XFOIL Version 6.96 Calculated polar for: RAF 15 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.250 -0.4011 0.08012 0.07537 -0.0178 1.0000 0.0314 -8.000 -0.4850 0.09164 0.08666 -0.0114 1.0000 0.0396 -7.750 -0.4976 0.08649 0.08156 -0.0137 1.0000 0.0309 -7.500 -0.4971 0.08280 0.07791 -0.0144 1.0000 0.0301 -7.250 -0.4965 0.07897 0.07410 -0.0153 1.0000 0.0294 -7.000 -0.4948 0.07490 0.07004 -0.0165 1.0000 0.0287 -6.750 -0.4915 0.07073 0.06585 -0.0176 1.0000 0.0280 -6.500 -0.4870 0.06626 0.06135 -0.0187 1.0000 0.0275 -6.250 -0.4809 0.06160 0.05661 -0.0196 1.0000 0.0270 -6.000 -0.4732 0.05676 0.05167 -0.0202 1.0000 0.0267 -5.750 -0.4634 0.05229 0.04705 -0.0204 1.0000 0.0278 -5.500 -0.4529 0.04739 0.04194 -0.0201 1.0000 0.0284 -5.250 -0.4426 0.04158 0.03579 -0.0193 1.0000 0.0290 -5.000 -0.4325 0.03622 0.02995 -0.0177 1.0000 0.0291 -4.750 -0.4207 0.03180 0.02494 -0.0155 1.0000 0.0295 -4.500 -0.4060 0.02836 0.02085 -0.0131 1.0000 0.0302 -4.250 -0.3880 0.02601 0.01788 -0.0110 1.0000 0.0320 -4.000 -0.3697 0.02388 0.01538 -0.0092 1.0000 0.0342 -3.750 -0.3494 0.02234 0.01362 -0.0076 1.0000 0.0365 -3.500 -0.3279 0.02102 0.01204 -0.0060 1.0000 0.0389 -3.250 -0.3056 0.02005 0.01078 -0.0046 1.0000 0.0430 -3.000 -0.2835 0.01889 0.00948 -0.0032 1.0000 0.0464 -2.750 -0.2617 0.01814 0.00868 -0.0019 1.0000 0.0509 -2.500 -0.2394 0.01757 0.00798 -0.0005 1.0000 0.0571 -2.000 -0.1955 0.01648 0.00688 0.0021 1.0000 0.0732 -1.750 -0.1735 0.01600 0.00648 0.0033 1.0000 0.0898 -1.500 -0.1511 0.01562 0.00625 0.0045 1.0000 0.1242 -1.250 -0.1110 0.01559 0.00630 0.0018 0.9934 0.1723 -1.000 -0.0691 0.01566 0.00637 -0.0013 0.9844 0.2140 -0.750 -0.0302 0.01552 0.00625 -0.0036 0.9749 0.2414 -0.500 0.0074 0.01527 0.00604 -0.0057 0.9640 0.2665 -0.250 0.0448 0.01497 0.00575 -0.0076 0.9515 0.2847 0.000 0.0815 0.01463 0.00545 -0.0093 0.9375 0.3041 0.250 0.1191 0.01425 0.00516 -0.0111 0.9224 0.3314 0.500 0.1572 0.01360 0.00485 -0.0131 0.9065 0.4010 1.000 0.3446 0.01223 0.00473 -0.0403 0.8686 1.0000 1.250 0.4115 0.01205 0.00438 -0.0480 0.8035 1.0000 1.500 0.4779 0.01214 0.00398 -0.0554 0.6921 1.0000 1.750 0.5104 0.01254 0.00395 -0.0559 0.6100 1.0000 2.000 0.5363 0.01294 0.00403 -0.0553 0.5510 1.0000 2.250 0.5598 0.01333 0.00417 -0.0542 0.5066 1.0000 2.500 0.5826 0.01369 0.00434 -0.0530 0.4712 1.0000 2.750 0.6052 0.01403 0.00455 -0.0518 0.4420 1.0000 3.000 0.6276 0.01436 0.00477 -0.0505 0.4168 1.0000 3.250 0.6498 0.01471 0.00501 -0.0493 0.3950 1.0000 3.500 0.6722 0.01505 0.00530 -0.0481 0.3760 1.0000 3.750 0.6946 0.01539 0.00560 -0.0469 0.3582 1.0000 4.000 0.7169 0.01574 0.00593 -0.0457 0.3415 1.0000 4.250 0.7390 0.01610 0.00630 -0.0444 0.3252 1.0000 4.500 0.7610 0.01647 0.00667 -0.0432 0.3089 1.0000 4.750 0.7822 0.01685 0.00702 -0.0418 0.2897 1.0000 5.000 0.8033 0.01717 0.00735 -0.0404 0.2651 1.0000 5.250 0.8240 0.01752 0.00769 -0.0390 0.2384 1.0000 5.500 0.8447 0.01791 0.00805 -0.0376 0.2144 1.0000 5.750 0.8654 0.01836 0.00848 -0.0363 0.1909 1.0000 6.000 0.8856 0.01889 0.00898 -0.0348 0.1697 1.0000 6.250 0.9055 0.01949 0.00957 -0.0334 0.1489 1.0000 6.500 0.9245 0.02019 0.01027 -0.0318 0.1307 1.0000 6.750 0.9432 0.02096 0.01106 -0.0301 0.1139 1.0000 7.000 0.9610 0.02182 0.01191 -0.0283 0.1017 1.0000 7.250 0.9787 0.02269 0.01285 -0.0265 0.0921 1.0000 7.500 0.9960 0.02360 0.01384 -0.0246 0.0847 1.0000 7.750 1.0131 0.02450 0.01485 -0.0228 0.0785 1.0000 8.000 1.0289 0.02559 0.01598 -0.0208 0.0746 1.0000 8.250 1.0462 0.02663 0.01723 -0.0189 0.0712 1.0000 8.500 1.0630 0.02775 0.01851 -0.0171 0.0681 1.0000 8.750 1.0789 0.02893 0.01979 -0.0152 0.0650 1.0000 9.000 1.0933 0.03036 0.02127 -0.0133 0.0614 1.0000 9.250 1.1088 0.03153 0.02281 -0.0113 0.0574 1.0000 9.500 1.1221 0.03260 0.02403 -0.0093 0.0530 1.0000 9.750 1.1329 0.03424 0.02566 -0.0072 0.0494 1.0000 10.000 1.1438 0.03562 0.02746 -0.0048 0.0457 1.0000 10.250 1.1527 0.03693 0.02897 -0.0024 0.0419 1.0000 10.500 1.1587 0.03855 0.03060 0.0001 0.0390 1.0000 10.750 1.1619 0.04070 0.03312 0.0031 0.0364 1.0000 11.000 1.1622 0.04280 0.03554 0.0063 0.0340 1.0000 11.250 1.1599 0.04430 0.03717 0.0096 0.0317 1.0000 11.500 1.1568 0.04604 0.03897 0.0126 0.0302 1.0000 11.750 1.1506 0.04859 0.04161 0.0153 0.0292 1.0000 12.000 1.1383 0.05179 0.04517 0.0176 0.0284 1.0000 12.250 1.1237 0.05553 0.04922 0.0187 0.0278 1.0000 12.500 1.1075 0.05992 0.05387 0.0183 0.0275 1.0000 12.750 1.0883 0.06539 0.05959 0.0162 0.0273 1.0000 13.000 1.0684 0.07184 0.06625 0.0125 0.0273 1.0000 13.250 1.0468 0.07940 0.07400 0.0076 0.0276 1.0000 13.500 1.0224 0.08819 0.08293 0.0018 0.0279 1.0000 13.750 0.9973 0.09750 0.09234 -0.0039 0.0284 1.0000 14.000 0.9700 0.10774 0.10264 -0.0099 0.0288 1.0000