MH 22 7.2% (mh22-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 22 7.2% (mh22-il) Reynolds number: 200,000 Max Cl/Cd: 63.9 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh22-il-200000.txt Download as CSV file: xf-mh22-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5238 0.10382 0.10047 0.0014 1.0000 0.0273
-8.500 -0.5210 0.09985 0.09654 -0.0010 1.0000 0.0273
-8.250 -0.5262 0.09361 0.09038 -0.0032 1.0000 0.0279
-8.000 -0.5230 0.08928 0.08607 -0.0025 1.0000 0.0288
-7.750 -0.5196 0.08586 0.08269 -0.0033 1.0000 0.0295
-7.500 -0.5184 0.08244 0.07931 -0.0048 1.0000 0.0300
-7.250 -0.5166 0.07863 0.07553 -0.0073 1.0000 0.0306
-7.000 -0.5118 0.07437 0.07129 -0.0108 1.0000 0.0313
-6.750 -0.5050 0.06992 0.06682 -0.0143 1.0000 0.0322
-6.500 -0.4962 0.06521 0.06208 -0.0179 1.0000 0.0332
-6.250 -0.4851 0.06027 0.05706 -0.0214 1.0000 0.0346
-6.000 -0.4711 0.05528 0.05192 -0.0245 1.0000 0.0363
-5.750 -0.4480 0.05162 0.04769 -0.0275 1.0000 0.0395
-5.500 -0.4414 0.04421 0.04019 -0.0287 1.0000 0.0410
-5.250 -0.4252 0.04071 0.03665 -0.0286 1.0000 0.0425
-5.000 -0.4069 0.03735 0.03302 -0.0285 1.0000 0.0443
-4.750 -0.3845 0.02737 0.02195 -0.0258 1.0000 0.0177
-4.500 -0.3601 0.02569 0.02001 -0.0246 1.0000 0.0162
-4.250 -0.3401 0.02214 0.01587 -0.0232 1.0000 0.0158
-4.000 -0.3197 0.01924 0.01248 -0.0217 1.0000 0.0178
-3.750 -0.2998 0.01827 0.01149 -0.0208 1.0000 0.0232
-3.500 -0.2816 0.01660 0.00959 -0.0187 1.0000 0.0233
-3.250 -0.2510 0.01490 0.00770 -0.0192 0.9941 0.0238
-3.000 -0.2079 0.01331 0.00598 -0.0219 0.9826 0.0261
-2.750 -0.1681 0.01117 0.00413 -0.0241 0.9687 0.1058
-2.500 -0.1315 0.01004 0.00386 -0.0267 0.9519 0.2938
-2.250 -0.1018 0.00892 0.00358 -0.0273 0.9331 0.5195
-2.000 -0.0571 0.00771 0.00357 -0.0291 0.9237 0.9043
-1.750 0.0312 0.00767 0.00319 -0.0411 0.9227 1.0000
-1.500 0.0585 0.00768 0.00297 -0.0408 0.8967 1.0000
-1.250 0.0805 0.00774 0.00281 -0.0394 0.8756 1.0000
-1.000 0.1027 0.00782 0.00271 -0.0380 0.8569 1.0000
-0.750 0.1253 0.00791 0.00257 -0.0368 0.8409 1.0000
-0.500 0.1484 0.00801 0.00251 -0.0357 0.8264 1.0000
-0.250 0.1720 0.00811 0.00247 -0.0347 0.8129 1.0000
0.000 0.1959 0.00821 0.00245 -0.0337 0.7999 1.0000
0.250 0.2201 0.00831 0.00245 -0.0329 0.7874 1.0000
0.500 0.2445 0.00842 0.00247 -0.0321 0.7751 1.0000
0.750 0.2691 0.00853 0.00251 -0.0313 0.7631 1.0000
1.000 0.2938 0.00864 0.00255 -0.0305 0.7510 1.0000
1.250 0.3186 0.00876 0.00260 -0.0297 0.7390 1.0000
1.500 0.3435 0.00887 0.00266 -0.0290 0.7267 1.0000
1.750 0.3684 0.00899 0.00273 -0.0282 0.7141 1.0000
2.000 0.3934 0.00910 0.00281 -0.0275 0.7011 1.0000
2.250 0.4185 0.00922 0.00295 -0.0268 0.6874 1.0000
2.500 0.4436 0.00932 0.00304 -0.0261 0.6729 1.0000
2.750 0.4688 0.00943 0.00314 -0.0254 0.6576 1.0000
3.000 0.4939 0.00953 0.00324 -0.0246 0.6415 1.0000
3.250 0.5190 0.00964 0.00333 -0.0239 0.6248 1.0000
3.500 0.5443 0.00973 0.00354 -0.0232 0.6046 1.0000
3.750 0.5694 0.00983 0.00364 -0.0224 0.5843 1.0000
4.000 0.5947 0.00992 0.00378 -0.0217 0.5601 1.0000
4.250 0.6197 0.01005 0.00392 -0.0210 0.5333 1.0000
4.500 0.6446 0.01022 0.00409 -0.0203 0.5028 1.0000
4.750 0.6690 0.01047 0.00430 -0.0195 0.4676 1.0000
5.000 0.6920 0.01086 0.00453 -0.0185 0.4133 1.0000
5.250 0.7109 0.01182 0.00483 -0.0174 0.2803 1.0000
5.500 0.7200 0.01507 0.00641 -0.0158 0.0202 1.0000
5.750 0.7409 0.01658 0.00827 -0.0143 0.0126 1.0000
6.000 0.7615 0.01790 0.00981 -0.0130 0.0113 1.0000
6.250 0.7809 0.01946 0.01151 -0.0115 0.0108 1.0000
6.500 0.8003 0.02127 0.01346 -0.0100 0.0106 1.0000
6.750 0.8207 0.02335 0.01570 -0.0085 0.0107 1.0000
7.000 0.8418 0.02579 0.01837 -0.0071 0.0110 1.0000
7.250 0.8621 0.02862 0.02153 -0.0056 0.0116 1.0000
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Polar data table (+)
Polar graphs
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