MH 92 15.49% (mh92-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 92 15.49% (mh92-il) Reynolds number: 50,000 Max Cl/Cd: 15.4 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh92-il-50000.txt Download as CSV file: xf-mh92-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 92 15.49%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5725 0.10080 0.09442 -0.0064 1.0000 0.1319
-10.500 -0.5830 0.09232 0.08596 -0.0112 1.0000 0.1230
-10.250 -0.6744 0.07903 0.07251 -0.0220 1.0000 0.1143
-10.000 -0.6844 0.07409 0.06754 -0.0225 1.0000 0.1120
-9.750 -0.7086 0.06951 0.06284 -0.0219 1.0000 0.1097
-9.500 -0.7387 0.06512 0.05818 -0.0198 1.0000 0.1070
-9.250 -0.7845 0.06124 0.05348 -0.0154 1.0000 0.1028
-9.000 -0.7769 0.05727 0.04930 -0.0143 1.0000 0.1018
-8.750 -0.7699 0.05355 0.04533 -0.0128 1.0000 0.1011
-8.500 -0.7622 0.05012 0.04159 -0.0111 1.0000 0.1008
-8.250 -0.7528 0.04711 0.03819 -0.0093 1.0000 0.1012
-8.000 -0.7436 0.04452 0.03512 -0.0070 1.0000 0.1025
-7.750 -0.7204 0.04147 0.03221 -0.0069 1.0000 0.1065
-7.500 -0.7009 0.03914 0.02971 -0.0058 1.0000 0.1102
-7.250 -0.6815 0.03696 0.02723 -0.0043 1.0000 0.1137
-7.000 -0.6594 0.03479 0.02510 -0.0035 1.0000 0.1210
-6.750 -0.6438 0.03336 0.02351 -0.0014 1.0000 0.1291
-6.500 -0.6235 0.03169 0.02204 -0.0001 1.0000 0.1416
-6.250 -0.6096 0.03035 0.02082 0.0021 1.0000 0.1587
-6.000 -0.6010 0.02901 0.01984 0.0049 1.0000 0.1827
-5.750 -0.6008 0.02771 0.01891 0.0088 1.0000 0.2201
-5.500 -0.6113 0.02607 0.01807 0.0141 1.0000 0.2916
-5.250 -0.6310 0.02457 0.01772 0.0214 1.0000 0.4160
-5.000 -0.6409 0.02432 0.01813 0.0284 1.0000 0.5271
-4.750 -0.6396 0.02485 0.01894 0.0343 1.0000 0.6015
-4.500 -0.6321 0.02588 0.02009 0.0395 1.0000 0.6573
-4.250 -0.5674 0.03001 0.02408 0.0397 0.9858 0.7302
-4.000 -0.4189 0.03570 0.02914 0.0284 0.9728 0.7810
-3.750 -0.2580 0.03756 0.03035 0.0094 0.9597 0.8145
-3.500 -0.1280 0.03734 0.02968 -0.0076 0.9449 0.8435
-3.250 -0.0216 0.03638 0.02838 -0.0215 0.9281 0.8696
-3.000 0.0462 0.03557 0.02736 -0.0291 0.9059 0.8922
-2.750 0.1102 0.03460 0.02618 -0.0357 0.8825 0.9125
-2.500 0.1573 0.03383 0.02523 -0.0393 0.8595 0.9321
-2.250 0.1960 0.03319 0.02446 -0.0419 0.8356 0.9514
-2.000 0.2334 0.03252 0.02366 -0.0443 0.8138 0.9705
-1.750 0.2797 0.03136 0.02236 -0.0482 0.7922 0.9889
-1.500 0.3128 0.03064 0.02150 -0.0502 0.7726 1.0000
-1.250 0.3255 0.03064 0.02142 -0.0487 0.7551 1.0000
-1.000 0.3389 0.03070 0.02140 -0.0474 0.7381 1.0000
-0.750 0.3529 0.03082 0.02145 -0.0462 0.7215 1.0000
-0.500 0.3673 0.03099 0.02155 -0.0450 0.7056 1.0000
-0.250 0.3819 0.03121 0.02171 -0.0439 0.6904 1.0000
0.000 0.3962 0.03139 0.02181 -0.0423 0.6770 1.0000
0.250 0.4106 0.03150 0.02183 -0.0405 0.6642 1.0000
0.500 0.4267 0.03196 0.02227 -0.0398 0.6493 1.0000
0.750 0.4425 0.03245 0.02274 -0.0389 0.6359 1.0000
1.000 0.4574 0.03251 0.02268 -0.0366 0.6255 1.0000
1.250 0.4736 0.03312 0.02330 -0.0360 0.6116 1.0000
1.500 0.4892 0.03391 0.02410 -0.0353 0.5987 1.0000
1.750 0.5055 0.03383 0.02389 -0.0327 0.5902 1.0000
2.000 0.5202 0.03500 0.02512 -0.0326 0.5764 1.0000
2.250 0.5345 0.03598 0.02613 -0.0318 0.5652 1.0000
2.500 0.5510 0.03622 0.02630 -0.0297 0.5560 1.0000
2.750 0.5617 0.03782 0.02798 -0.0293 0.5438 1.0000
3.000 0.5806 0.03769 0.02774 -0.0268 0.5367 1.0000
3.250 0.5849 0.04010 0.03031 -0.0266 0.5244 1.0000
3.500 0.6023 0.04034 0.03047 -0.0244 0.5170 1.0000
3.750 0.6013 0.04297 0.03322 -0.0236 0.5060 1.0000
4.000 0.6174 0.04345 0.03366 -0.0214 0.4992 1.0000
4.250 0.5995 0.04738 0.03771 -0.0201 0.4890 1.0000
4.500 0.6333 0.04616 0.03639 -0.0175 0.4832 1.0000
4.750 0.5608 0.05410 0.04447 -0.0151 0.4750 1.0000
5.000 0.5562 0.05614 0.04649 -0.0125 0.4691 1.0000
5.250 0.5510 0.05828 0.04859 -0.0098 0.4636 1.0000
5.500 0.4812 0.06347 0.05367 -0.0046 0.4627 1.0000
5.750 0.4415 0.06706 0.05715 -0.0009 0.4618 1.0000
6.000 0.4209 0.07034 0.06036 0.0011 0.4619 1.0000
6.250 0.4122 0.07345 0.06343 0.0021 0.4630 1.0000
6.500 0.4103 0.07652 0.06648 0.0026 0.4642 1.0000
7.750 0.3253 0.09483 0.08473 -0.0002 0.5434 1.0000
8.000 0.3622 0.09944 0.08937 -0.0019 0.5365 1.0000
8.250 0.3439 0.09946 0.08935 0.0001 0.5254 1.0000
8.500 0.3784 0.10410 0.09402 -0.0013 0.5180 1.0000
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Polar data table (+)
Polar graphs
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