XFOIL Version 6.96 Calculated polar for: S4094 (root airfoil designed for and used on the 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.4932 0.09573 0.09429 0.0052 1.0004 0.0139 -9.250 -0.4949 0.09139 0.08996 0.0039 1.0004 0.0141 -7.500 -0.6288 0.02907 0.02564 -0.0317 1.0004 0.0136 -7.250 -0.6027 0.02568 0.02201 -0.0327 1.0004 0.0128 -7.000 -0.5746 0.02302 0.01899 -0.0336 1.0004 0.0129 -6.750 -0.5457 0.02111 0.01681 -0.0344 1.0004 0.0130 -6.500 -0.5164 0.01958 0.01505 -0.0350 1.0004 0.0131 -6.250 -0.4869 0.01834 0.01363 -0.0356 1.0004 0.0132 -5.750 -0.4273 0.01526 0.01018 -0.0369 1.0004 0.0137 -5.500 -0.3975 0.01400 0.00884 -0.0375 1.0004 0.0142 -5.250 -0.3677 0.01325 0.00805 -0.0380 1.0004 0.0146 -5.000 -0.3377 0.01265 0.00741 -0.0385 1.0004 0.0150 -4.750 -0.3077 0.01212 0.00685 -0.0390 1.0004 0.0155 -4.500 -0.2760 0.01180 0.00649 -0.0398 0.9699 0.0160 -4.250 -0.2523 0.01172 0.00625 -0.0385 0.9123 0.0163 -4.000 -0.2259 0.01153 0.00589 -0.0379 0.8729 0.0167 -3.750 -0.1976 0.01133 0.00553 -0.0378 0.8408 0.0171 -3.500 -0.1687 0.01116 0.00523 -0.0379 0.8128 0.0175 -3.250 -0.1391 0.01081 0.00472 -0.0382 0.7879 0.0191 -3.000 -0.1095 0.01064 0.00445 -0.0384 0.7647 0.0205 -2.750 -0.0799 0.01052 0.00422 -0.0387 0.7438 0.0222 -2.500 -0.0501 0.01036 0.00400 -0.0391 0.7242 0.0274 -2.250 -0.0201 0.01005 0.00382 -0.0396 0.7061 0.0705 -2.000 0.0096 0.00986 0.00371 -0.0400 0.6894 0.1089 -1.750 0.0395 0.00965 0.00362 -0.0406 0.6738 0.1601 -1.250 0.0991 0.00923 0.00349 -0.0416 0.6447 0.2862 -1.000 0.1290 0.00901 0.00346 -0.0422 0.6314 0.3615 -0.750 0.1588 0.00879 0.00345 -0.0428 0.6184 0.4471 -0.500 0.1886 0.00838 0.00348 -0.0434 0.6061 0.5990 -0.250 0.2179 0.00807 0.00352 -0.0438 0.5940 0.7268 0.000 0.2410 0.00759 0.00356 -0.0424 0.5822 0.9054 0.250 0.2676 0.00713 0.00315 -0.0418 0.5703 0.9996 0.500 0.2974 0.00721 0.00315 -0.0422 0.5582 0.9996 0.750 0.3273 0.00729 0.00315 -0.0426 0.5459 0.9996 1.000 0.3570 0.00738 0.00316 -0.0429 0.5329 0.9996 1.250 0.3868 0.00747 0.00318 -0.0433 0.5197 0.9996 1.500 0.4165 0.00757 0.00320 -0.0437 0.5058 0.9996 1.750 0.4462 0.00767 0.00323 -0.0441 0.4906 0.9996 2.000 0.4759 0.00778 0.00327 -0.0445 0.4746 0.9996 2.250 0.5055 0.00791 0.00332 -0.0449 0.4576 0.9996 2.500 0.5350 0.00804 0.00338 -0.0452 0.4397 0.9996 2.750 0.5646 0.00819 0.00345 -0.0456 0.4221 0.9996 3.000 0.5940 0.00836 0.00352 -0.0460 0.4041 0.9996 3.250 0.6235 0.00851 0.00361 -0.0464 0.3869 0.9996 3.500 0.6529 0.00868 0.00371 -0.0468 0.3692 0.9996 3.750 0.6822 0.00886 0.00382 -0.0472 0.3520 0.9996 4.000 0.7115 0.00905 0.00393 -0.0476 0.3346 0.9996 4.500 0.7700 0.00946 0.00420 -0.0484 0.3003 0.9996 4.750 0.7992 0.00966 0.00435 -0.0488 0.2845 0.9996 5.000 0.8283 0.00988 0.00451 -0.0492 0.2687 0.9996 5.250 0.8573 0.01011 0.00468 -0.0496 0.2523 0.9996 5.500 0.8863 0.01034 0.00486 -0.0499 0.2378 0.9996 5.750 0.9152 0.01059 0.00505 -0.0503 0.2223 0.9996 6.000 0.9440 0.01085 0.00526 -0.0507 0.2075 0.9996 6.250 0.9727 0.01114 0.00548 -0.0511 0.1916 0.9996 6.500 1.0013 0.01144 0.00572 -0.0514 0.1763 0.9996 6.750 1.0299 0.01173 0.00597 -0.0518 0.1636 0.9996 7.000 1.0582 0.01207 0.00624 -0.0521 0.1485 0.9996 7.250 1.0864 0.01243 0.00654 -0.0525 0.1334 0.9996 7.500 1.1146 0.01279 0.00684 -0.0528 0.1202 0.9996 7.750 1.1427 0.01314 0.00716 -0.0531 0.1092 0.9996 8.000 1.1706 0.01352 0.00749 -0.0535 0.0975 0.9996 8.250 1.1982 0.01395 0.00786 -0.0538 0.0850 0.9996 8.500 1.2258 0.01436 0.00824 -0.0540 0.0752 0.9996 8.750 1.2532 0.01479 0.00865 -0.0543 0.0663 0.9996 9.000 1.2802 0.01528 0.00909 -0.0545 0.0568 0.9996 9.250 1.3071 0.01577 0.00954 -0.0547 0.0488 0.9996 9.500 1.3339 0.01624 0.01000 -0.0549 0.0420 0.9996 9.750 1.3602 0.01679 0.01053 -0.0550 0.0348 0.9996 10.000 1.3858 0.01746 0.01114 -0.0551 0.0262 0.9996 10.250 1.4092 0.01855 0.01211 -0.0550 0.0126 0.9996 10.500 1.4332 0.01944 0.01300 -0.0549 0.0085 0.9996 10.750 1.4572 0.02025 0.01386 -0.0547 0.0072 0.9996 11.000 1.4813 0.02093 0.01461 -0.0545 0.0067 0.9996 11.250 1.5047 0.02167 0.01545 -0.0542 0.0063 0.9996 11.500 1.5269 0.02254 0.01638 -0.0538 0.0059 0.9996 11.750 1.5474 0.02358 0.01752 -0.0532 0.0056 0.9996 12.000 1.5648 0.02493 0.01901 -0.0523 0.0053 0.9996 12.250 1.5836 0.02592 0.02009 -0.0514 0.0052 0.9996 12.500 1.6012 0.02694 0.02121 -0.0505 0.0051 0.9996 12.750 1.6168 0.02808 0.02246 -0.0493 0.0050 0.9996 13.000 1.6298 0.02932 0.02381 -0.0478 0.0049 0.9996 13.250 1.6396 0.03073 0.02533 -0.0459 0.0048 0.9996 13.500 1.6453 0.03230 0.02702 -0.0437 0.0047 0.9996 13.750 1.6395 0.03428 0.02912 -0.0399 0.0046 0.9996 14.000 1.6332 0.03684 0.03182 -0.0375 0.0046 0.9996 14.250 1.6281 0.04000 0.03511 -0.0367 0.0045 0.9996 14.500 1.6230 0.04371 0.03896 -0.0369 0.0045 0.9996 14.750 1.6161 0.04799 0.04339 -0.0377 0.0044 0.9996 15.000 1.6073 0.05283 0.04836 -0.0391 0.0044 0.9996 15.250 1.5957 0.05824 0.05392 -0.0409 0.0043 0.9996 15.500 1.5809 0.06420 0.06002 -0.0430 0.0043 0.9996 15.750 1.5634 0.07072 0.06669 -0.0453 0.0043 0.9996 16.000 1.5435 0.07770 0.07382 -0.0479 0.0043 0.9996 16.250 1.5220 0.08509 0.08136 -0.0507 0.0043 0.9996 16.500 1.4989 0.09293 0.08933 -0.0538 0.0043 0.9996 16.750 1.4762 0.10097 0.09751 -0.0572 0.0043 0.9996