XFOIL Version 6.94 Calculated polar for: BL BAP 04 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.022 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1748 0.05458 0.04475 -0.0386 0.9998 0.3344 -2.750 -0.1355 0.05273 0.04257 -0.0422 0.9998 0.3280 -2.500 -0.0988 0.05091 0.04056 -0.0451 0.9998 0.3256 -2.250 -0.0617 0.04948 0.03890 -0.0479 0.9998 0.3250 -2.000 -0.0256 0.04837 0.03759 -0.0504 0.9998 0.3257 -1.750 0.0083 0.04763 0.03668 -0.0527 0.9998 0.3269 -1.500 0.0776 0.04641 0.03509 -0.0621 0.9769 0.3300 -1.250 0.1456 0.04457 0.03316 -0.0709 0.9373 0.3374 -1.000 0.1883 0.04344 0.03205 -0.0748 0.8919 0.3484 -0.750 0.2177 0.04348 0.03195 -0.0769 0.8517 0.3629 -0.500 0.2535 0.04333 0.03202 -0.0800 0.8296 0.3898 -0.250 0.2922 0.04296 0.03218 -0.0834 0.8175 0.4420 0.000 0.3129 0.04112 0.03213 -0.0824 0.8087 1.0002 0.250 0.3618 0.04238 0.03204 -0.0863 0.8027 1.0002 0.500 0.3912 0.04424 0.03313 -0.0883 0.7977 1.0002 0.750 0.4157 0.04638 0.03476 -0.0901 0.7943 1.0002 1.000 0.4357 0.04894 0.03694 -0.0917 0.7938 1.0002 1.250 0.4515 0.05202 0.03974 -0.0933 0.7978 1.0002 1.500 0.4582 0.05571 0.04325 -0.0940 0.8047 1.0002 1.750 0.4472 0.06017 0.04759 -0.0926 0.8158 1.0002 2.000 0.4458 0.06420 0.05149 -0.0924 0.8276 1.0002 2.250 0.4397 0.06830 0.05546 -0.0914 0.8425 1.0002 2.500 0.4204 0.07221 0.05931 -0.0884 0.8607 1.0002 2.750 0.4058 0.07577 0.06280 -0.0858 0.8812 1.0002 3.000 0.3931 0.07917 0.06613 -0.0832 0.9055 1.0002 3.250 0.3610 0.08186 0.06879 -0.0770 0.9452 1.0002 3.500 0.3048 0.08251 0.06947 -0.0645 0.9998 1.0002 3.750 0.3187 0.08495 0.07172 -0.0653 0.9998 1.0002 4.000 0.3325 0.08743 0.07404 -0.0661 0.9998 1.0002 4.250 0.3461 0.08995 0.07641 -0.0669 0.9998 1.0002 4.500 0.3595 0.09250 0.07883 -0.0677 0.9998 1.0002 4.750 0.3728 0.09509 0.08130 -0.0685 0.9998 1.0002 5.000 0.3860 0.09771 0.08383 -0.0694 0.9998 1.0002