MH 95 15.86% (mh95-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 95 15.86% (mh95-il) Reynolds number: 200,000 Max Cl/Cd: 45.57 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh95-il-200000-n5.txt Download as CSV file: xf-mh95-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 95 15.86%
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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.6662 0.09631 0.09151 -0.0615 1.0000 0.0186
-15.250 -0.6905 0.08830 0.08336 -0.0659 1.0000 0.0184
-15.000 -0.7166 0.08067 0.07555 -0.0700 1.0000 0.0184
-14.750 -0.7405 0.07417 0.06888 -0.0731 1.0000 0.0183
-14.500 -0.7650 0.06833 0.06283 -0.0752 1.0000 0.0183
-14.250 -0.7860 0.06360 0.05790 -0.0762 1.0000 0.0184
-14.000 -0.8028 0.05972 0.05385 -0.0762 1.0000 0.0184
-13.750 -0.8208 0.05612 0.05005 -0.0756 1.0000 0.0184
-13.500 -0.8362 0.05304 0.04678 -0.0742 1.0000 0.0185
-13.250 -0.8477 0.05049 0.04406 -0.0724 1.0000 0.0185
-13.000 -0.8586 0.04817 0.04157 -0.0701 1.0000 0.0185
-12.750 -0.8702 0.04597 0.03917 -0.0674 1.0000 0.0186
-12.500 -0.8766 0.04420 0.03726 -0.0646 1.0000 0.0186
-12.250 -0.8800 0.04255 0.03553 -0.0618 1.0000 0.0187
-12.000 -0.8831 0.04109 0.03399 -0.0588 1.0000 0.0188
-11.750 -0.8856 0.03978 0.03261 -0.0557 1.0000 0.0189
-11.500 -0.8878 0.03854 0.03127 -0.0523 1.0000 0.0190
-11.250 -0.8897 0.03741 0.03005 -0.0488 1.0000 0.0191
-11.000 -0.8915 0.03635 0.02891 -0.0452 1.0000 0.0193
-10.750 -0.8862 0.03524 0.02771 -0.0428 0.9992 0.0194
-10.500 -0.8663 0.03391 0.02627 -0.0430 0.9967 0.0197
-10.250 -0.8449 0.03269 0.02494 -0.0432 0.9941 0.0200
-10.000 -0.8242 0.03152 0.02366 -0.0432 0.9914 0.0203
-9.750 -0.8035 0.03041 0.02245 -0.0430 0.9882 0.0207
-9.500 -0.7805 0.02937 0.02131 -0.0432 0.9853 0.0211
-9.250 -0.7557 0.02838 0.02021 -0.0436 0.9829 0.0215
-9.000 -0.7355 0.02750 0.01923 -0.0431 0.9792 0.0220
-8.750 -0.7171 0.02662 0.01838 -0.0424 0.9748 0.0226
-8.500 -0.6929 0.02588 0.01763 -0.0427 0.9715 0.0233
-8.250 -0.6656 0.02507 0.01677 -0.0435 0.9692 0.0242
-8.000 -0.6511 0.02440 0.01605 -0.0415 0.9629 0.0249
-7.750 -0.6274 0.02364 0.01523 -0.0414 0.9590 0.0257
-7.500 -0.6013 0.02281 0.01440 -0.0420 0.9561 0.0265
-7.250 -0.5843 0.02218 0.01375 -0.0404 0.9503 0.0273
-7.000 -0.5626 0.02155 0.01308 -0.0398 0.9453 0.0284
-6.750 -0.5347 0.02090 0.01238 -0.0403 0.9422 0.0298
-6.500 -0.5043 0.02022 0.01169 -0.0414 0.9399 0.0318
-6.250 -0.4925 0.01981 0.01123 -0.0385 0.9315 0.0340
-6.000 -0.4653 0.01920 0.01064 -0.0387 0.9277 0.0382
-5.750 -0.4347 0.01857 0.01004 -0.0396 0.9251 0.0452
-5.500 -0.4193 0.01808 0.00959 -0.0375 0.9177 0.0543
-5.250 -0.3956 0.01741 0.00906 -0.0370 0.9127 0.0771
-4.750 -0.3516 0.01584 0.00806 -0.0357 0.9028 0.1824
-4.500 -0.3318 0.01513 0.00764 -0.0346 0.8966 0.2428
-4.250 -0.3054 0.01430 0.00716 -0.0348 0.8931 0.3195
-4.000 -0.2904 0.01361 0.00684 -0.0326 0.8857 0.3957
-3.750 -0.2716 0.01286 0.00654 -0.0309 0.8792 0.4849
-3.500 -0.2429 0.01231 0.00639 -0.0309 0.8757 0.5694
-3.250 -0.2240 0.01216 0.00644 -0.0287 0.8673 0.6214
-3.000 -0.1938 0.01205 0.00639 -0.0287 0.8617 0.6553
-2.750 -0.1563 0.01191 0.00622 -0.0302 0.8580 0.6755
-2.500 -0.1348 0.01189 0.00618 -0.0286 0.8482 0.6901
-2.250 -0.0995 0.01177 0.00602 -0.0297 0.8425 0.7032
-2.000 -0.0718 0.01170 0.00589 -0.0295 0.8336 0.7158
-1.750 -0.0376 0.01164 0.00581 -0.0303 0.8258 0.7254
-1.500 -0.0084 0.01159 0.00570 -0.0303 0.8157 0.7360
-1.250 0.0278 0.01153 0.00560 -0.0315 0.8067 0.7451
-1.000 0.0557 0.01150 0.00551 -0.0313 0.7940 0.7539
-0.750 0.0878 0.01149 0.00546 -0.0317 0.7814 0.7609
-0.500 0.1197 0.01144 0.00530 -0.0323 0.7676 0.7690
-0.250 0.1514 0.01146 0.00526 -0.0327 0.7527 0.7743
0.000 0.1798 0.01151 0.00524 -0.0324 0.7360 0.7805
0.250 0.2070 0.01152 0.00514 -0.0322 0.7188 0.7883
0.500 0.2344 0.01162 0.00519 -0.0317 0.7012 0.7929
0.750 0.2608 0.01171 0.00520 -0.0311 0.6829 0.7985
1.000 0.2858 0.01178 0.00516 -0.0305 0.6644 0.8050
1.250 0.3105 0.01188 0.00518 -0.0296 0.6451 0.8095
1.500 0.3343 0.01200 0.00524 -0.0285 0.6254 0.8139
1.750 0.3573 0.01212 0.00526 -0.0274 0.6048 0.8191
2.000 0.3797 0.01221 0.00525 -0.0264 0.5838 0.8250
2.250 0.4015 0.01236 0.00532 -0.0250 0.5622 0.8285
2.500 0.4226 0.01252 0.00539 -0.0235 0.5402 0.8326
2.750 0.4432 0.01268 0.00545 -0.0220 0.5186 0.8374
3.000 0.4636 0.01283 0.00549 -0.0206 0.4954 0.8428
3.250 0.4826 0.01303 0.00559 -0.0188 0.4713 0.8465
3.500 0.5004 0.01325 0.00570 -0.0167 0.4467 0.8507
3.750 0.5184 0.01347 0.00581 -0.0149 0.4213 0.8556
4.000 0.5366 0.01369 0.00591 -0.0131 0.3978 0.8612
4.500 0.5703 0.01415 0.00621 -0.0089 0.3571 0.8697
4.750 0.5877 0.01436 0.00636 -0.0070 0.3396 0.8752
5.000 0.6051 0.01459 0.00652 -0.0052 0.3231 0.8805
5.250 0.6223 0.01481 0.00671 -0.0032 0.3079 0.8849
5.500 0.6400 0.01506 0.00691 -0.0014 0.2929 0.8905
5.750 0.6581 0.01533 0.00714 0.0002 0.2788 0.8967
6.000 0.6750 0.01560 0.00738 0.0022 0.2662 0.9017
6.250 0.6921 0.01590 0.00763 0.0040 0.2541 0.9078
6.500 0.7104 0.01617 0.00789 0.0055 0.2419 0.9142
6.750 0.7279 0.01646 0.00818 0.0072 0.2301 0.9206
7.000 0.7454 0.01680 0.00848 0.0088 0.2191 0.9282
7.250 0.7648 0.01714 0.00880 0.0100 0.2073 0.9347
7.500 0.7840 0.01748 0.00915 0.0112 0.1968 0.9429
7.750 0.8058 0.01789 0.00955 0.0118 0.1864 0.9504
8.000 0.8287 0.01834 0.00997 0.0120 0.1756 0.9589
8.250 0.8549 0.01882 0.01046 0.0115 0.1648 0.9668
8.500 0.8814 0.01938 0.01099 0.0108 0.1553 0.9752
8.750 0.9083 0.01993 0.01153 0.0099 0.1468 0.9860
9.000 0.9296 0.02046 0.01207 0.0101 0.1405 1.0000
9.250 0.9438 0.02097 0.01256 0.0116 0.1350 1.0000
9.500 0.9572 0.02160 0.01315 0.0132 0.1303 1.0000
9.750 0.9737 0.02214 0.01374 0.0144 0.1260 1.0000
10.000 0.9887 0.02278 0.01438 0.0156 0.1217 1.0000
10.250 1.0019 0.02353 0.01510 0.0171 0.1184 1.0000
10.500 1.0167 0.02423 0.01584 0.0183 0.1156 1.0000
10.750 1.0318 0.02493 0.01660 0.0194 0.1129 1.0000
11.000 1.0457 0.02571 0.01741 0.0207 0.1102 1.0000
11.250 1.0582 0.02657 0.01828 0.0220 0.1078 1.0000
11.500 1.0687 0.02758 0.01928 0.0234 0.1055 1.0000
11.750 1.0828 0.02843 0.02020 0.0244 0.1035 1.0000
12.000 1.0962 0.02932 0.02117 0.0254 0.1015 1.0000
12.250 1.1088 0.03028 0.02219 0.0265 0.0997 1.0000
12.500 1.1204 0.03131 0.02328 0.0275 0.0980 1.0000
12.750 1.1311 0.03243 0.02444 0.0285 0.0965 1.0000
13.000 1.1407 0.03368 0.02569 0.0296 0.0949 1.0000
13.250 1.1508 0.03493 0.02697 0.0305 0.0934 1.0000
13.500 1.1620 0.03611 0.02826 0.0313 0.0920 1.0000
13.750 1.1725 0.03736 0.02962 0.0320 0.0905 1.0000
14.000 1.1823 0.03871 0.03105 0.0327 0.0892 1.0000
14.250 1.1912 0.04013 0.03255 0.0333 0.0879 1.0000
14.500 1.1998 0.04161 0.03411 0.0339 0.0867 1.0000
14.750 1.2072 0.04322 0.03577 0.0344 0.0854 1.0000
15.000 1.2146 0.04487 0.03745 0.0348 0.0843 1.0000
15.250 1.2229 0.04654 0.03915 0.0352 0.0831 1.0000
15.500 1.2288 0.04842 0.04118 0.0354 0.0821 1.0000
15.750 1.2342 0.05040 0.04330 0.0355 0.0811 1.0000
16.000 1.2390 0.05250 0.04552 0.0356 0.0800 1.0000
16.250 1.2427 0.05473 0.04788 0.0354 0.0788 1.0000
16.500 1.2460 0.05706 0.05031 0.0352 0.0777 1.0000
16.750 1.2489 0.05948 0.05281 0.0348 0.0767 1.0000
17.000 1.2516 0.06198 0.05539 0.0343 0.0757 1.0000
17.250 1.2549 0.06444 0.05790 0.0338 0.0747 1.0000
17.500 1.2596 0.06679 0.06027 0.0334 0.0738 1.0000
17.750 1.2547 0.07046 0.06416 0.0322 0.0729 1.0000
18.000 1.2494 0.07431 0.06819 0.0308 0.0720 1.0000
18.250 1.2435 0.07837 0.07243 0.0291 0.0710 1.0000
18.500 1.2374 0.08254 0.07676 0.0273 0.0701 1.0000
18.750 1.2310 0.08685 0.08121 0.0253 0.0692 1.0000
19.000 1.2248 0.09122 0.08570 0.0232 0.0682 1.0000
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Polar data table (+)
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