XFOIL Version 6.96 Calculated polar for: S3014-095-85 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.7505 0.03525 0.03315 -0.0544 0.9600 0.0061 -10.000 -0.7545 0.03091 0.02838 -0.0536 0.9305 0.0062 -9.750 -0.7439 0.02882 0.02603 -0.0525 0.9161 0.0063 -9.500 -0.7304 0.02690 0.02385 -0.0516 0.9047 0.0063 -9.250 -0.7249 0.02312 0.01957 -0.0502 0.8939 0.0066 -9.000 -0.7060 0.02180 0.01806 -0.0494 0.8860 0.0068 -8.750 -0.6838 0.02096 0.01709 -0.0490 0.8788 0.0069 -8.250 -0.6371 0.01964 0.01553 -0.0481 0.8656 0.0072 -8.000 -0.6136 0.01888 0.01464 -0.0477 0.8594 0.0074 -7.750 -0.5899 0.01806 0.01368 -0.0473 0.8536 0.0076 -7.500 -0.5653 0.01743 0.01292 -0.0469 0.8475 0.0079 -7.250 -0.5406 0.01677 0.01212 -0.0465 0.8420 0.0082 -7.000 -0.5157 0.01603 0.01124 -0.0461 0.8362 0.0085 -6.750 -0.4907 0.01532 0.01040 -0.0457 0.8304 0.0088 -6.500 -0.4654 0.01457 0.00951 -0.0454 0.8249 0.0091 -6.250 -0.4398 0.01392 0.00873 -0.0450 0.8191 0.0093 -6.000 -0.4140 0.01332 0.00802 -0.0446 0.8138 0.0094 -5.750 -0.3878 0.01276 0.00736 -0.0444 0.8080 0.0096 -5.500 -0.3616 0.01224 0.00674 -0.0440 0.8022 0.0097 -5.250 -0.3350 0.01179 0.00622 -0.0438 0.7968 0.0098 -5.000 -0.3081 0.01146 0.00582 -0.0436 0.7907 0.0099 -4.750 -0.2833 0.01054 0.00477 -0.0430 0.7850 0.0104 -4.500 -0.2571 0.00998 0.00415 -0.0427 0.7786 0.0108 -4.250 -0.2304 0.00962 0.00370 -0.0424 0.7722 0.0112 -4.000 -0.2032 0.00931 0.00336 -0.0423 0.7654 0.0116 -3.750 -0.1759 0.00906 0.00305 -0.0421 0.7585 0.0121 -3.500 -0.1484 0.00882 0.00277 -0.0419 0.7512 0.0126 -3.250 -0.1210 0.00861 0.00249 -0.0417 0.7438 0.0130 -3.000 -0.0933 0.00842 0.00225 -0.0416 0.7358 0.0134 -2.750 -0.0657 0.00825 0.00203 -0.0415 0.7277 0.0137 -2.500 -0.0379 0.00810 0.00184 -0.0414 0.7184 0.0140 -2.250 -0.0102 0.00798 0.00167 -0.0412 0.7080 0.0144 -2.000 0.0176 0.00789 0.00152 -0.0411 0.6958 0.0148 -1.750 0.0453 0.00781 0.00137 -0.0410 0.6825 0.0154 -1.500 0.0730 0.00773 0.00122 -0.0409 0.6683 0.0170 -1.250 0.1007 0.00766 0.00111 -0.0408 0.6530 0.0207 -1.000 0.1276 0.00745 0.00100 -0.0406 0.6367 0.0668 -0.750 0.1546 0.00729 0.00093 -0.0404 0.6207 0.1126 -0.500 0.1816 0.00713 0.00089 -0.0403 0.6052 0.1667 -0.250 0.2083 0.00694 0.00085 -0.0402 0.5900 0.2344 0.250 0.2588 0.00618 0.00085 -0.0396 0.5584 0.5146 0.500 0.2846 0.00600 0.00087 -0.0392 0.5417 0.6009 0.750 0.3104 0.00588 0.00089 -0.0388 0.5242 0.6732 1.000 0.3351 0.00573 0.00093 -0.0381 0.5064 0.7550 1.250 0.3591 0.00561 0.00099 -0.0372 0.4884 0.8314 1.500 0.3842 0.00552 0.00106 -0.0364 0.4688 0.9121 1.750 0.4328 0.00564 0.00115 -0.0409 0.4437 0.9676 2.000 0.4699 0.00584 0.00122 -0.0430 0.4176 0.9838 2.250 0.5044 0.00603 0.00130 -0.0446 0.3925 0.9929 2.500 0.5406 0.00623 0.00138 -0.0465 0.3669 0.9981 2.750 0.5720 0.00643 0.00148 -0.0475 0.3431 1.0000 3.000 0.5972 0.00664 0.00158 -0.0470 0.3216 1.0000 3.250 0.6223 0.00684 0.00169 -0.0465 0.3020 1.0000 3.500 0.6476 0.00703 0.00181 -0.0460 0.2848 1.0000 3.750 0.6726 0.00725 0.00195 -0.0455 0.2659 1.0000 4.000 0.6978 0.00745 0.00208 -0.0450 0.2506 1.0000 4.250 0.7229 0.00767 0.00222 -0.0445 0.2347 1.0000 4.750 0.7731 0.00809 0.00254 -0.0436 0.2078 1.0000 5.000 0.7982 0.00830 0.00271 -0.0431 0.1952 1.0000 5.250 0.8234 0.00850 0.00288 -0.0427 0.1847 1.0000 5.500 0.8480 0.00876 0.00307 -0.0422 0.1699 1.0000 5.750 0.8720 0.00910 0.00330 -0.0416 0.1495 1.0000 6.000 0.8964 0.00938 0.00354 -0.0410 0.1353 1.0000 6.250 0.9201 0.00975 0.00381 -0.0404 0.1161 1.0000 6.500 0.9436 0.01013 0.00409 -0.0398 0.0994 1.0000 6.750 0.9674 0.01049 0.00438 -0.0392 0.0851 1.0000 7.000 0.9908 0.01087 0.00470 -0.0386 0.0708 1.0000 7.250 1.0134 0.01134 0.00508 -0.0379 0.0546 1.0000 7.500 1.0356 0.01185 0.00550 -0.0371 0.0394 1.0000 7.750 1.0576 0.01236 0.00594 -0.0363 0.0267 1.0000 8.000 1.0764 0.01321 0.00665 -0.0351 0.0075 1.0000 8.250 1.0987 0.01367 0.00712 -0.0343 0.0052 1.0000 8.500 1.1214 0.01407 0.00757 -0.0336 0.0044 1.0000 8.750 1.1439 0.01448 0.00802 -0.0329 0.0041 1.0000 9.000 1.1658 0.01492 0.00851 -0.0321 0.0038 1.0000 9.250 1.1869 0.01542 0.00905 -0.0312 0.0035 1.0000 9.500 1.2074 0.01597 0.00965 -0.0302 0.0032 1.0000 9.750 1.2267 0.01659 0.01035 -0.0291 0.0030 1.0000 10.000 1.2455 0.01721 0.01103 -0.0279 0.0028 1.0000 10.250 1.2645 0.01778 0.01167 -0.0267 0.0028 1.0000 10.500 1.2824 0.01838 0.01234 -0.0255 0.0027 1.0000 10.750 1.2995 0.01900 0.01302 -0.0241 0.0026 1.0000 11.000 1.3149 0.01969 0.01378 -0.0225 0.0025 1.0000 11.250 1.3264 0.02041 0.01457 -0.0202 0.0025 1.0000 11.500 1.3357 0.02119 0.01544 -0.0177 0.0024 1.0000 11.750 1.3452 0.02202 0.01634 -0.0155 0.0023 1.0000 12.000 1.3536 0.02297 0.01737 -0.0133 0.0023 1.0000 12.250 1.3608 0.02406 0.01856 -0.0112 0.0022 1.0000 12.500 1.3676 0.02524 0.01984 -0.0093 0.0021 1.0000 12.750 1.3725 0.02664 0.02133 -0.0075 0.0021 1.0000 13.000 1.3788 0.02800 0.02278 -0.0060 0.0020 1.0000 13.250 1.3835 0.02955 0.02442 -0.0046 0.0020 1.0000 13.500 1.3888 0.03112 0.02607 -0.0035 0.0019 1.0000 13.750 1.3910 0.03306 0.02811 -0.0024 0.0019 1.0000 14.000 1.3891 0.03551 0.03067 -0.0015 0.0018 1.0000 14.250 1.3907 0.03774 0.03300 -0.0010 0.0018 1.0000 14.500 1.3905 0.04028 0.03565 -0.0007 0.0018 1.0000 14.750 1.3867 0.04337 0.03885 -0.0008 0.0018 1.0000 15.000 1.3815 0.04684 0.04244 -0.0012 0.0017 1.0000 15.250 1.3719 0.05106 0.04679 -0.0022 0.0017 1.0000 15.500 1.3685 0.05469 0.05052 -0.0032 0.0017 1.0000 15.750 1.3533 0.06026 0.05624 -0.0052 0.0017 1.0000 16.000 1.3446 0.06515 0.06125 -0.0072 0.0017 1.0000 16.250 1.3233 0.07236 0.06862 -0.0105 0.0017 1.0000 16.500 1.3076 0.07894 0.07533 -0.0136 0.0016 1.0000 16.750 1.2931 0.08556 0.08208 -0.0169 0.0017 1.0000 17.000 1.2774 0.09255 0.08919 -0.0203 0.0017 1.0000 17.250 1.2559 0.10089 0.09767 -0.0246 0.0017 1.0000 17.500 1.2388 0.10854 0.10543 -0.0285 0.0017 1.0000