XFOIL Version 6.96 Calculated polar for: MH 95 15.86% 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -0.8558 0.12243 0.11958 -0.0476 1.0000 0.0089 -19.500 -0.8831 0.11354 0.11055 -0.0521 1.0000 0.0089 -19.250 -0.9062 0.10566 0.10255 -0.0560 1.0000 0.0089 -19.000 -0.9304 0.09785 0.09460 -0.0599 1.0000 0.0089 -18.750 -0.9483 0.09130 0.08794 -0.0631 1.0000 0.0089 -18.500 -0.9665 0.08486 0.08137 -0.0662 1.0000 0.0089 -18.250 -0.9832 0.07885 0.07525 -0.0689 1.0000 0.0089 -18.000 -0.9951 0.07373 0.07003 -0.0712 1.0000 0.0090 -17.750 -1.0097 0.06841 0.06459 -0.0733 1.0000 0.0089 -17.500 -1.0193 0.06396 0.06003 -0.0750 1.0000 0.0089 -17.250 -1.0278 0.05989 0.05585 -0.0763 1.0000 0.0089 -17.000 -1.0369 0.05591 0.05177 -0.0773 1.0000 0.0090 -16.750 -1.0419 0.05264 0.04842 -0.0778 1.0000 0.0090 -16.500 -1.0492 0.04934 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0.3142 0.7435 2.500 0.4456 0.00820 0.00233 -0.0320 0.2988 0.7492 2.750 0.4700 0.00837 0.00243 -0.0313 0.2832 0.7540 3.000 0.4941 0.00853 0.00255 -0.0306 0.2685 0.7590 3.250 0.5185 0.00869 0.00266 -0.0299 0.2561 0.7638 3.500 0.5433 0.00884 0.00276 -0.0293 0.2452 0.7680 3.750 0.5673 0.00900 0.00288 -0.0286 0.2338 0.7717 4.000 0.5901 0.00918 0.00300 -0.0277 0.2211 0.7753 4.250 0.6135 0.00932 0.00312 -0.0268 0.2112 0.7792 4.500 0.6364 0.00948 0.00325 -0.0259 0.2022 0.7831 4.750 0.6592 0.00966 0.00337 -0.0249 0.1924 0.7866 5.000 0.6818 0.00983 0.00352 -0.0239 0.1829 0.7900 5.250 0.7035 0.01004 0.00369 -0.0228 0.1722 0.7937 5.500 0.7254 0.01025 0.00386 -0.0217 0.1620 0.7975 5.750 0.7475 0.01046 0.00404 -0.0207 0.1529 0.8013 6.000 0.7690 0.01071 0.00423 -0.0196 0.1436 0.8050 6.250 0.7908 0.01093 0.00444 -0.0185 0.1354 0.8086 6.500 0.8118 0.01116 0.00465 -0.0174 0.1282 0.8125 6.750 0.8327 0.01142 0.00488 -0.0162 0.1205 0.8164 7.000 0.8539 0.01166 0.00511 -0.0151 0.1144 0.8204 7.250 0.8751 0.01192 0.00534 -0.0140 0.1091 0.8244 7.500 0.8956 0.01217 0.00558 -0.0127 0.1045 0.8284 7.750 0.9166 0.01239 0.00583 -0.0116 0.1012 0.8326 8.000 0.9370 0.01265 0.00609 -0.0104 0.0978 0.8369 8.250 0.9571 0.01294 0.00636 -0.0092 0.0939 0.8411 8.500 0.9778 0.01317 0.00662 -0.0081 0.0918 0.8454 8.750 0.9976 0.01343 0.00690 -0.0068 0.0895 0.8502 9.000 1.0170 0.01371 0.00720 -0.0055 0.0871 0.8553 9.250 1.0362 0.01403 0.00752 -0.0042 0.0847 0.8601 9.500 1.0552 0.01432 0.00784 -0.0029 0.0829 0.8647 9.750 1.0743 0.01459 0.00816 -0.0016 0.0818 0.8703 10.000 1.0933 0.01489 0.00849 -0.0003 0.0803 0.8762 10.250 1.1114 0.01521 0.00885 0.0011 0.0789 0.8819 10.500 1.1284 0.01556 0.00923 0.0026 0.0774 0.8884 10.750 1.1454 0.01594 0.00963 0.0041 0.0757 0.8951 11.000 1.1608 0.01635 0.01009 0.0059 0.0738 0.9023 11.250 1.1778 0.01669 0.01049 0.0074 0.0732 0.9110 11.500 1.1940 0.01704 0.01090 0.0090 0.0724 0.9206 11.750 1.2095 0.01742 0.01135 0.0106 0.0716 0.9326 12.000 1.2261 0.01783 0.01183 0.0120 0.0705 0.9490 12.250 1.2523 0.01834 0.01239 0.0112 0.0694 0.9693 12.500 1.2745 0.01890 0.01298 0.0110 0.0677 1.0000 12.750 1.2895 0.01949 0.01359 0.0123 0.0667 1.0000 13.000 1.3029 0.02018 0.01429 0.0138 0.0654 1.0000 13.250 1.3186 0.02075 0.01491 0.0149 0.0649 1.0000 13.500 1.3339 0.02135 0.01556 0.0161 0.0642 1.0000 13.750 1.3485 0.02200 0.01625 0.0172 0.0632 1.0000 14.000 1.3623 0.02271 0.01699 0.0184 0.0622 1.0000 14.250 1.3751 0.02350 0.01781 0.0196 0.0612 1.0000 14.500 1.3871 0.02435 0.01869 0.0208 0.0602 1.0000 14.750 1.3983 0.02529 0.01966 0.0220 0.0591 1.0000 15.000 1.4081 0.02634 0.02074 0.0233 0.0580 1.0000 15.250 1.4184 0.02738 0.02183 0.0244 0.0574 1.0000 15.500 1.4302 0.02836 0.02287 0.0253 0.0568 1.0000 15.750 1.4406 0.02947 0.02404 0.0262 0.0562 1.0000 16.000 1.4502 0.03066 0.02529 0.0271 0.0555 1.0000 16.250 1.4593 0.03193 0.02661 0.0279 0.0545 1.0000 16.500 1.4674 0.03333 0.02806 0.0286 0.0538 1.0000 16.750 1.4743 0.03487 0.02964 0.0293 0.0530 1.0000 17.000 1.4801 0.03656 0.03138 0.0299 0.0522 1.0000 17.250 1.4840 0.03847 0.03334 0.0304 0.0512 1.0000 17.500 1.4892 0.04033 0.03527 0.0307 0.0506 1.0000 17.750 1.4949 0.04220 0.03721 0.0309 0.0501 1.0000 18.000 1.5003 0.04415 0.03924 0.0310 0.0491 1.0000 18.250 1.5040 0.04633 0.04148 0.0310 0.0483 1.0000 18.500 1.5060 0.04874 0.04396 0.0309 0.0475 1.0000 18.750 1.5065 0.05138 0.04666 0.0305 0.0465 1.0000 19.000 1.5045 0.05440 0.04974 0.0300 0.0456 1.0000 19.250 1.5021 0.05755 0.05296 0.0294 0.0451 1.0000