MH 91 14.98% (mh91-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 91 14.98% (mh91-il) Reynolds number: 100,000 Max Cl/Cd: 34.26 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh91-il-100000.txt Download as CSV file: xf-mh91-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5303 0.07808 0.07385 -0.0184 1.0000 0.0780
-10.250 -0.5912 0.06672 0.06232 -0.0254 1.0000 0.0759
-10.000 -0.6452 0.05971 0.05507 -0.0274 1.0000 0.0747
-9.750 -0.6782 0.05423 0.04932 -0.0261 1.0000 0.0693
-9.500 -0.7578 0.05935 0.05389 -0.0198 1.0000 0.0691
-9.250 -0.7844 0.05350 0.04732 -0.0161 1.0000 0.0612
-9.000 -0.7790 0.04947 0.04307 -0.0146 1.0000 0.0589
-8.750 -0.7929 0.04559 0.03808 -0.0097 1.0000 0.0542
-8.500 -0.7751 0.04208 0.03445 -0.0089 1.0000 0.0535
-8.250 -0.7584 0.03918 0.03131 -0.0078 1.0000 0.0530
-8.000 -0.7409 0.03653 0.02836 -0.0065 1.0000 0.0528
-7.750 -0.7210 0.03422 0.02579 -0.0054 1.0000 0.0528
-7.500 -0.7003 0.03218 0.02350 -0.0043 1.0000 0.0533
-7.250 -0.6823 0.03064 0.02173 -0.0027 1.0000 0.0541
-7.000 -0.6679 0.02902 0.02022 -0.0010 1.0000 0.0563
-6.750 -0.6629 0.02822 0.01946 0.0022 1.0000 0.0581
-6.500 -0.6597 0.02757 0.01875 0.0056 1.0000 0.0604
-6.250 -0.6226 0.02586 0.01705 0.0035 0.9937 0.0643
-6.000 -0.5718 0.02407 0.01534 -0.0010 0.9832 0.0730
-5.750 -0.5263 0.02222 0.01375 -0.0050 0.9715 0.0893
-5.500 -0.4900 0.01993 0.01195 -0.0075 0.9580 0.1402
-5.250 -0.4817 0.01723 0.01098 -0.0055 0.9388 0.3943
-5.000 -0.4572 0.01679 0.01094 -0.0045 0.9215 0.4973
-4.750 -0.4329 0.01670 0.01103 -0.0028 0.9046 0.5631
-4.500 -0.4100 0.01680 0.01124 -0.0006 0.8879 0.6146
-4.250 -0.3872 0.01708 0.01158 0.0020 0.8719 0.6576
-4.000 -0.3645 0.01750 0.01201 0.0049 0.8562 0.6944
-3.750 -0.3389 0.01806 0.01252 0.0076 0.8413 0.7234
-3.500 -0.3155 0.01850 0.01284 0.0104 0.8270 0.7483
-3.250 -0.2902 0.01892 0.01315 0.0126 0.8115 0.7688
-3.000 -0.2620 0.01938 0.01349 0.0143 0.7960 0.7865
-2.750 -0.2337 0.01981 0.01378 0.0159 0.7808 0.8035
-2.500 -0.1949 0.02036 0.01418 0.0159 0.7658 0.8152
-2.250 -0.1600 0.02072 0.01437 0.0163 0.7513 0.8282
-2.000 -0.1284 0.02092 0.01438 0.0169 0.7375 0.8422
-1.750 -0.0984 0.02108 0.01439 0.0175 0.7223 0.8570
-1.500 -0.0465 0.02133 0.01445 0.0143 0.7055 0.8644
-1.250 -0.0115 0.02137 0.01435 0.0136 0.6899 0.8774
-1.000 0.0280 0.02142 0.01425 0.0120 0.6740 0.8891
-0.750 0.0723 0.02141 0.01406 0.0096 0.6579 0.8989
-0.500 0.1063 0.02136 0.01386 0.0087 0.6433 0.9117
-0.250 0.1474 0.02129 0.01361 0.0066 0.6282 0.9228
0.000 0.1896 0.02116 0.01331 0.0041 0.6127 0.9333
0.250 0.2274 0.02103 0.01308 0.0021 0.5967 0.9451
0.500 0.2653 0.02093 0.01288 0.0000 0.5811 0.9571
0.750 0.3114 0.02065 0.01248 -0.0037 0.5650 0.9665
1.000 0.3538 0.02039 0.01210 -0.0068 0.5498 0.9764
1.250 0.3958 0.02012 0.01171 -0.0099 0.5353 0.9860
1.500 0.4385 0.01981 0.01125 -0.0132 0.5216 0.9949
1.750 0.4732 0.01959 0.01095 -0.0152 0.5081 1.0000
2.000 0.4936 0.01967 0.01102 -0.0145 0.4961 1.0000
2.250 0.5137 0.01973 0.01095 -0.0136 0.4866 1.0000
2.500 0.5344 0.01983 0.01104 -0.0130 0.4753 1.0000
2.750 0.5551 0.01999 0.01116 -0.0122 0.4653 1.0000
3.000 0.5759 0.02010 0.01118 -0.0113 0.4559 1.0000
3.250 0.5967 0.02033 0.01145 -0.0107 0.4456 1.0000
3.500 0.6178 0.02047 0.01146 -0.0097 0.4375 1.0000
3.750 0.6385 0.02078 0.01185 -0.0091 0.4273 1.0000
4.000 0.6598 0.02094 0.01187 -0.0081 0.4198 1.0000
4.250 0.6801 0.02132 0.01238 -0.0074 0.4100 1.0000
4.500 0.7015 0.02154 0.01246 -0.0065 0.4031 1.0000
4.750 0.7211 0.02200 0.01306 -0.0056 0.3940 1.0000
5.000 0.7420 0.02226 0.01324 -0.0046 0.3869 1.0000
5.250 0.7610 0.02279 0.01387 -0.0036 0.3788 1.0000
5.500 0.7810 0.02314 0.01421 -0.0026 0.3716 1.0000
5.750 0.8005 0.02366 0.01474 -0.0015 0.3649 1.0000
6.000 0.8186 0.02418 0.01535 -0.0003 0.3571 1.0000
6.250 0.8400 0.02452 0.01554 0.0008 0.3515 1.0000
6.500 0.8547 0.02534 0.01661 0.0022 0.3439 1.0000
6.750 0.8738 0.02576 0.01701 0.0035 0.3377 1.0000
7.000 0.8914 0.02642 0.01769 0.0049 0.3317 1.0000
7.250 0.9057 0.02717 0.01861 0.0065 0.3248 1.0000
7.500 0.9262 0.02754 0.01889 0.0078 0.3194 1.0000
7.750 0.9382 0.02853 0.02006 0.0096 0.3132 1.0000
8.000 0.9528 0.02921 0.02082 0.0114 0.3069 1.0000
8.250 0.9758 0.02953 0.02100 0.0124 0.3018 1.0000
8.500 0.9810 0.03081 0.02258 0.0149 0.2955 1.0000
8.750 0.9968 0.03139 0.02320 0.0166 0.2895 1.0000
9.000 1.0208 0.03180 0.02346 0.0174 0.2845 1.0000
9.250 1.0212 0.03328 0.02529 0.0203 0.2782 1.0000
9.500 1.0402 0.03371 0.02571 0.0216 0.2724 1.0000
9.750 1.0591 0.03446 0.02643 0.0227 0.2672 1.0000
10.000 1.0596 0.03604 0.02831 0.0253 0.2611 1.0000
10.250 1.0839 0.03626 0.02846 0.0260 0.2555 1.0000
10.500 1.0944 0.03757 0.02988 0.0275 0.2503 1.0000
10.750 1.0943 0.03926 0.03181 0.0298 0.2445 1.0000
11.000 1.1268 0.03906 0.03148 0.0298 0.2388 1.0000
11.250 1.1215 0.04124 0.03390 0.0322 0.2339 1.0000
11.500 1.1125 0.04344 0.03633 0.0347 0.2289 1.0000
11.750 1.1647 0.04223 0.03486 0.0335 0.2226 1.0000
12.000 1.1342 0.04562 0.03860 0.0372 0.2190 1.0000
12.250 1.0620 0.05173 0.04499 0.0410 0.2174 1.0000
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Polar data table (+)
Polar graphs
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