MH 22 7.2% (mh22-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 22 7.2% (mh22-il) Reynolds number: 100,000 Max Cl/Cd: 47.81 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh22-il-100000-n5.txt Download as CSV file: xf-mh22-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 22 7.2%
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5174 0.08881 0.08417 -0.0003 1.0000 0.0135
-7.750 -0.5170 0.08483 0.08026 -0.0027 1.0000 0.0137
-7.500 -0.5177 0.08094 0.07643 -0.0050 1.0000 0.0128
-7.250 -0.5169 0.07647 0.07201 -0.0087 1.0000 0.0128
-7.000 -0.5127 0.07153 0.06708 -0.0128 1.0000 0.0129
-6.750 -0.5061 0.06630 0.06182 -0.0170 1.0000 0.0132
-6.500 -0.4971 0.06086 0.05631 -0.0206 1.0000 0.0135
-6.250 -0.4860 0.05525 0.05055 -0.0237 1.0000 0.0140
-6.000 -0.4729 0.05005 0.04514 -0.0256 1.0000 0.0141
-5.750 -0.4580 0.04488 0.03967 -0.0269 1.0000 0.0146
-5.500 -0.4416 0.04014 0.03455 -0.0273 1.0000 0.0150
-5.250 -0.4239 0.03583 0.02978 -0.0272 1.0000 0.0152
-5.000 -0.4049 0.03198 0.02543 -0.0266 1.0000 0.0151
-4.750 -0.3842 0.02853 0.02144 -0.0257 1.0000 0.0152
-4.500 -0.3620 0.02563 0.01802 -0.0247 1.0000 0.0154
-4.250 -0.3388 0.02316 0.01495 -0.0235 1.0000 0.0158
-4.000 -0.3154 0.02120 0.01267 -0.0224 1.0000 0.0163
-3.750 -0.2934 0.01922 0.01050 -0.0211 1.0000 0.0171
-3.500 -0.2728 0.01771 0.00886 -0.0197 1.0000 0.0188
-3.250 -0.2524 0.01667 0.00771 -0.0184 0.9995 0.0219
-3.000 -0.2152 0.01537 0.00642 -0.0204 0.9810 0.0445
-2.750 -0.1807 0.01402 0.00563 -0.0222 0.9619 0.1525
-2.500 -0.1451 0.01323 0.00514 -0.0241 0.9439 0.2522
-2.250 -0.1115 0.01240 0.00475 -0.0256 0.9262 0.3919
-2.000 -0.0831 0.01138 0.00453 -0.0254 0.9085 0.6216
-1.750 -0.0114 0.01060 0.00421 -0.0323 0.9044 0.9427
-1.500 0.0452 0.01055 0.00383 -0.0381 0.8901 1.0000
-1.250 0.0726 0.01060 0.00362 -0.0379 0.8680 1.0000
-1.000 0.0978 0.01067 0.00345 -0.0372 0.8489 1.0000
-0.750 0.1221 0.01075 0.00326 -0.0363 0.8310 1.0000
-0.500 0.1462 0.01085 0.00317 -0.0354 0.8149 1.0000
-0.250 0.1703 0.01095 0.00311 -0.0345 0.8000 1.0000
0.000 0.1946 0.01105 0.00308 -0.0336 0.7860 1.0000
0.250 0.2189 0.01116 0.00307 -0.0327 0.7726 1.0000
0.500 0.2433 0.01128 0.00309 -0.0319 0.7595 1.0000
0.750 0.2680 0.01140 0.00314 -0.0311 0.7466 1.0000
1.000 0.2928 0.01153 0.00319 -0.0304 0.7337 1.0000
1.250 0.3176 0.01166 0.00326 -0.0297 0.7208 1.0000
1.500 0.3424 0.01180 0.00334 -0.0289 0.7077 1.0000
1.750 0.3673 0.01194 0.00345 -0.0282 0.6945 1.0000
2.000 0.3922 0.01208 0.00357 -0.0275 0.6810 1.0000
2.250 0.4171 0.01223 0.00377 -0.0267 0.6671 1.0000
2.500 0.4421 0.01237 0.00392 -0.0260 0.6526 1.0000
2.750 0.4671 0.01252 0.00407 -0.0252 0.6377 1.0000
3.000 0.4922 0.01267 0.00426 -0.0246 0.6209 1.0000
3.250 0.5173 0.01282 0.00447 -0.0239 0.6029 1.0000
3.500 0.5423 0.01298 0.00477 -0.0231 0.5841 1.0000
3.750 0.5674 0.01313 0.00501 -0.0224 0.5620 1.0000
4.000 0.5923 0.01330 0.00525 -0.0217 0.5379 1.0000
4.250 0.6170 0.01349 0.00549 -0.0209 0.5111 1.0000
4.500 0.6414 0.01373 0.00576 -0.0200 0.4817 1.0000
4.750 0.6655 0.01403 0.00608 -0.0191 0.4498 1.0000
5.000 0.6892 0.01442 0.00648 -0.0182 0.4148 1.0000
5.250 0.7124 0.01490 0.00694 -0.0173 0.3732 1.0000
5.500 0.7346 0.01551 0.00747 -0.0164 0.3157 1.0000
5.750 0.7522 0.01685 0.00834 -0.0153 0.1883 1.0000
6.250 0.7798 0.02197 0.01222 -0.0123 0.0152 1.0000
6.500 0.7991 0.02340 0.01386 -0.0111 0.0109 1.0000
6.750 0.8186 0.02467 0.01532 -0.0101 0.0083 1.0000
7.000 0.8360 0.02635 0.01719 -0.0088 0.0073 1.0000
7.250 0.8525 0.02836 0.01941 -0.0073 0.0069 1.0000
7.500 0.8685 0.03079 0.02208 -0.0059 0.0065 1.0000
7.750 0.8845 0.03354 0.02511 -0.0045 0.0063 1.0000
8.000 0.8987 0.03672 0.02865 -0.0031 0.0062 1.0000
8.250 0.9104 0.04003 0.03235 -0.0017 0.0061 1.0000
8.500 0.9188 0.04341 0.03613 -0.0004 0.0061 1.0000
8.750 0.9230 0.04691 0.04002 0.0010 0.0061 1.0000
9.000 0.9230 0.05041 0.04388 0.0023 0.0061 1.0000
9.250 0.9197 0.05371 0.04748 0.0035 0.0061 1.0000
9.500 0.9092 0.05699 0.05100 0.0048 0.0061 1.0000
9.750 0.8972 0.06049 0.05471 0.0049 0.0062 1.0000
10.000 0.8865 0.06432 0.05872 0.0037 0.0062 1.0000
10.250 0.8746 0.06892 0.06349 0.0012 0.0063 1.0000
10.500 0.8604 0.07460 0.06933 -0.0025 0.0063 1.0000
10.750 0.8471 0.08103 0.07589 -0.0072 0.0064 1.0000
11.000 0.8357 0.08817 0.08315 -0.0124 0.0065 1.0000
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Polar data table (+)
Polar graphs
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