MH 108 11.98% (mh108-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 108 11.98% (mh108-il) Reynolds number: 50,000 Max Cl/Cd: 16.39 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh108-il-50000.txt Download as CSV file: xf-mh108-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 108 11.98%
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6753 0.08691 0.08064 -0.0076 1.0000 0.1284
-9.500 -0.6866 0.08080 0.07453 -0.0101 1.0000 0.1265
-9.250 -0.7021 0.07524 0.06898 -0.0114 1.0000 0.1250
-9.000 -0.7203 0.06968 0.06336 -0.0122 1.0000 0.1229
-8.750 -0.7409 0.06379 0.05728 -0.0127 1.0000 0.1211
-8.500 -0.7547 0.05841 0.05160 -0.0123 1.0000 0.1211
-8.250 -0.7621 0.05354 0.04632 -0.0111 1.0000 0.1235
-8.000 -0.7672 0.04868 0.04083 -0.0093 1.0000 0.1265
-7.750 -0.7524 0.04584 0.03798 -0.0079 1.0000 0.1364
-7.500 -0.7429 0.04249 0.03430 -0.0062 1.0000 0.1464
-7.250 -0.7297 0.03982 0.03137 -0.0044 1.0000 0.1602
-7.000 -0.7134 0.03740 0.02878 -0.0027 1.0000 0.1759
-6.750 -0.6962 0.03534 0.02656 -0.0010 1.0000 0.1945
-6.500 -0.6799 0.03322 0.02408 0.0008 1.0000 0.2139
-6.250 -0.6580 0.03159 0.02259 0.0021 1.0000 0.2352
-6.000 -0.6389 0.02997 0.02081 0.0037 1.0000 0.2590
-5.750 -0.6174 0.02857 0.01945 0.0051 1.0000 0.2836
-5.500 -0.5962 0.02726 0.01821 0.0066 1.0000 0.3105
-5.250 -0.5754 0.02607 0.01708 0.0082 1.0000 0.3402
-5.000 -0.5547 0.02494 0.01602 0.0098 1.0000 0.3722
-4.750 -0.5344 0.02393 0.01510 0.0115 1.0000 0.4073
-4.500 -0.5142 0.02302 0.01438 0.0134 1.0000 0.4449
-4.250 -0.4947 0.02215 0.01371 0.0155 1.0000 0.4854
-4.000 -0.4761 0.02139 0.01317 0.0178 1.0000 0.5297
-3.750 -0.4583 0.02073 0.01276 0.0203 1.0000 0.5770
-3.500 -0.4424 0.02019 0.01242 0.0232 1.0000 0.6282
-3.250 -0.4258 0.01986 0.01238 0.0263 1.0000 0.6803
-3.000 -0.4125 0.01974 0.01247 0.0299 1.0000 0.7352
-2.750 -0.3931 0.01996 0.01285 0.0327 1.0000 0.7943
-2.500 -0.3380 0.02093 0.01375 0.0302 1.0000 0.8612
-2.250 -0.2021 0.02223 0.01459 0.0137 1.0000 0.9239
-2.000 -0.0682 0.02211 0.01413 -0.0065 1.0000 0.9743
-1.750 0.0351 0.02138 0.01320 -0.0251 0.9739 1.0000
-1.500 0.1257 0.02061 0.01214 -0.0391 0.9179 1.0000
-1.250 0.1651 0.02041 0.01167 -0.0422 0.8693 1.0000
-1.000 0.1816 0.02053 0.01156 -0.0408 0.8323 1.0000
-0.750 0.1953 0.02073 0.01158 -0.0388 0.8016 1.0000
-0.500 0.2095 0.02095 0.01163 -0.0366 0.7761 1.0000
-0.250 0.2255 0.02123 0.01179 -0.0351 0.7519 1.0000
0.000 0.2421 0.02151 0.01192 -0.0332 0.7319 1.0000
0.250 0.2597 0.02190 0.01222 -0.0320 0.7115 1.0000
0.500 0.2779 0.02231 0.01254 -0.0306 0.6938 1.0000
0.750 0.2970 0.02276 0.01290 -0.0293 0.6775 1.0000
1.000 0.3160 0.02327 0.01333 -0.0281 0.6623 1.0000
1.250 0.3354 0.02384 0.01384 -0.0270 0.6481 1.0000
1.500 0.3550 0.02446 0.01442 -0.0259 0.6346 1.0000
1.750 0.3748 0.02513 0.01506 -0.0249 0.6219 1.0000
2.000 0.3946 0.02580 0.01569 -0.0237 0.6105 1.0000
2.250 0.4146 0.02646 0.01631 -0.0225 0.5996 1.0000
2.500 0.4342 0.02740 0.01729 -0.0219 0.5876 1.0000
2.750 0.4537 0.02838 0.01829 -0.0212 0.5768 1.0000
3.000 0.4738 0.02911 0.01900 -0.0198 0.5676 1.0000
3.250 0.4927 0.03019 0.02015 -0.0192 0.5567 1.0000
3.500 0.5106 0.03149 0.02153 -0.0186 0.5463 1.0000
3.750 0.5305 0.03236 0.02240 -0.0173 0.5375 1.0000
4.000 0.5479 0.03365 0.02377 -0.0166 0.5271 1.0000
4.250 0.5631 0.03534 0.02556 -0.0161 0.5170 1.0000
4.500 0.5834 0.03614 0.02636 -0.0145 0.5082 1.0000
4.750 0.5970 0.03799 0.02835 -0.0140 0.4978 1.0000
5.000 0.6085 0.04005 0.03052 -0.0134 0.4876 1.0000
5.250 0.6299 0.04076 0.03123 -0.0116 0.4787 1.0000
5.500 0.6375 0.04325 0.03386 -0.0112 0.4681 1.0000
5.750 0.6416 0.04609 0.03680 -0.0108 0.4579 1.0000
6.000 0.6625 0.04699 0.03774 -0.0090 0.4486 1.0000
6.250 0.6638 0.05011 0.04098 -0.0087 0.4384 1.0000
6.500 0.6537 0.05445 0.04539 -0.0091 0.4293 1.0000
6.750 0.6779 0.05511 0.04612 -0.0071 0.4192 1.0000
7.000 0.6376 0.06245 0.05342 -0.0095 0.4135 1.0000
7.250 0.6532 0.06421 0.05525 -0.0082 0.4036 1.0000
7.500 0.6187 0.07020 0.06113 -0.0093 0.4022 1.0000
7.750 0.5995 0.07499 0.06587 -0.0101 0.4009 1.0000
8.000 0.5880 0.07935 0.07021 -0.0110 0.3999 1.0000
8.250 0.5822 0.08378 0.07466 -0.0122 0.4024 1.0000
8.500 0.6080 0.08598 0.07697 -0.0113 0.3910 1.0000
8.750 0.5313 0.09890 0.08973 -0.0225 0.4944 1.0000
9.000 0.5411 0.10173 0.09263 -0.0221 0.4796 1.0000
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Polar data table (+)
Polar graphs
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