XFOIL Version 6.96 Calculated polar for: RAF 38 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.4522 0.10000 0.09255 -0.0399 1.0000 0.0713 -10.500 -0.4602 0.09465 0.08728 -0.0425 1.0000 0.0723 -10.250 -0.4714 0.08869 0.08141 -0.0458 1.0000 0.0728 -10.000 -0.4875 0.08169 0.07451 -0.0501 1.0000 0.0728 -9.750 -0.5141 0.07376 0.06665 -0.0555 1.0000 0.0720 -9.500 -0.5439 0.06835 0.06128 -0.0569 1.0000 0.0712 -9.250 -0.5716 0.06402 0.05691 -0.0558 1.0000 0.0711 -9.000 -0.5937 0.06000 0.05277 -0.0540 1.0000 0.0715 -8.750 -0.6112 0.05629 0.04888 -0.0517 1.0000 0.0723 -8.500 -0.6250 0.05279 0.04511 -0.0489 1.0000 0.0733 -8.250 -0.6363 0.04952 0.04150 -0.0456 1.0000 0.0747 -8.000 -0.6461 0.04652 0.03800 -0.0420 1.0000 0.0763 -7.750 -0.6426 0.04474 0.03622 -0.0393 1.0000 0.0787 -7.500 -0.6385 0.04327 0.03469 -0.0366 1.0000 0.0814 -7.250 -0.6356 0.04149 0.03268 -0.0337 1.0000 0.0841 -7.000 -0.6321 0.03956 0.03034 -0.0309 1.0000 0.0875 -6.750 -0.6160 0.03742 0.02778 -0.0302 0.9964 0.0917 -6.500 -0.5848 0.03586 0.02610 -0.0320 0.9882 0.0973 -6.250 -0.5539 0.03400 0.02367 -0.0335 0.9799 0.1039 -6.000 -0.5219 0.03263 0.02227 -0.0351 0.9722 0.1095 -5.750 -0.4887 0.03140 0.02073 -0.0367 0.9648 0.1169 -5.500 -0.4573 0.03017 0.01934 -0.0377 0.9567 0.1220 -5.250 -0.4246 0.02930 0.01834 -0.0391 0.9492 0.1299 -5.000 -0.3912 0.02841 0.01734 -0.0405 0.9420 0.1384 -4.750 -0.3597 0.02762 0.01644 -0.0414 0.9342 0.1465 -4.500 -0.3242 0.02681 0.01557 -0.0430 0.9276 0.1574 -4.250 -0.2948 0.02616 0.01490 -0.0436 0.9193 0.1736 -4.000 -0.2592 0.02537 0.01416 -0.0455 0.9131 0.2036 -3.750 -0.2314 0.02461 0.01356 -0.0460 0.9046 0.2429 -3.500 -0.1991 0.02384 0.01306 -0.0473 0.8980 0.3015 -3.250 -0.1744 0.02330 0.01282 -0.0470 0.8893 0.3717 -3.000 -0.1462 0.02278 0.01265 -0.0471 0.8819 0.4647 -2.750 -0.1251 0.02231 0.01274 -0.0452 0.8733 0.5797 -2.500 -0.0947 0.02203 0.01296 -0.0440 0.8664 0.7065 -2.250 -0.0519 0.02203 0.01304 -0.0452 0.8604 0.7939 -2.000 -0.0006 0.02214 0.01302 -0.0485 0.8533 0.8491 -1.750 0.0603 0.02217 0.01281 -0.0539 0.8483 0.8926 -1.500 0.1162 0.02227 0.01270 -0.0589 0.8408 0.9266 -1.250 0.1868 0.02224 0.01243 -0.0667 0.8352 0.9622 -1.000 0.2686 0.02190 0.01185 -0.0771 0.8310 0.9939 -0.750 0.2947 0.02191 0.01174 -0.0777 0.8198 1.0000 -0.500 0.3133 0.02196 0.01167 -0.0766 0.8097 1.0000 -0.250 0.3343 0.02201 0.01160 -0.0757 0.8000 1.0000 0.000 0.3500 0.02223 0.01172 -0.0740 0.7890 1.0000 0.250 0.3744 0.02227 0.01166 -0.0734 0.7809 1.0000 0.500 0.3895 0.02256 0.01188 -0.0715 0.7696 1.0000 0.750 0.4081 0.02279 0.01204 -0.0700 0.7599 1.0000 1.000 0.4304 0.02295 0.01213 -0.0691 0.7511 1.0000 1.250 0.4463 0.02330 0.01243 -0.0672 0.7404 1.0000 1.500 0.4728 0.02337 0.01244 -0.0667 0.7331 1.0000 1.750 0.4866 0.02383 0.01288 -0.0645 0.7216 1.0000 2.000 0.5070 0.02410 0.01313 -0.0632 0.7123 1.0000 2.250 0.5284 0.02435 0.01336 -0.0620 0.7032 1.0000 2.500 0.5453 0.02479 0.01380 -0.0602 0.6929 1.0000 2.750 0.5713 0.02490 0.01390 -0.0595 0.6851 1.0000 3.000 0.5857 0.02545 0.01447 -0.0575 0.6739 1.0000 3.250 0.6104 0.02562 0.01465 -0.0566 0.6659 1.0000 3.500 0.6277 0.02606 0.01513 -0.0549 0.6552 1.0000 3.750 0.6460 0.02649 0.01560 -0.0532 0.6450 1.0000 4.000 0.6721 0.02656 0.01570 -0.0525 0.6364 1.0000 4.250 0.6872 0.02707 0.01626 -0.0504 0.6244 1.0000 4.500 0.7083 0.02731 0.01656 -0.0490 0.6136 1.0000 4.750 0.7344 0.02730 0.01659 -0.0480 0.6038 1.0000 5.000 0.7498 0.02778 0.01715 -0.0460 0.5912 1.0000 5.250 0.7692 0.02812 0.01758 -0.0444 0.5801 1.0000 5.500 0.7974 0.02804 0.01757 -0.0437 0.5710 1.0000 5.750 0.8116 0.02864 0.01828 -0.0416 0.5584 1.0000 6.000 0.8295 0.02907 0.01884 -0.0399 0.5469 1.0000 6.250 0.8543 0.02916 0.01901 -0.0389 0.5365 1.0000 6.500 0.8748 0.02944 0.01942 -0.0374 0.5248 1.0000 6.750 0.8910 0.02993 0.02006 -0.0355 0.5119 1.0000 7.000 0.9100 0.03020 0.02044 -0.0338 0.4983 1.0000 7.250 0.9302 0.03016 0.02049 -0.0319 0.4816 1.0000 7.500 0.9525 0.02973 0.02007 -0.0298 0.4608 1.0000 7.750 0.9630 0.02994 0.02031 -0.0267 0.4374 1.0000 8.000 0.9766 0.03005 0.02039 -0.0240 0.4139 1.0000 8.250 0.9878 0.03053 0.02092 -0.0214 0.3932 1.0000 8.500 0.9957 0.03124 0.02175 -0.0185 0.3727 1.0000 8.750 1.0020 0.03192 0.02248 -0.0155 0.3509 1.0000 9.000 1.0053 0.03276 0.02334 -0.0122 0.3281 1.0000 9.250 1.0075 0.03373 0.02430 -0.0091 0.3032 1.0000 9.500 1.0096 0.03493 0.02546 -0.0063 0.2783 1.0000 9.750 1.0109 0.03632 0.02672 -0.0038 0.2538 1.0000 10.000 1.0102 0.03806 0.02836 -0.0015 0.2295 1.0000 10.250 1.0086 0.04006 0.03024 0.0006 0.2072 1.0000 10.500 1.0074 0.04224 0.03234 0.0023 0.1868 1.0000 10.750 1.0070 0.04449 0.03452 0.0037 0.1698 1.0000 11.000 1.0082 0.04673 0.03670 0.0050 0.1560 1.0000 11.250 1.0095 0.04900 0.03891 0.0060 0.1444 1.0000 11.500 1.0111 0.05132 0.04121 0.0069 0.1338 1.0000 11.750 1.0146 0.05362 0.04358 0.0077 0.1242 1.0000 12.000 1.0169 0.05597 0.04584 0.0085 0.1162 1.0000 12.250 1.0208 0.05840 0.04844 0.0091 0.1082 1.0000 12.500 1.0247 0.06076 0.05075 0.0097 0.1014 1.0000 12.750 1.0290 0.06331 0.05349 0.0102 0.0949 1.0000 13.000 1.0361 0.06546 0.05554 0.0109 0.0891 1.0000 13.250 1.0376 0.06855 0.05893 0.0110 0.0838 1.0000 13.500 1.0446 0.07086 0.06122 0.0115 0.0788 1.0000 13.750 1.0467 0.07406 0.06463 0.0116 0.0748 1.0000 14.000 1.0444 0.07781 0.06864 0.0113 0.0716 1.0000 14.250 1.0458 0.08098 0.07191 0.0111 0.0684 1.0000 14.500 1.0491 0.08411 0.07511 0.0110 0.0653 1.0000 14.750 1.0346 0.08972 0.08105 0.0092 0.0641 1.0000 15.000 1.0179 0.09594 0.08755 0.0068 0.0632 1.0000 15.250 0.9971 0.10321 0.09509 0.0035 0.0625 1.0000 15.500 0.9718 0.11192 0.10401 -0.0011 0.0624 1.0000 15.750 0.9379 0.12333 0.11563 -0.0076 0.0628 1.0000 16.000 0.8984 0.13773 0.13014 -0.0159 0.0636 1.0000