USA 27 mod. AIRFOIL (usa27m2-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 27 mod. AIRFOIL (usa27m2-il) Reynolds number: 200,000 Max Cl/Cd: 62.9 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa27m2-il-200000-n5.txt Download as CSV file: xf-usa27m2-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 27 mod. AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2304 0.09952 0.09589 -0.0597 0.9824 0.0440
-9.250 -0.2213 0.09611 0.09248 -0.0622 0.9781 0.0452
-9.000 -0.2374 0.08741 0.08381 -0.0768 0.9697 0.0485
-8.750 -0.2190 0.08549 0.08189 -0.0743 0.9673 0.0491
-8.500 -0.2022 0.08315 0.07956 -0.0751 0.9639 0.0499
-8.250 -0.1871 0.07980 0.07620 -0.0786 0.9607 0.0510
-8.000 -0.2454 0.05745 0.05349 -0.0960 0.9389 0.0360
-7.750 -0.2292 0.05581 0.05187 -0.0964 0.9351 0.0363
-7.500 -0.2076 0.05438 0.05042 -0.0977 0.9325 0.0367
-7.250 -0.2109 0.04759 0.04337 -0.0984 0.9230 0.0350
-7.000 -0.2046 0.04132 0.03663 -0.0999 0.9177 0.0349
-6.750 -0.1993 0.03771 0.03268 -0.0982 0.9101 0.0348
-6.500 -0.1855 0.03447 0.02908 -0.0974 0.9040 0.0344
-6.250 -0.1624 0.03131 0.02548 -0.0979 0.9002 0.0341
-6.000 -0.1512 0.02936 0.02320 -0.0952 0.8899 0.0340
-5.750 -0.1223 0.02711 0.02056 -0.0958 0.8847 0.0339
-5.500 -0.1051 0.02564 0.01882 -0.0938 0.8745 0.0340
-5.250 -0.0739 0.02399 0.01685 -0.0946 0.8685 0.0340
-5.000 -0.0531 0.02291 0.01552 -0.0931 0.8578 0.0344
-4.750 -0.0193 0.02173 0.01403 -0.0942 0.8513 0.0350
-4.500 0.0023 0.02093 0.01304 -0.0928 0.8407 0.0353
-4.250 0.0341 0.01996 0.01187 -0.0934 0.8335 0.0354
-4.000 0.0594 0.01921 0.01097 -0.0927 0.8230 0.0355
-3.750 0.0881 0.01847 0.01010 -0.0927 0.8130 0.0356
-3.500 0.1183 0.01779 0.00929 -0.0930 0.8022 0.0358
-3.250 0.1441 0.01726 0.00866 -0.0924 0.7892 0.0360
-3.000 0.1708 0.01658 0.00796 -0.0920 0.7756 0.0363
-2.750 0.1973 0.01601 0.00736 -0.0916 0.7599 0.0366
-2.500 0.2235 0.01554 0.00684 -0.0911 0.7415 0.0370
-2.250 0.2495 0.01515 0.00639 -0.0906 0.7210 0.0375
-2.000 0.2748 0.01485 0.00600 -0.0899 0.6990 0.0385
-1.750 0.2997 0.01464 0.00567 -0.0892 0.6786 0.0397
-1.500 0.3239 0.01449 0.00538 -0.0883 0.6604 0.0406
-1.250 0.3477 0.01439 0.00514 -0.0873 0.6439 0.0412
-1.000 0.3715 0.01433 0.00494 -0.0864 0.6285 0.0417
-0.750 0.3950 0.01426 0.00476 -0.0854 0.6139 0.0425
-0.500 0.4183 0.01422 0.00460 -0.0843 0.5996 0.0436
-0.250 0.4415 0.01420 0.00449 -0.0833 0.5852 0.0450
0.000 0.4646 0.01418 0.00441 -0.0822 0.5709 0.0469
0.250 0.4874 0.01416 0.00435 -0.0811 0.5562 0.0502
0.500 0.5086 0.01398 0.00428 -0.0798 0.5410 0.0850
0.750 0.5278 0.01370 0.00438 -0.0782 0.5251 0.2118
1.000 0.5488 0.01373 0.00444 -0.0768 0.5084 0.2501
1.250 0.5697 0.01382 0.00449 -0.0754 0.4918 0.2771
1.500 0.5901 0.01390 0.00456 -0.0740 0.4766 0.3076
1.750 0.6107 0.01402 0.00463 -0.0725 0.4627 0.3317
2.000 0.6303 0.01408 0.00471 -0.0710 0.4503 0.3745
2.250 0.6470 0.01366 0.00475 -0.0690 0.4394 0.5331
2.750 0.8210 0.01425 0.00596 -0.0941 0.4099 0.9973
3.000 0.8508 0.01450 0.00610 -0.0948 0.4028 1.0000
3.250 0.8696 0.01470 0.00624 -0.0930 0.3972 1.0000
3.500 0.8885 0.01489 0.00639 -0.0913 0.3910 1.0000
3.750 0.9063 0.01512 0.00654 -0.0894 0.3852 1.0000
4.000 0.9249 0.01533 0.00670 -0.0877 0.3802 1.0000
4.250 0.9440 0.01552 0.00688 -0.0860 0.3756 1.0000
4.500 0.9623 0.01573 0.00706 -0.0842 0.3712 1.0000
4.750 0.9801 0.01598 0.00725 -0.0824 0.3670 1.0000
5.000 0.9987 0.01618 0.00746 -0.0806 0.3626 1.0000
5.250 1.0163 0.01638 0.00766 -0.0787 0.3571 1.0000
5.500 1.0329 0.01663 0.00786 -0.0766 0.3519 1.0000
5.750 1.0500 0.01689 0.00809 -0.0746 0.3479 1.0000
6.000 1.0678 0.01708 0.00833 -0.0728 0.3437 1.0000
6.250 1.0841 0.01729 0.00856 -0.0707 0.3394 1.0000
6.500 1.0997 0.01753 0.00879 -0.0684 0.3356 1.0000
6.750 1.1152 0.01782 0.00905 -0.0662 0.3321 1.0000
7.000 1.1323 0.01804 0.00933 -0.0643 0.3283 1.0000
7.250 1.1491 0.01827 0.00961 -0.0623 0.3241 1.0000
7.500 1.1654 0.01855 0.00991 -0.0603 0.3199 1.0000
7.750 1.1812 0.01887 0.01023 -0.0583 0.3160 1.0000
8.000 1.1985 0.01916 0.01057 -0.0566 0.3118 1.0000
8.250 1.2149 0.01945 0.01093 -0.0547 0.3061 1.0000
8.500 1.2289 0.01982 0.01128 -0.0525 0.3000 1.0000
8.750 1.2439 0.02015 0.01169 -0.0505 0.2920 1.0000
9.000 1.2560 0.02059 0.01211 -0.0481 0.2832 1.0000
9.250 1.2709 0.02098 0.01257 -0.0463 0.2733 1.0000
9.500 1.2840 0.02148 0.01307 -0.0442 0.2641 1.0000
9.750 1.2970 0.02201 0.01363 -0.0423 0.2538 1.0000
10.000 1.3102 0.02258 0.01423 -0.0404 0.2424 1.0000
10.250 1.3205 0.02330 0.01493 -0.0382 0.2281 1.0000
10.500 1.3288 0.02418 0.01575 -0.0359 0.2125 1.0000
10.750 1.3364 0.02516 0.01670 -0.0336 0.1994 1.0000
11.000 1.3439 0.02621 0.01773 -0.0315 0.1895 1.0000
11.250 1.3497 0.02742 0.01891 -0.0293 0.1808 1.0000
11.500 1.3568 0.02860 0.02011 -0.0274 0.1726 1.0000
11.750 1.3607 0.03004 0.02155 -0.0253 0.1641 1.0000
12.000 1.3648 0.03153 0.02306 -0.0234 0.1549 1.0000
12.250 1.3703 0.03299 0.02456 -0.0217 0.1471 1.0000
12.500 1.3740 0.03465 0.02625 -0.0201 0.1382 1.0000
12.750 1.3794 0.03625 0.02790 -0.0187 0.1272 1.0000
13.000 1.3750 0.03872 0.03029 -0.0170 0.1039 1.0000
13.250 1.3542 0.04289 0.03423 -0.0150 0.0760 1.0000
13.500 1.3290 0.04787 0.03907 -0.0135 0.0415 1.0000
13.750 1.3104 0.05256 0.04373 -0.0128 0.0283 1.0000
14.000 1.3014 0.05643 0.04769 -0.0126 0.0249 1.0000
14.250 1.2947 0.06014 0.05151 -0.0125 0.0232 1.0000
14.750 1.2825 0.06775 0.05938 -0.0129 0.0212 1.0000
15.000 1.2764 0.07170 0.06346 -0.0134 0.0205 1.0000
15.250 1.2693 0.07587 0.06777 -0.0140 0.0200 1.0000
15.500 1.2612 0.08027 0.07232 -0.0148 0.0196 1.0000
15.750 1.2523 0.08488 0.07707 -0.0158 0.0192 1.0000
16.000 1.2426 0.08969 0.08202 -0.0169 0.0189 1.0000
16.250 1.2320 0.09470 0.08717 -0.0181 0.0186 1.0000
16.500 1.2209 0.09988 0.09250 -0.0196 0.0184 1.0000
16.750 1.2092 0.10525 0.09801 -0.0211 0.0181 1.0000
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