XFOIL Version 6.94 Calculated polar for: SD7037-092-88 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3868 0.00702 0.00265 -0.0815 0.8251 1.0000 0.500 0.4378 0.00704 0.00243 -0.0800 0.7925 1.0000 1.000 0.4897 0.00716 0.00231 -0.0787 0.7554 1.0000 1.500 0.5417 0.00739 0.00228 -0.0775 0.7155 1.0000 2.000 0.5936 0.00768 0.00235 -0.0764 0.6738 1.0000 2.500 0.6453 0.00804 0.00249 -0.0753 0.6308 1.0000 3.000 0.6968 0.00843 0.00270 -0.0742 0.5874 1.0000 3.500 0.7478 0.00889 0.00295 -0.0732 0.5432 1.0000 4.000 0.7986 0.00937 0.00330 -0.0721 0.4979 1.0000 4.500 0.8486 0.00993 0.00368 -0.0710 0.4524 1.0000 5.000 0.8980 0.01055 0.00416 -0.0699 0.4059 1.0000 5.500 0.9469 0.01122 0.00470 -0.0687 0.3595 1.0000 6.000 0.9948 0.01198 0.00536 -0.0674 0.3144 1.0000 6.500 1.0413 0.01287 0.00609 -0.0660 0.2690 1.0000 7.000 1.0875 0.01378 0.00691 -0.0646 0.2251 1.0000 7.500 1.1320 0.01482 0.00783 -0.0630 0.1856 1.0000 8.000 1.1757 0.01589 0.00884 -0.0613 0.1473 1.0000 8.500 1.2174 0.01710 0.00998 -0.0595 0.1139 1.0000 9.000 1.2566 0.01846 0.01127 -0.0573 0.0837 1.0000 9.500 1.2892 0.02033 0.01300 -0.0542 0.0465 1.0000 10.000 1.3063 0.02322 0.01583 -0.0488 0.0238 1.0000 10.500 1.3196 0.02567 0.01845 -0.0431 0.0199 1.0000 11.000 1.3264 0.02868 0.02172 -0.0374 0.0184 1.0000 11.500 1.3344 0.03192 0.02522 -0.0329 0.0173 1.0000 12.000 1.3387 0.03584 0.02937 -0.0291 0.0164 1.0000 12.500 1.3409 0.04041 0.03417 -0.0264 0.0157 1.0000 13.000 1.3405 0.04582 0.03982 -0.0246 0.0152 1.0000 13.500 1.3379 0.05210 0.04636 -0.0236 0.0149 1.0000 14.000 1.3298 0.05976 0.05438 -0.0235 0.0145 1.0000 14.500 1.3145 0.06872 0.06374 -0.0253 0.0143 1.0000 15.000 1.2964 0.07870 0.07412 -0.0290 0.0141 1.0000 15.500 1.2731 0.09049 0.08630 -0.0347 0.0140 1.0000 16.000 1.2450 0.10437 0.10056 -0.0424 0.0140 1.0000 16.500 1.2118 0.12046 0.11699 -0.0519 0.0141 1.0000 17.000 1.1764 0.13853 0.13539 -0.0634 0.0143 1.0000 17.500 1.1448 0.15743 0.15457 -0.0757 0.0145 1.0000