MH 91 14.98% (mh91-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 91 14.98% (mh91-il) Reynolds number: 100,000 Max Cl/Cd: 40.06 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh91-il-100000-n5.txt Download as CSV file: xf-mh91-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 91 14.98%
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7090 0.08794 0.08254 -0.0120 1.0000 0.0220
-12.500 -0.7331 0.07999 0.07444 -0.0176 1.0000 0.0219
-12.250 -0.7573 0.07320 0.06745 -0.0219 1.0000 0.0218
-12.000 -0.7786 0.06765 0.06169 -0.0246 1.0000 0.0218
-11.750 -0.7907 0.06358 0.05747 -0.0258 1.0000 0.0216
-11.500 -0.8111 0.05923 0.05284 -0.0262 1.0000 0.0217
-11.250 -0.8224 0.05589 0.04930 -0.0256 1.0000 0.0217
-11.000 -0.8345 0.05269 0.04582 -0.0241 1.0000 0.0218
-10.750 -0.8439 0.04979 0.04263 -0.0220 1.0000 0.0219
-10.500 -0.8474 0.04723 0.03980 -0.0198 1.0000 0.0219
-10.250 -0.8478 0.04475 0.03701 -0.0174 1.0000 0.0220
-10.000 -0.8394 0.04252 0.03462 -0.0159 1.0000 0.0222
-9.750 -0.8277 0.04048 0.03243 -0.0146 1.0000 0.0225
-9.500 -0.8138 0.03857 0.03037 -0.0135 1.0000 0.0228
-9.250 -0.7978 0.03675 0.02840 -0.0124 1.0000 0.0232
-9.000 -0.7798 0.03499 0.02648 -0.0115 1.0000 0.0236
-8.750 -0.7604 0.03329 0.02464 -0.0107 1.0000 0.0243
-8.500 -0.7395 0.03169 0.02289 -0.0100 1.0000 0.0249
-8.250 -0.7181 0.03021 0.02127 -0.0092 1.0000 0.0257
-8.000 -0.6991 0.02901 0.02011 -0.0084 1.0000 0.0270
-7.750 -0.6795 0.02795 0.01904 -0.0076 1.0000 0.0284
-7.500 -0.6600 0.02689 0.01789 -0.0067 1.0000 0.0304
-7.250 -0.6420 0.02588 0.01696 -0.0058 0.9924 0.0318
-7.000 -0.6096 0.02472 0.01571 -0.0074 0.9560 0.0342
-6.750 -0.5815 0.02366 0.01459 -0.0081 0.9302 0.0370
-6.500 -0.5585 0.02283 0.01368 -0.0075 0.9068 0.0415
-6.250 -0.5394 0.02211 0.01285 -0.0060 0.8855 0.0471
-6.000 -0.5226 0.02134 0.01207 -0.0040 0.8665 0.0549
-5.750 -0.5063 0.02052 0.01129 -0.0020 0.8490 0.0684
-5.500 -0.4905 0.01959 0.01054 0.0001 0.8327 0.0977
-5.250 -0.4766 0.01847 0.00984 0.0022 0.8171 0.1693
-5.000 -0.4628 0.01746 0.00935 0.0044 0.8025 0.2668
-4.750 -0.4470 0.01676 0.00900 0.0066 0.7885 0.3514
-4.500 -0.4297 0.01623 0.00875 0.0088 0.7750 0.4218
-4.250 -0.4104 0.01584 0.00857 0.0107 0.7607 0.4850
-4.000 -0.3898 0.01556 0.00845 0.0126 0.7472 0.5412
-3.750 -0.3677 0.01538 0.00838 0.0144 0.7343 0.5892
-3.500 -0.3438 0.01529 0.00830 0.0160 0.7215 0.6272
-3.250 -0.3178 0.01527 0.00828 0.0170 0.7076 0.6567
-3.000 -0.2919 0.01528 0.00822 0.0181 0.6944 0.6829
-2.750 -0.2652 0.01535 0.00820 0.0192 0.6820 0.7060
-2.500 -0.2385 0.01542 0.00817 0.0201 0.6686 0.7274
-2.250 -0.2117 0.01550 0.00815 0.0209 0.6551 0.7466
-2.000 -0.1844 0.01560 0.00813 0.0216 0.6424 0.7632
-1.750 -0.1568 0.01571 0.00809 0.0224 0.6301 0.7780
-1.500 -0.1291 0.01581 0.00809 0.0229 0.6163 0.7920
-1.250 -0.1025 0.01590 0.00806 0.0236 0.6035 0.8058
-1.000 -0.0751 0.01601 0.00804 0.0242 0.5912 0.8182
-0.750 -0.0451 0.01616 0.00806 0.0244 0.5784 0.8284
-0.500 -0.0187 0.01625 0.00805 0.0250 0.5653 0.8406
-0.250 0.0122 0.01640 0.00809 0.0250 0.5525 0.8499
0.000 0.0405 0.01652 0.00807 0.0253 0.5410 0.8603
0.250 0.0704 0.01666 0.00813 0.0252 0.5275 0.8701
0.500 0.1016 0.01680 0.00817 0.0249 0.5148 0.8789
0.750 0.1319 0.01694 0.00818 0.0248 0.5032 0.8881
1.000 0.1635 0.01706 0.00821 0.0243 0.4907 0.8959
1.250 0.1968 0.01719 0.00827 0.0234 0.4782 0.9031
1.500 0.2252 0.01730 0.00827 0.0233 0.4672 0.9114
1.750 0.2614 0.01743 0.00830 0.0218 0.4552 0.9167
2.000 0.2886 0.01754 0.00836 0.0218 0.4438 0.9253
2.250 0.3255 0.01766 0.00839 0.0201 0.4328 0.9298
2.500 0.3609 0.01779 0.00844 0.0185 0.4216 0.9352
2.750 0.3890 0.01792 0.00854 0.0183 0.4114 0.9428
3.000 0.4268 0.01806 0.00857 0.0162 0.4013 0.9468
3.250 0.4604 0.01820 0.00871 0.0148 0.3906 0.9526
3.500 0.4916 0.01836 0.00880 0.0139 0.3816 0.9586
3.750 0.5277 0.01851 0.00894 0.0120 0.3717 0.9632
4.000 0.5590 0.01870 0.00909 0.0110 0.3630 0.9694
4.250 0.5938 0.01886 0.00923 0.0093 0.3541 0.9739
4.500 0.6276 0.01906 0.00943 0.0078 0.3456 0.9790
4.750 0.6601 0.01926 0.00961 0.0064 0.3374 0.9841
5.000 0.6946 0.01948 0.00983 0.0047 0.3296 0.9885
5.250 0.7271 0.01972 0.01009 0.0033 0.3218 0.9934
5.500 0.7607 0.01996 0.01032 0.0016 0.3145 0.9977
5.750 0.7871 0.02024 0.01066 0.0013 0.3072 1.0000
6.000 0.8059 0.02054 0.01090 0.0026 0.3020 1.0000
6.250 0.8243 0.02089 0.01134 0.0038 0.2957 1.0000
6.500 0.8423 0.02122 0.01171 0.0051 0.2898 1.0000
7.000 0.8771 0.02197 0.01253 0.0080 0.2788 1.0000
7.250 0.8940 0.02236 0.01295 0.0095 0.2735 1.0000
7.500 0.9110 0.02274 0.01328 0.0111 0.2690 1.0000
7.750 0.9262 0.02321 0.01389 0.0128 0.2632 1.0000
8.000 0.9417 0.02364 0.01437 0.0145 0.2579 1.0000
8.250 0.9579 0.02405 0.01475 0.0162 0.2536 1.0000
8.500 0.9719 0.02459 0.01541 0.0180 0.2482 1.0000
8.750 0.9863 0.02508 0.01597 0.0198 0.2429 1.0000
9.000 1.0020 0.02552 0.01639 0.0215 0.2384 1.0000
9.250 1.0155 0.02612 0.01710 0.0233 0.2333 1.0000
9.500 1.0290 0.02669 0.01776 0.0250 0.2280 1.0000
9.750 1.0444 0.02718 0.01824 0.0266 0.2235 1.0000
10.000 1.0577 0.02786 0.01902 0.0282 0.2185 1.0000
10.250 1.0702 0.02855 0.01984 0.0298 0.2133 1.0000
10.500 1.0845 0.02914 0.02044 0.0312 0.2089 1.0000
10.750 1.0966 0.02990 0.02127 0.0328 0.2044 1.0000
11.000 1.1055 0.03079 0.02232 0.0345 0.1995 1.0000
11.250 1.1154 0.03153 0.02310 0.0362 0.1952 1.0000
11.500 1.1251 0.03229 0.02386 0.0379 0.1914 1.0000
11.750 1.1255 0.03358 0.02534 0.0399 0.1869 1.0000
12.000 1.1301 0.03476 0.02661 0.0413 0.1827 1.0000
12.250 1.1389 0.03575 0.02761 0.0423 0.1789 1.0000
12.500 1.1397 0.03745 0.02945 0.0433 0.1749 1.0000
12.750 1.1391 0.03937 0.03153 0.0439 0.1707 1.0000
13.000 1.1426 0.04100 0.03321 0.0444 0.1668 1.0000
13.250 1.1497 0.04246 0.03466 0.0447 0.1633 1.0000
13.500 1.1397 0.04562 0.03806 0.0444 0.1594 1.0000
13.750 1.1348 0.04844 0.04103 0.0440 0.1556 1.0000
14.000 1.1380 0.05048 0.04308 0.0438 0.1521 1.0000
14.250 1.1345 0.05338 0.04607 0.0431 0.1488 1.0000
14.500 1.1140 0.05853 0.05145 0.0412 0.1454 1.0000
14.750 1.1003 0.06304 0.05609 0.0393 0.1420 1.0000
15.000 1.1055 0.06513 0.05818 0.0388 0.1387 1.0000
15.250 1.0890 0.07036 0.06353 0.0365 0.1357 1.0000
15.500 0.9233 0.10108 0.09463 0.0200 0.1287 1.0000
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Polar data table (+)
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