.01691 -0.0468 0.8979 0.0068 -9.500 -0.7703 0.02193 0.01581 -0.0458 0.8952 0.0073 -9.250 -0.7511 0.02134 0.01509 -0.0449 0.8926 0.0079 -9.000 -0.7321 0.02015 0.01377 -0.0440 0.8903 0.0078 -8.750 -0.7115 0.01970 0.01319 -0.0431 0.8879 0.0082 -8.500 -0.6955 0.01830 0.01166 -0.0417 0.8856 0.0086 -8.250 -0.6798 0.01744 0.01074 -0.0400 0.8830 0.0091 -8.000 -0.6629 0.01676 0.00999 -0.0385 0.8807 0.0093 -7.750 -0.6446 0.01628 0.00945 -0.0371 0.8785 0.0099 -7.500 -0.6281 0.01570 0.00878 -0.0353 0.8762 0.0101 -7.250 -0.6113 0.01518 0.00818 -0.0335 0.8741 0.0106 -7.000 -0.5931 0.01477 0.00771 -0.0320 0.8720 0.0112 -6.750 -0.5746 0.01435 0.00724 -0.0305 0.8699 0.0117 -6.500 -0.5538 0.01407 0.00691 -0.0295 0.8679 0.0125 -6.250 -0.5377 0.01342 0.00620 -0.0275 0.8656 0.0142 -6.000 -0.5174 0.01307 0.00580 -0.0263 0.8635 0.0156 -5.750 -0.4962 0.01276 0.00544 -0.0252 0.8617 0.0171 -5.500 -0.4745 0.01247 0.00510 -0.0243 0.8600 0.0192 -5.250 -0.4538 0.01213 0.00476 -0.0231 0.8582 0.0250 -5.000 -0.4320 0.01188 0.00450 -0.0221 0.8561 0.0298 -4.750 -0.4116 0.01153 0.00421 -0.0210 0.8540 0.0466 -4.500 -0.3938 0.01101 0.00391 -0.0194 0.8517 0.0931 -4.250 -0.3775 0.01041 0.00362 -0.0175 0.8494 0.1628 -4.000 -0.3601 0.00988 0.00335 -0.0159 0.8474 0.2314 -3.750 -0.3438 0.00931 0.00308 -0.0140 0.8455 0.3117 -3.500 -0.3330 0.00854 0.00279 -0.0111 0.8430 0.4273 -3.250 -0.3264 0.00771 0.00254 -0.0071 0.8398 0.5620 -3.000 -0.3133 0.00722 0.00247 -0.0041 0.8371 0.6562 -2.750 -0.2907 0.00710 0.00247 -0.0029 0.8349 0.6976 -2.500 -0.2658 0.00708 0.00250 -0.0023 0.8330 0.7260 -2.250 -0.2395 0.00709 0.00249 -0.0019 0.8311 0.7428 -2.000 -0.2137 0.00712 0.00251 -0.0015 0.8288 0.7559 -1.750 -0.1879 0.00716 0.00256 -0.0011 0.8259 0.7679 -1.500 -0.1617 0.00720 0.00259 -0.0007 0.8231 0.7779 -1.250 -0.1359 0.00724 0.00259 -0.0003 0.8205 0.7876 -1.000 -0.1080 0.00728 0.00263 -0.0004 0.8184 0.7926 -0.750 -0.0804 0.00730 0.00262 -0.0004 0.8165 0.7969 -0.500 -0.0548 0.00731 0.00261 0.0000 0.8133 0.8015 -0.250 -0.0276 0.00731 0.00263 0.0000 0.8102 0.8042 0.000 0.0000 0.00732 0.00264 0.0000 0.8071 0.8070 0.250 0.0276 0.00731 0.00263 0.0000 0.8042 0.8101 0.500 0.0548 0.00731 0.00261 0.0000 0.8015 0.8134 0.750 0.0804 0.00730 0.00261 0.0004 0.7968 0.8164 1.000 0.1080 0.00728 0.00262 0.0004 0.7923 0.8184 1.250 0.1360 0.00725 0.00259 0.0003 0.7877 0.8206 1.500 0.1617 0.00720 0.00259 0.0008 0.7778 0.8231 1.750 0.1880 0.00716 0.00256 0.0011 0.7680 0.8258 2.000 0.2139 0.00712 0.00252 0.0015 0.7569 0.8287 2.250 0.2396 0.00709 0.00249 0.0019 0.7430 0.8312 2.500 0.2658 0.00708 0.00250 0.0023 0.7261 0.8329 2.750 0.2907 0.00710 0.00247 0.0029 0.6977 0.8348 3.000 0.3138 0.00721 0.00247 0.0040 0.6609 0.8371 3.250 0.3284 0.00764 0.00254 0.0067 0.5746 0.8398 3.500 0.3338 0.00851 0.00278 0.0109 0.4327 0.8429 3.750 0.3445 0.00927 0.00307 0.0139 0.3176 0.8454 4.000 0.3597 0.00991 0.00336 0.0160 0.2278 0.8474 4.250 0.3769 0.01045 0.00362 0.0177 0.1589 0.8495 4.500 0.3943 0.01098 0.00390 0.0193 0.0976 0.8517 4.750 0.4124 0.01147 0.00419 0.0208 0.0526 0.8540 5.000 0.4328 0.01183 0.00448 0.0220 0.0334 0.8561 5.250 0.4534 0.01215 0.00477 0.0232 0.0237 0.8582 5.500 0.4745 0.01247 0.00509 0.0243 0.0195 0.8600 5.750 0.4961 0.01276 0.00545 0.0253 0.0174 0.8616 6.000 0.5174 0.01306 0.00578 0.0263 0.0152 0.8634 6.250 0.5363 0.01351 0.00629 0.0278 0.0133 0.8656 6.500 0.5557 0.01391 0.00673 0.0291 0.0122 0.8678 6.750 0.5753 0.01429 0.00717 0.0304 0.0118 0.8699 7.000 0.5940 0.01470 0.00764 0.0319 0.0108 0.8719 7.250 0.6105 0.01522 0.00823 0.0337 0.0106 0.8741 7.500 0.6279 0.01569 0.00877 0.0353 0.0101 0.8762 7.750 0.6446 0.01627 0.00945 0.0371 0.0100 0.8785 8.000 0.6622 0.01681 0.01001 0.0386 0.0090 0.8807 8.250 0.6782 0.01756 0.01084 0.0402 0.0086 0.8831 8.500 0.6937 0.01857 0.01195 0.0419 0.0084 0.8857 8.750 0.7117 0.01967 0.01318 0.0432 0.0080 0.8880 9.000 0.7315 0.02065 0.01431 0.0441 0.0078 0.8902 9.250 0.7511 0.02105 0.01480 0.0449 0.0075 0.8927 9.500 0.7699 0.02249 0.01642 0.0458 0.0075 0.8950 9.750 0.7878 0.02335 0.01746 0.0469 0.0069 0.8978 10.000 0.8040 0.02480 0.01910 0.0481 0.0067 0.9007 10.250 0.8211 0.02583 0.02030 0.0489 0.0065 0.9038 10.500 0.8363 0.02717 0.02183 0.0499 0.0062 0.9075 10.750 0.8491 0.02880 0.02369 0.0510 0.0061 0.9118 11.000 0.8571 0.03126 0.02647 0.0524 0.0061 0.9163 11.250 0.8738 0.03199 0.02730 0.0522 0.0058 0.9213 11.500 0.8824 0.03430 0.02989 0.0526 0.0057 0.9277 11.750 0.8936 0.03652 0.03234 0.0518 0.0056 0.9346 12.250 0.8779 0.04761 0.04438 0.0483 0.0057 0.9560 12.500 0.8738 0.05204 0.04899 0.0443 0.0052 0.9786 12.750 0.8742 0.05527 0.05239 0.0435 0.0054 1.0000 13.000 0.8576 0.06058 0.05789 0.0416 0.0054 1.0000 13.250 0.8307 0.06834 0.06583 0.0371 0.0053 1.0000 13.500 0.7587 0.09285 0.09075 0.0205 0.0055 1.0000