MH 22 7.2% (mh22-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 22 7.2% (mh22-il) Reynolds number: 200,000 Max Cl/Cd: 60.27 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh22-il-200000-n5.txt Download as CSV file: xf-mh22-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5152 0.08618 0.08286 0.0003 1.0000 0.0060
-7.750 -0.5159 0.08212 0.07884 -0.0020 1.0000 0.0059
-7.500 -0.5187 0.07810 0.07489 -0.0045 1.0000 0.0058
-7.250 -0.5190 0.07347 0.07029 -0.0083 1.0000 0.0057
-7.000 -0.5153 0.06825 0.06506 -0.0128 1.0000 0.0056
-6.750 -0.5089 0.06273 0.05950 -0.0171 1.0000 0.0054
-6.500 -0.4999 0.05698 0.05366 -0.0208 1.0000 0.0053
-6.250 -0.4888 0.05106 0.04759 -0.0237 1.0000 0.0052
-6.000 -0.4755 0.04534 0.04165 -0.0256 1.0000 0.0051
-5.750 -0.4608 0.03961 0.03562 -0.0265 1.0000 0.0049
-5.500 -0.4447 0.03428 0.02991 -0.0266 1.0000 0.0048
-5.250 -0.4270 0.02961 0.02476 -0.0260 1.0000 0.0048
-5.000 -0.4075 0.02581 0.02045 -0.0250 1.0000 0.0048
-4.750 -0.3863 0.02271 0.01683 -0.0238 1.0000 0.0049
-4.500 -0.3640 0.02027 0.01396 -0.0226 1.0000 0.0052
-4.250 -0.3380 0.01851 0.01185 -0.0221 0.9949 0.0058
-4.000 -0.3045 0.01642 0.00932 -0.0236 0.9698 0.0092
-3.750 -0.2695 0.01493 0.00762 -0.0248 0.9446 0.0103
-3.500 -0.2361 0.01372 0.00620 -0.0256 0.9191 0.0111
-3.250 -0.2060 0.01287 0.00511 -0.0256 0.8936 0.0124
-3.000 -0.1782 0.01225 0.00423 -0.0251 0.8698 0.0155
-2.750 -0.1536 0.01137 0.00359 -0.0243 0.8484 0.0766
-2.500 -0.1296 0.01076 0.00333 -0.0237 0.8288 0.1669
-2.250 -0.1047 0.01043 0.00306 -0.0230 0.8116 0.2245
-2.000 -0.0803 0.01004 0.00283 -0.0224 0.7963 0.3039
-1.750 -0.0564 0.00960 0.00258 -0.0216 0.7823 0.4043
-1.500 -0.0345 0.00902 0.00244 -0.0204 0.7694 0.5474
-1.250 -0.0149 0.00834 0.00237 -0.0181 0.7575 0.7318
-1.000 0.0444 0.00798 0.00232 -0.0237 0.7462 0.9359
-0.750 0.0910 0.00802 0.00218 -0.0275 0.7349 0.9842
-0.500 0.1299 0.00806 0.00200 -0.0299 0.7239 1.0000
-0.250 0.1548 0.00812 0.00192 -0.0293 0.7133 1.0000
0.000 0.1799 0.00818 0.00187 -0.0287 0.7030 1.0000
0.250 0.2052 0.00825 0.00183 -0.0281 0.6923 1.0000
0.500 0.2306 0.00832 0.00182 -0.0276 0.6817 1.0000
0.750 0.2560 0.00839 0.00183 -0.0270 0.6713 1.0000
1.000 0.2815 0.00847 0.00184 -0.0265 0.6608 1.0000
1.250 0.3070 0.00856 0.00186 -0.0259 0.6502 1.0000
1.500 0.3326 0.00865 0.00191 -0.0254 0.6386 1.0000
1.750 0.3583 0.00873 0.00196 -0.0249 0.6265 1.0000
2.000 0.3839 0.00882 0.00203 -0.0244 0.6138 1.0000
2.250 0.4096 0.00892 0.00215 -0.0239 0.6002 1.0000
2.500 0.4353 0.00902 0.00223 -0.0234 0.5853 1.0000
2.750 0.4610 0.00912 0.00233 -0.0229 0.5685 1.0000
3.000 0.4867 0.00923 0.00244 -0.0224 0.5490 1.0000
3.250 0.5122 0.00936 0.00255 -0.0219 0.5269 1.0000
3.500 0.5375 0.00953 0.00276 -0.0213 0.5013 1.0000
3.750 0.5626 0.00973 0.00292 -0.0207 0.4733 1.0000
4.000 0.5876 0.00999 0.00312 -0.0202 0.4446 1.0000
4.250 0.6124 0.01028 0.00337 -0.0196 0.4152 1.0000
4.500 0.6372 0.01060 0.00365 -0.0190 0.3847 1.0000
4.750 0.6618 0.01098 0.00398 -0.0185 0.3495 1.0000
5.000 0.6849 0.01156 0.00435 -0.0179 0.2880 1.0000
5.250 0.7022 0.01314 0.00501 -0.0171 0.1278 1.0000
5.500 0.7180 0.01526 0.00625 -0.0160 0.0070 1.0000
5.750 0.7414 0.01607 0.00736 -0.0151 0.0046 1.0000
6.000 0.7642 0.01695 0.00847 -0.0142 0.0039 1.0000
6.250 0.7860 0.01797 0.00972 -0.0132 0.0036 1.0000
6.500 0.8065 0.01921 0.01115 -0.0121 0.0034 1.0000
6.750 0.8259 0.02060 0.01273 -0.0109 0.0033 1.0000
7.000 0.8448 0.02220 0.01450 -0.0096 0.0032 1.0000
7.250 0.8635 0.02401 0.01650 -0.0082 0.0031 1.0000
7.500 0.8820 0.02609 0.01883 -0.0069 0.0031 1.0000
7.750 0.9000 0.02845 0.02148 -0.0055 0.0032 1.0000
8.000 0.9162 0.03118 0.02456 -0.0040 0.0032 1.0000
8.250 0.9296 0.03424 0.02802 -0.0024 0.0033 1.0000
8.500 0.9392 0.03761 0.03182 -0.0008 0.0033 1.0000
8.750 0.9442 0.04126 0.03589 0.0009 0.0034 1.0000
9.000 0.9442 0.04503 0.04003 0.0026 0.0035 1.0000
9.250 0.9394 0.04871 0.04404 0.0042 0.0035 1.0000
9.500 0.9271 0.05218 0.04775 0.0061 0.0036 1.0000
9.750 0.9120 0.05578 0.05155 0.0067 0.0036 1.0000
10.000 0.8973 0.05998 0.05592 0.0053 0.0037 1.0000
10.250 0.8822 0.06503 0.06113 0.0025 0.0037 1.0000
10.500 0.8656 0.07128 0.06752 -0.0019 0.0037 1.0000
10.750 0.8497 0.07862 0.07499 -0.0074 0.0037 1.0000
11.000 0.8354 0.08703 0.08349 -0.0136 0.0037 1.0000
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Polar data table (+)
Polar graphs
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