XFOIL Version 6.94 Calculated polar for: Eif385mod 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.035 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0933 0.03944 0.02662 -0.0265 0.9993 0.3645 -2.750 -0.0667 0.03926 0.02623 -0.0268 0.9993 0.3652 -2.500 -0.0404 0.03919 0.02597 -0.0270 0.9993 0.3663 -2.250 -0.0145 0.03912 0.02580 -0.0272 0.9993 0.3684 -2.000 0.0108 0.03907 0.02576 -0.0272 0.9993 0.3738 -1.750 0.0352 0.03918 0.02590 -0.0273 0.9993 0.3824 -1.500 0.0592 0.03949 0.02616 -0.0273 0.9993 0.3908 -1.250 0.0828 0.03969 0.02653 -0.0273 0.9993 0.3990 -1.000 0.1054 0.04011 0.02707 -0.0273 0.9993 0.4083 -0.750 0.1275 0.04056 0.02775 -0.0274 0.9993 0.4235 -0.500 0.1489 0.04113 0.02864 -0.0275 0.9993 0.4434 -0.250 0.1698 0.04177 0.02975 -0.0279 0.9993 0.4731 0.000 0.1786 0.04128 0.03096 -0.0259 0.9993 0.8967 0.250 0.2543 0.04172 0.03113 -0.0369 0.9705 1.0007 0.500 0.3643 0.04111 0.03026 -0.0522 0.9254 1.0007 0.750 0.4749 0.03840 0.02747 -0.0654 0.8635 1.0007 1.000 0.5772 0.03445 0.02341 -0.0741 0.7968 1.0007 1.250 0.6327 0.03252 0.02119 -0.0751 0.7332 1.0007 1.500 0.6688 0.03228 0.02058 -0.0745 0.6850 1.0007 1.750 0.7006 0.03263 0.02060 -0.0740 0.6518 1.0007 2.000 0.7290 0.03346 0.02121 -0.0738 0.6261 1.0007 2.250 0.7593 0.03429 0.02182 -0.0740 0.6072 1.0007 2.500 0.7881 0.03534 0.02275 -0.0743 0.5909 1.0007 2.750 0.8163 0.03644 0.02377 -0.0747 0.5768 1.0007 3.000 0.8420 0.03783 0.02517 -0.0750 0.5640 1.0007 3.250 0.8675 0.03935 0.02673 -0.0756 0.5540 1.0007 3.500 0.8953 0.04075 0.02814 -0.0762 0.5464 1.0007 3.750 0.9173 0.04285 0.03037 -0.0768 0.5398 1.0007 4.000 0.9390 0.04499 0.03265 -0.0773 0.5341 1.0007 4.250 0.9646 0.04679 0.03449 -0.0780 0.5295 1.0007 4.500 0.9783 0.04981 0.03772 -0.0781 0.5251 1.0007 4.750 0.9848 0.05346 0.04162 -0.0778 0.5203 1.0007 5.000 0.9956 0.05663 0.04493 -0.0775 0.5158 1.0007