MH 22 7.2% (mh22-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 22 7.2% (mh22-il) Reynolds number: 100,000 Max Cl/Cd: 48.54 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh22-il-100000.txt Download as CSV file: xf-mh22-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5232 0.09233 0.08792 -0.0029 1.0000 0.0769
-7.500 -0.5250 0.08859 0.08424 -0.0071 1.0000 0.0772
-7.250 -0.5266 0.08440 0.08001 -0.0156 1.0000 0.0779
-7.000 -0.4485 0.07194 0.06801 -0.0070 1.0000 0.0964
-6.750 -0.4500 0.06778 0.06388 -0.0098 1.0000 0.1004
-6.500 -0.4636 0.06265 0.05858 -0.0212 1.0000 0.1043
-5.500 -0.4540 0.05563 0.05106 -0.0229 1.0000 0.1251
-5.250 -0.4392 0.05162 0.04694 -0.0243 1.0000 0.1356
-5.000 -0.4229 0.04800 0.04318 -0.0252 1.0000 0.1480
-4.750 -0.3896 0.03652 0.03041 -0.0283 1.0000 0.0616
-4.500 -0.3672 0.03128 0.02449 -0.0272 1.0000 0.0486
-4.250 -0.3450 0.02736 0.01999 -0.0259 1.0000 0.0443
-4.000 -0.3208 0.02422 0.01614 -0.0242 1.0000 0.0416
-3.750 -0.2971 0.02185 0.01342 -0.0229 1.0000 0.0416
-3.500 -0.2743 0.01985 0.01125 -0.0215 1.0000 0.0433
-3.250 -0.2528 0.01827 0.00958 -0.0199 1.0000 0.0473
-3.000 -0.2343 0.01701 0.00834 -0.0182 1.0000 0.0605
-2.750 -0.2194 0.01552 0.00714 -0.0160 1.0000 0.1143
-2.500 -0.2069 0.01412 0.00639 -0.0138 1.0000 0.2314
-2.250 -0.0893 0.01066 0.00526 -0.0279 1.0000 1.0000
-2.000 -0.0840 0.01084 0.00522 -0.0248 1.0000 1.0000
-1.750 -0.0833 0.01115 0.00533 -0.0211 1.0000 1.0000
-1.500 -0.0672 0.01144 0.00529 -0.0202 0.9972 1.0000
-1.250 -0.0137 0.01162 0.00514 -0.0260 0.9842 1.0000
-1.000 0.0392 0.01174 0.00501 -0.0315 0.9719 1.0000
-0.750 0.0926 0.01179 0.00486 -0.0370 0.9602 1.0000
-0.500 0.1426 0.01180 0.00465 -0.0417 0.9475 1.0000
-0.250 0.1877 0.01181 0.00455 -0.0452 0.9335 1.0000
0.000 0.2273 0.01185 0.00450 -0.0474 0.9185 1.0000
0.250 0.2610 0.01193 0.00450 -0.0484 0.9030 1.0000
0.500 0.2883 0.01208 0.00460 -0.0480 0.8864 1.0000
0.750 0.3123 0.01226 0.00472 -0.0469 0.8695 1.0000
1.000 0.3352 0.01245 0.00486 -0.0455 0.8532 1.0000
1.250 0.3573 0.01264 0.00501 -0.0438 0.8375 1.0000
1.500 0.3790 0.01285 0.00517 -0.0421 0.8219 1.0000
1.750 0.4007 0.01308 0.00539 -0.0405 0.8049 1.0000
2.000 0.4227 0.01330 0.00566 -0.0389 0.7883 1.0000
2.250 0.4448 0.01350 0.00584 -0.0372 0.7721 1.0000
2.500 0.4671 0.01370 0.00603 -0.0356 0.7557 1.0000
2.750 0.4898 0.01392 0.00628 -0.0342 0.7369 1.0000
3.000 0.5126 0.01410 0.00647 -0.0326 0.7191 1.0000
3.250 0.5356 0.01430 0.00670 -0.0311 0.6999 1.0000
3.500 0.5588 0.01447 0.00701 -0.0296 0.6798 1.0000
3.750 0.5822 0.01464 0.00724 -0.0282 0.6585 1.0000
4.000 0.6057 0.01475 0.00737 -0.0267 0.6375 1.0000
4.250 0.6294 0.01488 0.00758 -0.0253 0.6128 1.0000
4.500 0.6531 0.01497 0.00776 -0.0239 0.5868 1.0000
4.750 0.6769 0.01502 0.00789 -0.0225 0.5590 1.0000
5.000 0.7004 0.01509 0.00806 -0.0211 0.5262 1.0000
5.250 0.7235 0.01517 0.00819 -0.0195 0.4879 1.0000
5.500 0.7451 0.01535 0.00849 -0.0177 0.4372 1.0000
5.750 0.7622 0.01583 0.00865 -0.0156 0.3258 1.0000
6.000 0.7603 0.02092 0.01149 -0.0124 0.0476 1.0000
6.250 0.7755 0.02325 0.01386 -0.0103 0.0357 1.0000
6.500 0.7956 0.02470 0.01542 -0.0090 0.0273 1.0000
6.750 0.8131 0.02738 0.01813 -0.0075 0.0237 1.0000
7.000 0.8355 0.02971 0.02066 -0.0061 0.0227 1.0000
7.250 0.8575 0.03255 0.02380 -0.0048 0.0225 1.0000
7.500 0.8773 0.03582 0.02746 -0.0034 0.0226 1.0000
7.750 0.8935 0.03948 0.03154 -0.0021 0.0231 1.0000
8.000 0.9054 0.04371 0.03620 -0.0007 0.0237 1.0000
8.250 0.9153 0.04871 0.04154 0.0003 0.0246 1.0000
8.500 0.9297 0.05024 0.04363 0.0023 0.0266 1.0000
8.750 0.9226 0.05559 0.04972 0.0041 0.0294 1.0000
9.000 0.9153 0.06036 0.05483 0.0050 0.0312 1.0000
9.250 0.9055 0.06471 0.05940 0.0055 0.0324 1.0000
9.500 0.8901 0.06869 0.06353 0.0061 0.0332 1.0000
9.750 0.8731 0.07296 0.06792 0.0049 0.0335 1.0000
10.000 0.8566 0.07792 0.07298 0.0021 0.0338 1.0000
10.250 0.8394 0.08384 0.07898 -0.0023 0.0339 1.0000
10.500 0.8226 0.09104 0.08624 -0.0079 0.0340 1.0000
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Polar data table (+)
Polar graphs
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