XFOIL Version 6.94 Calculated polar for: GD BAP 02 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.030 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1643 0.05509 0.04446 -0.0440 0.9998 0.2931 -2.750 -0.1220 0.05347 0.04221 -0.0485 0.9998 0.2772 -2.500 -0.0913 0.05171 0.04030 -0.0499 0.9998 0.2723 -2.250 -0.0586 0.05030 0.03867 -0.0515 0.9998 0.2679 -2.000 -0.0259 0.04915 0.03726 -0.0529 0.9998 0.2644 -1.750 0.0063 0.04823 0.03605 -0.0540 0.9998 0.2614 -1.500 0.0384 0.04755 0.03504 -0.0548 0.9998 0.2589 -1.250 0.0696 0.04701 0.03423 -0.0554 0.9998 0.2575 -1.000 0.0998 0.04653 0.03359 -0.0556 0.9998 0.2577 -0.750 0.1296 0.04613 0.03311 -0.0558 0.9998 0.2594 -0.500 0.1589 0.04582 0.03281 -0.0559 0.9998 0.2635 -0.250 0.1878 0.04564 0.03271 -0.0560 0.9998 0.2710 0.000 0.2167 0.04559 0.03280 -0.0562 0.9998 0.2806 0.250 0.2448 0.04564 0.03328 -0.0568 0.9998 0.2949 0.500 0.3672 0.04150 0.03192 -0.0754 0.9383 0.5981 0.750 0.4175 0.03652 0.02652 -0.0762 0.7734 1.0002 1.000 0.5191 0.03312 0.02176 -0.0850 0.7147 1.0002 1.250 0.6211 0.03182 0.01916 -0.0972 0.6626 1.0002 1.500 0.6765 0.03242 0.01906 -0.1023 0.6326 1.0002 1.750 0.7212 0.03329 0.01945 -0.1056 0.6120 1.0002 2.000 0.7645 0.03425 0.01998 -0.1087 0.5961 1.0002 2.250 0.7992 0.03527 0.02090 -0.1104 0.5841 1.0002 2.500 0.8397 0.03637 0.02177 -0.1132 0.5751 1.0002 2.750 0.8735 0.03756 0.02298 -0.1150 0.5678 1.0002 3.000 0.9061 0.03883 0.02426 -0.1165 0.5605 1.0002 3.250 0.9421 0.04014 0.02550 -0.1185 0.5533 1.0002 3.500 0.9738 0.04161 0.02699 -0.1199 0.5474 1.0002 3.750 0.9988 0.04324 0.02882 -0.1204 0.5430 1.0002 4.000 1.0235 0.04501 0.03075 -0.1208 0.5391 1.0002 4.250 1.0478 0.04687 0.03274 -0.1212 0.5350 1.0002 4.500 1.0740 0.04879 0.03472 -0.1218 0.5307 1.0002 4.750 1.1019 0.05088 0.03687 -0.1226 0.5268 1.0002 5.000 1.1125 0.05357 0.03981 -0.1213 0.5251 1.0002