MH 22 7.2% (mh22-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 22 7.2% (mh22-il) Reynolds number: 50,000 Max Cl/Cd: 35 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh22-il-50000-n5.txt Download as CSV file: xf-mh22-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4548 0.10683 0.10055 0.0007 1.0000 0.0388
-9.000 -0.4481 0.10250 0.09624 0.0007 1.0000 0.0373
-8.750 -0.5254 0.10469 0.09804 0.0032 1.0000 0.0374
-8.500 -0.5212 0.10067 0.09407 0.0019 1.0000 0.0361
-8.250 -0.5182 0.09673 0.09020 0.0001 1.0000 0.0349
-8.000 -0.5168 0.09258 0.08614 -0.0020 1.0000 0.0339
-7.750 -0.5161 0.08853 0.08217 -0.0045 1.0000 0.0330
-7.500 -0.5162 0.08432 0.07804 -0.0075 1.0000 0.0320
-7.250 -0.5137 0.07947 0.07324 -0.0114 1.0000 0.0311
-7.000 -0.5098 0.07411 0.06789 -0.0157 1.0000 0.0300
-6.750 -0.5038 0.06804 0.06175 -0.0203 1.0000 0.0287
-6.250 -0.4828 0.05783 0.05106 -0.0255 1.0000 0.0272
-6.000 -0.4712 0.05338 0.04640 -0.0266 1.0000 0.0270
-5.750 -0.4576 0.04895 0.04167 -0.0274 1.0000 0.0269
-5.500 -0.4419 0.04471 0.03705 -0.0279 1.0000 0.0269
-5.250 -0.4242 0.04071 0.03258 -0.0278 1.0000 0.0270
-5.000 -0.4045 0.03709 0.02845 -0.0275 1.0000 0.0272
-4.750 -0.3846 0.03352 0.02449 -0.0270 1.0000 0.0282
-4.500 -0.3638 0.03124 0.02199 -0.0265 1.0000 0.0322
-4.250 -0.3399 0.02891 0.01895 -0.0257 1.0000 0.0373
-4.000 -0.3153 0.02645 0.01607 -0.0246 1.0000 0.0406
-3.750 -0.2916 0.02439 0.01386 -0.0235 1.0000 0.0454
-3.500 -0.2674 0.02267 0.01197 -0.0224 1.0000 0.0572
-3.250 -0.2425 0.02107 0.01034 -0.0217 1.0000 0.0882
-3.000 -0.2194 0.01955 0.00908 -0.0210 1.0000 0.1524
-2.750 -0.1988 0.01828 0.00823 -0.0201 1.0000 0.2415
-2.500 -0.1810 0.01705 0.00761 -0.0187 1.0000 0.3699
-2.250 -0.1691 0.01561 0.00733 -0.0154 1.0000 0.6099
-2.000 -0.0738 0.01473 0.00638 -0.0262 1.0000 1.0000
-1.750 -0.0606 0.01482 0.00607 -0.0242 1.0000 1.0000
-1.500 -0.0494 0.01498 0.00598 -0.0220 1.0000 1.0000
-1.250 -0.0192 0.01516 0.00583 -0.0235 0.9879 1.0000
-1.000 0.0250 0.01532 0.00566 -0.0273 0.9701 1.0000
-0.750 0.0699 0.01546 0.00552 -0.0312 0.9543 1.0000
-0.500 0.1112 0.01559 0.00534 -0.0342 0.9372 1.0000
-0.250 0.1511 0.01573 0.00530 -0.0368 0.9204 1.0000
0.000 0.1892 0.01587 0.00529 -0.0389 0.9039 1.0000
0.250 0.2237 0.01602 0.00533 -0.0401 0.8871 1.0000
0.500 0.2541 0.01620 0.00542 -0.0406 0.8695 1.0000
0.750 0.2830 0.01640 0.00556 -0.0406 0.8527 1.0000
1.000 0.3105 0.01660 0.00569 -0.0403 0.8364 1.0000
1.250 0.3358 0.01683 0.00588 -0.0395 0.8196 1.0000
1.500 0.3604 0.01707 0.00609 -0.0386 0.8029 1.0000
1.750 0.3847 0.01732 0.00632 -0.0376 0.7865 1.0000
2.000 0.4089 0.01756 0.00657 -0.0365 0.7706 1.0000
2.250 0.4326 0.01782 0.00694 -0.0354 0.7537 1.0000
2.500 0.4561 0.01808 0.00725 -0.0342 0.7363 1.0000
2.750 0.4798 0.01833 0.00755 -0.0330 0.7193 1.0000
3.000 0.5034 0.01859 0.00787 -0.0318 0.7019 1.0000
3.250 0.5268 0.01886 0.00825 -0.0306 0.6828 1.0000
3.500 0.5504 0.01911 0.00858 -0.0293 0.6645 1.0000
3.750 0.5739 0.01939 0.00918 -0.0281 0.6435 1.0000
4.000 0.5977 0.01963 0.00955 -0.0268 0.6229 1.0000
4.250 0.6212 0.01989 0.00999 -0.0255 0.5997 1.0000
4.500 0.6446 0.02013 0.01042 -0.0242 0.5746 1.0000
4.750 0.6678 0.02036 0.01084 -0.0228 0.5477 1.0000
5.000 0.6908 0.02056 0.01120 -0.0212 0.5186 1.0000
5.250 0.7133 0.02083 0.01167 -0.0197 0.4843 1.0000
5.500 0.7352 0.02114 0.01209 -0.0180 0.4457 1.0000
5.750 0.7553 0.02158 0.01280 -0.0161 0.3946 1.0000
6.000 0.7716 0.02232 0.01333 -0.0140 0.3118 1.0000
6.250 0.7823 0.02421 0.01440 -0.0123 0.1691 1.0000
6.500 0.7898 0.02769 0.01696 -0.0107 0.0756 1.0000
6.750 0.8013 0.03041 0.01945 -0.0092 0.0482 1.0000
7.000 0.8164 0.03278 0.02203 -0.0071 0.0396 1.0000
7.250 0.8323 0.03515 0.02454 -0.0055 0.0326 1.0000
7.500 0.8472 0.03737 0.02689 -0.0044 0.0255 1.0000
7.750 0.8653 0.04034 0.03011 -0.0029 0.0236 1.0000
8.000 0.8840 0.04344 0.03367 -0.0015 0.0225 1.0000
8.250 0.8986 0.04691 0.03761 -0.0002 0.0218 1.0000
8.500 0.9083 0.05064 0.04181 0.0010 0.0214 1.0000
8.750 0.9127 0.05458 0.04619 0.0021 0.0212 1.0000
9.000 0.9118 0.05860 0.05060 0.0030 0.0211 1.0000
9.250 0.9061 0.06258 0.05489 0.0036 0.0211 1.0000
9.500 0.8940 0.06651 0.05906 0.0040 0.0212 1.0000
9.750 0.8796 0.07069 0.06342 0.0033 0.0213 1.0000
10.000 0.8653 0.07543 0.06830 0.0010 0.0215 1.0000
10.250 0.8507 0.08091 0.07391 -0.0024 0.0217 1.0000
10.500 0.8358 0.08731 0.08038 -0.0067 0.0219 1.0000
10.750 0.8229 0.09420 0.08732 -0.0115 0.0222 1.0000
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Polar data table (+)
Polar graphs
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