XFOIL Version 6.94 Calculated polar for: AH 95-160 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.6326 0.01093 0.00575 -0.1293 0.6437 0.8051 0.500 0.6878 0.01099 0.00582 -0.1290 0.6403 0.8486 1.000 0.7350 0.01131 0.00619 -0.1269 0.6364 0.9029 1.500 0.7728 0.01126 0.00628 -0.1225 0.6332 0.9637 2.000 0.8432 0.01133 0.00635 -0.1261 0.6290 0.9998 2.500 0.9043 0.01150 0.00647 -0.1279 0.6249 0.9998 3.000 0.9658 0.01165 0.00656 -0.1296 0.6213 0.9998 3.500 1.0268 0.01198 0.00680 -0.1311 0.6174 0.9998 4.000 1.0836 0.01229 0.00720 -0.1321 0.6130 0.9998 4.500 1.1409 0.01248 0.00744 -0.1329 0.6078 0.9998 5.000 1.2003 0.01249 0.00745 -0.1340 0.6026 0.9998 5.500 1.2598 0.01257 0.00748 -0.1350 0.5965 0.9998 6.000 1.3142 0.01244 0.00747 -0.1352 0.5872 0.9998 6.500 1.3725 0.01220 0.00716 -0.1358 0.5773 0.9998 7.000 1.4245 0.01223 0.00734 -0.1356 0.5665 0.9998 7.500 1.4779 0.01233 0.00748 -0.1356 0.5561 0.9998 8.000 1.5280 0.01248 0.00772 -0.1351 0.5426 0.9998 8.500 1.5742 0.01282 0.00816 -0.1340 0.5259 0.9998 9.000 1.6137 0.01335 0.00870 -0.1317 0.5023 0.9998 9.500 1.6389 0.01432 0.00969 -0.1272 0.4707 0.9998 10.000 1.6410 0.01665 0.01187 -0.1204 0.4251 0.9998 10.500 1.6200 0.02149 0.01646 -0.1131 0.3666 0.9998 11.000 1.5907 0.02785 0.02258 -0.1066 0.3124 0.9998 11.500 1.5655 0.03411 0.02866 -0.1009 0.2660 0.9998 12.000 1.5469 0.04017 0.03452 -0.0963 0.2239 0.9998 12.500 1.5357 0.04590 0.04010 -0.0925 0.1876 0.9998 13.000 1.5295 0.05143 0.04550 -0.0895 0.1583 0.9998 13.500 1.5304 0.05642 0.05044 -0.0871 0.1350 0.9998 14.000 1.5327 0.06145 0.05543 -0.0850 0.1160 0.9998 14.500 1.5366 0.06638 0.06036 -0.0832 0.1006 0.9998 15.000 1.5395 0.07156 0.06557 -0.0817 0.0883 0.9998 15.500 1.5396 0.07719 0.07120 -0.0803 0.0772 0.9998 16.000 1.5484 0.08188 0.07599 -0.0793 0.0691 0.9998 16.500 1.5458 0.08798 0.08214 -0.0783 0.0613 0.9998 17.000 1.5527 0.09311 0.08741 -0.0778 0.0560 0.9998 17.500 1.5456 0.10002 0.09437 -0.0774 0.0499 0.9998 18.000 1.5527 0.10516 0.09969 -0.0774 0.0465 0.9998 18.500 1.5543 0.11114 0.10580 -0.0777 0.0430 0.9998 19.000 1.5465 0.11845 0.11319 -0.0784 0.0393 0.9998 19.500 1.5460 0.12479 0.11971 -0.0792 0.0369 0.9998 20.000 1.5494 0.13074 0.12584 -0.0805 0.0347 0.9998 20.500 1.5489 0.13731 0.13257 -0.0823 0.0324 0.9998 21.000 1.5426 0.14484 0.14020 -0.0848 0.0301 0.9998 21.500 1.5377 0.15199 0.14751 -0.0872 0.0280 0.9998 22.000 1.5384 0.15883 0.15456 -0.0904 0.0268 0.9998 22.500 1.5371 0.16603 0.16195 -0.0940 0.0253 0.9998 23.000 1.5341 0.17360 0.16968 -0.0981 0.0239 0.9998 23.500 1.5288 0.18159 0.17779 -0.1029 0.0226 0.9998 24.000 1.5209 0.18955 0.18589 -0.1075 0.0207 0.9998 24.500 1.5169 0.19792 0.19449 -0.1133 0.0202 0.9998 25.000 1.5096 0.20716 0.20397 -0.1199 0.0194 0.9998 25.500 1.5006 0.21700 0.21404 -0.1272 0.0185 0.9998 26.000 1.4917 0.22707 0.22430 -0.1350 0.0176 0.9998 26.500 1.4833 0.23725 0.23463 -0.1431 0.0167 0.9998 27.000 1.4746 0.24765 0.24516 -0.1516 0.0159 0.9998 27.500 1.4419 0.26559 0.26338 -0.1656 0.0150 0.9998