MH 20 9.01% (mh20-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 20 9.01% (mh20-il) Reynolds number: 200,000 Max Cl/Cd: 68.72 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh20-il-200000.txt Download as CSV file: xf-mh20-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 20 9.01%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5128 0.09152 0.08855 -0.0123 1.0000 0.0370
-8.250 -0.5162 0.08666 0.08372 -0.0173 1.0000 0.0370
-8.000 -0.5229 0.08015 0.07729 -0.0167 1.0000 0.0383
-7.750 -0.5185 0.07688 0.07404 -0.0168 1.0000 0.0392
-7.500 -0.5133 0.07325 0.07042 -0.0185 1.0000 0.0401
-7.250 -0.5081 0.06915 0.06631 -0.0211 1.0000 0.0412
-7.000 -0.5013 0.06482 0.06195 -0.0240 1.0000 0.0427
-6.750 -0.4925 0.06017 0.05717 -0.0272 1.0000 0.0445
-6.500 -0.4813 0.05583 0.05232 -0.0319 1.0000 0.0497
-6.250 -0.4735 0.04872 0.04505 -0.0343 0.9880 0.0512
-5.250 -0.3844 0.02770 0.02212 -0.0348 0.9220 0.0234
-5.000 -0.3677 0.02454 0.01847 -0.0325 0.9095 0.0214
-4.750 -0.3478 0.02185 0.01524 -0.0303 0.8990 0.0197
-4.500 -0.3254 0.01970 0.01265 -0.0284 0.8894 0.0187
-4.250 -0.3015 0.01803 0.01072 -0.0270 0.8801 0.0183
-4.000 -0.2785 0.01674 0.00925 -0.0255 0.8721 0.0186
-3.750 -0.2554 0.01567 0.00805 -0.0242 0.8640 0.0198
-3.500 -0.2319 0.01481 0.00705 -0.0230 0.8562 0.0224
-3.250 -0.2092 0.01380 0.00592 -0.0214 0.8493 0.0374
-3.000 -0.1895 0.01236 0.00544 -0.0203 0.8417 0.2087
-2.750 -0.1684 0.01170 0.00510 -0.0191 0.8354 0.3143
-2.500 -0.1490 0.01088 0.00490 -0.0177 0.8279 0.4726
-2.250 -0.1351 0.00986 0.00481 -0.0142 0.8219 0.7097
-2.000 -0.0454 0.00964 0.00491 -0.0251 0.8181 0.9380
-1.750 0.0098 0.00988 0.00491 -0.0301 0.8121 0.9765
-1.500 0.0764 0.00985 0.00459 -0.0380 0.8073 0.9999
-1.250 0.1002 0.00984 0.00445 -0.0375 0.7991 1.0000
-1.000 0.1229 0.00984 0.00431 -0.0366 0.7923 1.0000
-0.750 0.1469 0.00985 0.00421 -0.0359 0.7847 1.0000
-0.500 0.1706 0.00987 0.00411 -0.0352 0.7778 1.0000
-0.250 0.1947 0.00989 0.00404 -0.0345 0.7705 1.0000
0.000 0.2190 0.00994 0.00400 -0.0338 0.7635 1.0000
0.250 0.2432 0.00998 0.00396 -0.0331 0.7563 1.0000
0.500 0.2679 0.01003 0.00397 -0.0325 0.7488 1.0000
0.750 0.2921 0.01008 0.00393 -0.0317 0.7419 1.0000
1.000 0.3172 0.01014 0.00397 -0.0312 0.7337 1.0000
1.250 0.3413 0.01019 0.00394 -0.0302 0.7271 1.0000
1.500 0.3667 0.01025 0.00400 -0.0298 0.7179 1.0000
1.750 0.3915 0.01031 0.00404 -0.0291 0.7099 1.0000
2.000 0.4162 0.01035 0.00405 -0.0284 0.7016 1.0000
2.250 0.4414 0.01041 0.00411 -0.0278 0.6920 1.0000
2.500 0.4664 0.01046 0.00415 -0.0271 0.6830 1.0000
2.750 0.4912 0.01050 0.00416 -0.0263 0.6739 1.0000
3.000 0.5164 0.01054 0.00427 -0.0257 0.6627 1.0000
3.250 0.5416 0.01058 0.00434 -0.0250 0.6513 1.0000
3.500 0.5667 0.01061 0.00440 -0.0243 0.6392 1.0000
3.750 0.5918 0.01063 0.00445 -0.0236 0.6262 1.0000
4.000 0.6169 0.01065 0.00454 -0.0229 0.6117 1.0000
4.250 0.6420 0.01066 0.00459 -0.0222 0.5960 1.0000
4.500 0.6671 0.01069 0.00463 -0.0215 0.5790 1.0000
4.750 0.6922 0.01072 0.00474 -0.0208 0.5574 1.0000
5.000 0.7171 0.01080 0.00485 -0.0201 0.5338 1.0000
5.250 0.7416 0.01092 0.00498 -0.0194 0.5066 1.0000
5.500 0.7655 0.01114 0.00515 -0.0186 0.4748 1.0000
5.750 0.7888 0.01148 0.00549 -0.0177 0.4380 1.0000
6.000 0.8112 0.01194 0.00584 -0.0169 0.3958 1.0000
6.250 0.8327 0.01251 0.00627 -0.0160 0.3458 1.0000
6.500 0.8534 0.01319 0.00678 -0.0151 0.2904 1.0000
6.750 0.8720 0.01413 0.00745 -0.0141 0.2197 1.0000
7.000 0.8775 0.01678 0.00898 -0.0120 0.0643 1.0000
7.250 0.8845 0.01927 0.01121 -0.0093 0.0233 1.0000
7.500 0.8910 0.02153 0.01356 -0.0065 0.0166 1.0000
7.750 0.9051 0.02291 0.01507 -0.0044 0.0149 1.0000
8.000 0.9184 0.02456 0.01683 -0.0023 0.0143 1.0000
8.250 0.9333 0.02644 0.01884 -0.0003 0.0136 1.0000
8.500 0.9502 0.02854 0.02110 0.0014 0.0134 1.0000
8.750 0.9676 0.03107 0.02387 0.0030 0.0134 1.0000
9.000 0.9830 0.03394 0.02704 0.0047 0.0137 1.0000
9.250 0.9943 0.03708 0.03061 0.0067 0.0141 1.0000
9.500 1.0004 0.04053 0.03444 0.0088 0.0146 1.0000
9.750 1.0019 0.04394 0.03816 0.0110 0.0151 1.0000
10.000 0.9962 0.04788 0.04241 0.0134 0.0156 1.0000
10.250 1.0050 0.05158 0.04625 0.0148 0.0174 1.0000
10.500 0.9805 0.05497 0.05027 0.0195 0.0208 1.0000
10.750 0.9595 0.05944 0.05501 0.0208 0.0223 1.0000
11.000 0.9432 0.06340 0.05915 0.0208 0.0229 1.0000
11.250 0.9235 0.06821 0.06413 0.0198 0.0236 1.0000
11.500 0.9026 0.07360 0.06966 0.0177 0.0240 1.0000
11.750 0.8841 0.07903 0.07523 0.0147 0.0238 1.0000
12.000 0.8629 0.08574 0.08207 0.0104 0.0237 1.0000
12.250 0.8452 0.09274 0.08911 0.0052 0.0230 1.0000
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Polar data table (+)
Polar graphs
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