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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.250 -0.9501 0.09311 0.09065 -0.0379 1.0000 0.0134 -17.000 -1.0062 0.07984 0.07721 -0.0457 1.0000 0.0132 -16.750 -1.0632 0.06642 0.06355 -0.0539 1.0000 0.0128 -16.500 -1.0981 0.05648 0.05344 -0.0607 1.0000 0.0129 -16.250 -1.1211 0.04880 0.04559 -0.0663 1.0000 0.0129 -16.000 -1.1395 0.04233 0.03894 -0.0711 1.0000 0.0129 -15.750 -1.1475 0.03809 0.03456 -0.0737 1.0000 0.0130 -15.500 -1.1502 0.03503 0.03140 -0.0750 1.0000 0.0132 -15.250 -1.1562 0.03212 0.02836 -0.0754 1.0000 0.0133 -15.000 -1.1527 0.03041 0.02656 -0.0749 1.0000 0.0136 -14.750 -1.1534 0.02860 0.02464 -0.0737 1.0000 0.0137 -14.500 -1.1510 0.02723 0.02316 -0.0719 1.0000 0.0139 -14.250 -1.1482 0.02603 0.02186 -0.0696 1.0000 0.0141 -14.000 -1.1429 0.02511 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0.7364 0.500 0.2630 0.00558 0.00129 -0.0372 0.6127 0.7740 0.750 0.2876 0.00548 0.00131 -0.0363 0.6050 0.8150 1.000 0.3125 0.00541 0.00134 -0.0355 0.5964 0.8558 1.250 0.3397 0.00538 0.00139 -0.0351 0.5864 0.8912 1.500 0.3722 0.00541 0.00147 -0.0359 0.5759 0.9246 1.750 0.4108 0.00552 0.00157 -0.0381 0.5640 0.9456 2.250 0.4816 0.00577 0.00172 -0.0412 0.5360 0.9639 2.500 0.5146 0.00592 0.00180 -0.0422 0.5178 0.9709 2.750 0.5534 0.00608 0.00190 -0.0445 0.5022 0.9742 3.000 0.5898 0.00625 0.00201 -0.0464 0.4874 0.9789 3.250 0.6226 0.00643 0.00213 -0.0474 0.4721 0.9833 3.500 0.6594 0.00660 0.00222 -0.0494 0.4528 0.9853 3.750 0.6950 0.00676 0.00232 -0.0512 0.4390 0.9877 4.000 0.7294 0.00693 0.00244 -0.0527 0.4262 0.9905 4.500 0.7983 0.00724 0.00266 -0.0558 0.3981 0.9952 4.750 0.8344 0.00740 0.00276 -0.0577 0.3818 0.9974 5.000 0.8716 0.00760 0.00288 -0.0599 0.3590 0.9996 5.250 0.8957 0.00782 0.00302 -0.0593 0.3355 1.0000 5.500 0.9138 0.00816 0.00320 -0.0576 0.3006 1.0000 5.750 0.9293 0.00866 0.00347 -0.0553 0.2565 1.0000 6.000 0.9453 0.00912 0.00377 -0.0532 0.2223 1.0000 6.250 0.9616 0.00957 0.00407 -0.0511 0.1927 1.0000 6.500 0.9765 0.01010 0.00441 -0.0487 0.1575 1.0000 6.750 0.9857 0.01093 0.00493 -0.0455 0.1027 1.0000 7.000 0.9993 0.01150 0.00535 -0.0429 0.0792 1.0000 7.250 1.0170 0.01185 0.00568 -0.0411 0.0714 1.0000 7.500 1.0342 0.01223 0.00602 -0.0391 0.0656 1.0000 7.750 1.0531 0.01250 0.00631 -0.0375 0.0626 1.0000 8.000 1.0717 0.01280 0.00661 -0.0358 0.0599 1.0000 8.250 1.0888 0.01316 0.00697 -0.0339 0.0566 1.0000 8.500 1.1057 0.01353 0.00735 -0.0320 0.0536 1.0000 8.750 1.1250 0.01378 0.00762 -0.0305 0.0517 1.0000 9.000 1.1426 0.01410 0.00795 -0.0287 0.0492 1.0000 9.250 1.1576 0.01454 0.00837 -0.0265 0.0460 1.0000 9.500 1.1749 0.01485 0.00872 -0.0248 0.0440 1.0000 9.750 1.1897 0.01515 0.00903 -0.0225 0.0416 1.0000 10.000 1.2009 0.01557 0.00943 -0.0197 0.0389 1.0000 10.250 1.2142 0.01596 0.00985 -0.0173 0.0365 1.0000 10.500 1.2278 0.01639 0.01028 -0.0151 0.0340 1.0000 10.750 1.2392 0.01697 0.01085 -0.0127 0.0314 1.0000 11.000 1.2535 0.01745 0.01137 -0.0108 0.0295 1.0000 11.250 1.2655 0.01810 0.01201 -0.0088 0.0278 1.0000 11.500 1.2760 0.01887 0.01282 -0.0067 0.0260 1.0000 11.750 1.2892 0.01954 0.01354 -0.0051 0.0248 1.0000 12.000 1.3009 0.02035 0.01437 -0.0035 0.0237 1.0000 12.250 1.3099 0.02139 0.01544 -0.0018 0.0224 1.0000 12.500 1.3190 0.02249 0.01659 -0.0003 0.0215 1.0000 12.750 1.3303 0.02350 0.01767 0.0009 0.0208 1.0000 13.000 1.3422 0.02450 0.01870 0.0019 0.0198 1.0000 13.250 1.3502 0.02584 0.02009 0.0030 0.0191 1.0000 13.500 1.3557 0.02745 0.02174 0.0042 0.0184 1.0000 13.750 1.3611 0.02912 0.02348 0.0052 0.0177 1.0000 14.000 1.3693 0.03061 0.02504 0.0059 0.0174 1.0000 14.250 1.3773 0.03215 0.02664 0.0066 0.0169 1.0000 14.500 1.3835 0.03387 0.02843 0.0073 0.0165 1.0000 14.750 1.3901 0.03560 0.03022 0.0078 0.0160 1.0000 15.000 1.3929 0.03773 0.03242 0.0083 0.0156 1.0000 15.250 1.3916 0.04030 0.03505 0.0087 0.0151 1.0000 15.500 1.3867 0.04334 0.03817 0.0090 0.0147 1.0000 15.750 1.3906 0.04555 0.04046 0.0092 0.0145 1.0000 16.000 1.3908 0.04822 0.04322 0.0092 0.0144 1.0000 16.250 1.3946 0.05057 0.04565 0.0091 0.0140 1.0000 16.500 1.3957 0.05330 0.04846 0.0089 0.0137 1.0000 16.750 1.3955 0.05622 0.05146 0.0085 0.0135 1.0000 17.000 1.3943 0.05933 0.05465 0.0080 0.0133 1.0000 17.250 1.3933 0.06251 0.05791 0.0074 0.0130 1.0000 17.500 1.3895 0.06612 0.06160 0.0066 0.0128 1.0000 17.750 1.3841 0.06998 0.06555 0.0057 0.0126 1.0000 18.000 1.3767 0.07421 0.06985 0.0045 0.0123 1.0000 18.250 1.3701 0.07840 0.07413 0.0033 0.0123 1.0000 18.500 1.3563 0.08365 0.07947 0.0017 0.0121 1.0000 18.750 1.3458 0.08851 0.08443 0.0001 0.0120 1.0000