XFOIL Version 6.96 Calculated polar for: HQ 2.5/9.0 smoothed by Eppler 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.3488 0.08527 0.08051 -0.0387 1.0000 0.0402 -9.000 -0.4225 0.09165 0.08656 -0.0368 1.0000 0.0373 -8.750 -0.4208 0.08821 0.08316 -0.0368 1.0000 0.0356 -8.500 -0.4237 0.08437 0.07940 -0.0378 1.0000 0.0343 -8.250 -0.4305 0.08044 0.07556 -0.0390 1.0000 0.0332 -8.000 -0.4425 0.07649 0.07172 -0.0402 1.0000 0.0323 -7.500 -0.4763 0.06233 0.05740 -0.0507 1.0000 0.0287 -7.250 -0.4812 0.05876 0.05372 -0.0502 1.0000 0.0287 -7.000 -0.4863 0.05493 0.04983 -0.0495 1.0000 0.0292 -6.750 -0.4826 0.05366 0.04864 -0.0478 1.0000 0.0304 -6.500 -0.4700 0.05094 0.04577 -0.0489 0.9979 0.0318 -6.250 -0.4437 0.04514 0.03951 -0.0539 0.9920 0.0319 -6.000 -0.4157 0.03974 0.03357 -0.0577 0.9864 0.0316 -5.750 -0.3850 0.03545 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1.0000 4.000 0.7621 0.01371 0.00618 -0.0711 0.6072 1.0000 4.250 0.7858 0.01398 0.00609 -0.0696 0.5383 1.0000 4.500 0.8069 0.01457 0.00630 -0.0681 0.4777 1.0000 4.750 0.8283 0.01522 0.00668 -0.0670 0.4323 1.0000 5.000 0.8507 0.01579 0.00712 -0.0661 0.3972 1.0000 5.250 0.8735 0.01633 0.00759 -0.0653 0.3678 1.0000 5.500 0.8962 0.01687 0.00811 -0.0645 0.3391 1.0000 5.750 0.9185 0.01744 0.00863 -0.0636 0.3076 1.0000 6.000 0.9403 0.01804 0.00917 -0.0627 0.2735 1.0000 6.250 0.9611 0.01874 0.00975 -0.0618 0.2303 1.0000 6.500 0.9796 0.01971 0.01045 -0.0606 0.1754 1.0000 6.750 0.9976 0.02085 0.01130 -0.0595 0.1334 1.0000 7.000 1.0163 0.02194 0.01225 -0.0584 0.1074 1.0000 7.250 1.0348 0.02303 0.01327 -0.0573 0.0906 1.0000 7.500 1.0529 0.02413 0.01436 -0.0561 0.0778 1.0000 7.750 1.0709 0.02521 0.01558 -0.0548 0.0684 1.0000 8.000 1.0871 0.02648 0.01692 -0.0532 0.0615 1.0000 8.250 1.1033 0.02771 0.01821 -0.0518 0.0555 1.0000 8.500 1.1189 0.02906 0.01965 -0.0503 0.0507 1.0000 8.750 1.1355 0.03038 0.02112 -0.0489 0.0469 1.0000 9.000 1.1511 0.03182 0.02266 -0.0474 0.0441 1.0000 9.250 1.1662 0.03365 0.02452 -0.0461 0.0417 1.0000 9.500 1.1837 0.03515 0.02630 -0.0449 0.0390 1.0000 9.750 1.1993 0.03676 0.02810 -0.0435 0.0364 1.0000 10.000 1.2139 0.03854 0.03003 -0.0422 0.0347 1.0000 10.250 1.2256 0.04040 0.03196 -0.0408 0.0329 1.0000 10.500 1.2358 0.04267 0.03449 -0.0390 0.0313 1.0000 10.750 1.2429 0.04488 0.03709 -0.0370 0.0296 1.0000 11.000 1.2475 0.04747 0.03999 -0.0349 0.0286 1.0000 11.250 1.2483 0.05009 0.04290 -0.0327 0.0276 1.0000 11.500 1.2463 0.05265 0.04570 -0.0307 0.0268 1.0000 11.750 1.2434 0.05514 0.04837 -0.0290 0.0259 1.0000 12.000 1.2397 0.05780 0.05117 -0.0277 0.0252 1.0000 12.250 1.2335 0.06112 0.05461 -0.0268 0.0244 1.0000 12.500 1.2199 0.06532 0.05908 -0.0263 0.0241 1.0000 12.750 1.2031 0.07006 0.06414 -0.0265 0.0239 1.0000 13.000 1.1845 0.07544 0.06980 -0.0278 0.0237 1.0000 13.250 1.1641 0.08160 0.07622 -0.0302 0.0237 1.0000 13.500 1.1430 0.08857 0.08343 -0.0338 0.0237 1.0000 13.750 1.1211 0.09649 0.09154 -0.0386 0.0239 1.0000 14.000 1.0984 0.10549 0.10071 -0.0445 0.0241 1.0000