XFOIL Version 6.96 Calculated polar for: RG 15A-1.8/11.0 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.000 -0.7668 0.08309 0.08033 -0.0384 1.0000 0.0063 -13.750 -0.8106 0.07004 0.06715 -0.0461 1.0000 0.0062 -13.500 -0.8439 0.05862 0.05557 -0.0541 1.0000 0.0062 -13.250 -0.8699 0.04962 0.04636 -0.0611 1.0000 0.0061 -13.000 -0.8882 0.04365 0.04019 -0.0651 1.0000 0.0061 -12.750 -0.9006 0.03958 0.03595 -0.0668 1.0000 0.0062 -12.500 -0.9133 0.03622 0.03242 -0.0669 1.0000 0.0062 -12.250 -0.9218 0.03391 0.02994 -0.0656 1.0000 0.0063 -12.000 -0.9353 0.03201 0.02790 -0.0622 1.0000 0.0063 -11.750 -0.9411 0.03043 0.02615 -0.0588 1.0000 0.0063 -11.500 -0.9401 0.02886 0.02440 -0.0561 1.0000 0.0064 -11.250 -0.9391 0.02714 0.02253 -0.0533 1.0000 0.0066 -11.000 -0.9315 0.02588 0.02116 -0.0511 1.0000 0.0068 -10.750 -0.9207 0.02484 0.02001 -0.0491 1.0000 0.0069 -10.500 -0.9077 0.02396 0.01904 -0.0472 1.0000 0.0071 -10.250 -0.8943 0.02306 0.01803 -0.0454 1.0000 0.0073 -10.000 -0.8789 0.02236 0.01725 -0.0438 1.0000 0.0076 -9.750 -0.8557 0.02152 0.01629 -0.0437 0.9990 0.0080 -9.500 -0.8262 0.02063 0.01525 -0.0449 0.9970 0.0085 -9.250 -0.7963 0.01975 0.01422 -0.0461 0.9950 0.0090 -9.000 -0.7672 0.01885 0.01319 -0.0471 0.9929 0.0094 -8.750 -0.7397 0.01787 0.01213 -0.0478 0.9900 0.0100 -8.500 -0.7097 0.01719 0.01138 -0.0489 0.9873 0.0105 -8.250 -0.6786 0.01654 0.01065 -0.0500 0.9851 0.0112 -8.000 -0.6465 0.01591 0.00992 -0.0514 0.9833 0.0119 -7.750 -0.6195 0.01533 0.00926 -0.0515 0.9792 0.0126 -7.500 -0.5904 0.01470 0.00855 -0.0522 0.9754 0.0133 -7.250 -0.5594 0.01407 0.00790 -0.0533 0.9726 0.0145 -7.000 -0.5266 0.01356 0.00732 -0.0546 0.9704 0.0156 -6.750 -0.5009 0.01310 0.00680 -0.0543 0.9644 0.0164 -6.500 -0.4699 0.01269 0.00633 -0.0552 0.9605 0.0173 -6.250 -0.4376 0.01211 0.00571 -0.0563 0.9577 0.0190 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0.5603 -1.250 0.1326 0.00672 0.00142 -0.0603 0.7334 0.6050 -1.000 0.1591 0.00672 0.00142 -0.0599 0.7175 0.6342 -0.750 0.1856 0.00674 0.00143 -0.0595 0.7014 0.6567 -0.500 0.2123 0.00678 0.00143 -0.0591 0.6851 0.6750 -0.250 0.2389 0.00683 0.00144 -0.0587 0.6686 0.6904 0.000 0.2655 0.00689 0.00146 -0.0583 0.6518 0.7039 0.250 0.2919 0.00696 0.00148 -0.0579 0.6346 0.7163 0.500 0.3185 0.00703 0.00152 -0.0576 0.6169 0.7276 0.750 0.3450 0.00711 0.00155 -0.0572 0.5982 0.7384 1.000 0.3712 0.00721 0.00160 -0.0568 0.5788 0.7496 1.250 0.3973 0.00731 0.00165 -0.0563 0.5594 0.7603 1.500 0.4234 0.00741 0.00172 -0.0559 0.5389 0.7707 1.750 0.4492 0.00754 0.00179 -0.0554 0.5178 0.7815 2.000 0.4751 0.00767 0.00187 -0.0550 0.4969 0.7922 2.250 0.5007 0.00780 0.00197 -0.0545 0.4761 0.8024 2.500 0.5262 0.00795 0.00207 -0.0540 0.4551 0.8134 3.250 0.6024 0.00842 0.00243 -0.0524 0.3931 0.8438 3.750 0.6518 0.00880 0.00272 -0.0511 0.3484 0.8661 4.000 0.6757 0.00902 0.00288 -0.0503 0.3246 0.8791 4.250 0.6995 0.00921 0.00305 -0.0495 0.3034 0.8936 4.750 0.7468 0.00962 0.00341 -0.0478 0.2638 0.9330 5.000 0.7764 0.00985 0.00362 -0.0482 0.2453 0.9586 5.250 0.8103 0.01017 0.00386 -0.0498 0.2238 0.9959 5.500 0.8351 0.01049 0.00410 -0.0494 0.2034 1.0000 5.750 0.8588 0.01087 0.00438 -0.0488 0.1811 1.0000 6.000 0.8822 0.01128 0.00467 -0.0482 0.1572 1.0000 6.250 0.9058 0.01166 0.00499 -0.0476 0.1396 1.0000 6.500 0.9297 0.01202 0.00530 -0.0470 0.1255 1.0000 6.750 0.9532 0.01241 0.00563 -0.0464 0.1116 1.0000 7.000 0.9765 0.01281 0.00598 -0.0458 0.0983 1.0000 7.250 0.9995 0.01323 0.00636 -0.0451 0.0867 1.0000 7.500 1.0225 0.01363 0.00675 -0.0444 0.0771 1.0000 7.750 1.0453 0.01404 0.00715 -0.0437 0.0684 1.0000 8.000 1.0676 0.01449 0.00758 -0.0429 0.0602 1.0000 8.250 1.0895 0.01496 0.00803 -0.0420 0.0529 1.0000 8.500 1.1114 0.01540 0.00850 -0.0412 0.0468 1.0000 8.750 1.1320 0.01594 0.00901 -0.0402 0.0400 1.0000 9.000 1.1525 0.01646 0.00953 -0.0391 0.0344 1.0000 9.250 1.1725 0.01700 0.01008 -0.0381 0.0300 1.0000 9.500 1.1923 0.01753 0.01063 -0.0369 0.0269 1.0000 9.750 1.2107 0.01816 0.01127 -0.0356 0.0240 1.0000 10.000 1.2302 0.01864 0.01184 -0.0344 0.0226 1.0000 10.250 1.2483 0.01920 0.01244 -0.0331 0.0208 1.0000 10.500 1.2633 0.01984 0.01310 -0.0313 0.0187 1.0000 10.750 1.2782 0.02044 0.01376 -0.0294 0.0170 1.0000 11.000 1.2928 0.02104 0.01443 -0.0275 0.0156 1.0000 11.250 1.3056 0.02176 0.01517 -0.0255 0.0139 1.0000 11.500 1.3180 0.02250 0.01598 -0.0235 0.0126 1.0000 11.750 1.3300 0.02329 0.01684 -0.0216 0.0112 1.0000 12.000 1.3398 0.02422 0.01782 -0.0195 0.0100 1.0000 12.250 1.3496 0.02517 0.01885 -0.0175 0.0089 1.0000 12.500 1.3579 0.02624 0.01999 -0.0156 0.0079 1.0000 12.750 1.3644 0.02748 0.02131 -0.0136 0.0072 1.0000 13.000 1.3702 0.02884 0.02276 -0.0117 0.0067 1.0000 13.250 1.3755 0.03028 0.02430 -0.0101 0.0063 1.0000 13.500 1.3799 0.03187 0.02600 -0.0086 0.0059 1.0000 13.750 1.3830 0.03366 0.02790 -0.0073 0.0056 1.0000 14.000 1.3839 0.03576 0.03009 -0.0062 0.0053 1.0000 14.250 1.3843 0.03802 0.03248 -0.0054 0.0051 1.0000 14.500 1.3802 0.04090 0.03548 -0.0049 0.0048 1.0000 14.750 1.3784 0.04372 0.03843 -0.0047 0.0047 1.0000 15.000 1.3762 0.04673 0.04158 -0.0049 0.0046 1.0000 15.250 1.3708 0.05032 0.04531 -0.0055 0.0045 1.0000 15.500 1.3660 0.05404 0.04916 -0.0064 0.0044 1.0000 15.750 1.3591 0.05823 0.05349 -0.0078 0.0043 1.0000 16.000 1.3502 0.06296 0.05837 -0.0095 0.0041 1.0000 16.250 1.3391 0.06827 0.06382 -0.0118 0.0041 1.0000 16.500 1.3265 0.07407 0.06977 -0.0145 0.0041 1.0000 16.750 1.3125 0.08037 0.07622 -0.0176 0.0041 1.0000 17.000 1.2967 0.08724 0.08324 -0.0212 0.0040 1.0000 17.250 1.2775 0.09501 0.09117 -0.0253 0.0040 1.0000 17.500 1.2597 0.10273 0.09904 -0.0295 0.0039 1.0000 17.750 1.2393 0.11121 0.10766 -0.0342 0.0040 1.0000 18.000 1.2205 0.11960 0.11619 -0.0389 0.0040 1.0000