MH 42 8.94% (mh42-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: MH 42 8.94% (mh42-il) Reynolds number: 50,000 Max Cl/Cd: 32.75 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh42-il-50000.txt Download as CSV file: xf-mh42-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 42 8.94%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4812 0.10736 0.10086 0.0036 1.0000 0.2274
-8.500 -0.4926 0.10570 0.09931 0.0013 1.0000 0.2355
-8.250 -0.4882 0.10217 0.09585 0.0012 1.0000 0.2492
-8.000 -0.4802 0.09839 0.09212 0.0015 1.0000 0.2625
-7.750 -0.4689 0.09430 0.08807 0.0019 1.0000 0.2745
-7.500 -0.4622 0.09053 0.08436 0.0020 1.0000 0.2856
-7.250 -0.4592 0.08722 0.08114 0.0018 1.0000 0.2971
-7.000 -0.4579 0.08397 0.07798 0.0019 1.0000 0.3099
-6.750 -0.4571 0.08078 0.07488 0.0021 1.0000 0.3233
-6.500 -0.4560 0.07756 0.07176 0.0024 1.0000 0.3370
-6.250 -0.4525 0.07412 0.06840 0.0025 1.0000 0.3515
-6.000 -0.4772 0.05285 0.04574 -0.0359 1.0000 0.1129
-5.750 -0.4614 0.04855 0.04145 -0.0353 1.0000 0.1095
-5.500 -0.4492 0.04331 0.03519 -0.0355 1.0000 0.0997
-5.250 -0.4323 0.03944 0.03112 -0.0346 1.0000 0.0982
-5.000 -0.4150 0.03589 0.02713 -0.0332 1.0000 0.0975
-4.750 -0.3964 0.03290 0.02352 -0.0316 1.0000 0.0993
-4.500 -0.3786 0.03064 0.02120 -0.0302 1.0000 0.1103
-4.250 -0.3586 0.02814 0.01847 -0.0285 1.0000 0.1197
-4.000 -0.3387 0.02619 0.01630 -0.0268 1.0000 0.1372
-3.750 -0.3184 0.02426 0.01424 -0.0250 1.0000 0.1653
-3.500 -0.2989 0.02237 0.01260 -0.0231 1.0000 0.2205
-3.250 -0.2813 0.02034 0.01126 -0.0211 1.0000 0.3340
-3.000 -0.2692 0.01872 0.01058 -0.0178 1.0000 0.4848
-2.750 -0.0932 0.01702 0.00942 -0.0341 1.0000 1.0000
-2.500 -0.1144 0.01672 0.00907 -0.0288 1.0000 1.0000
-2.250 -0.1237 0.01668 0.00880 -0.0245 1.0000 1.0000
-2.000 -0.1229 0.01676 0.00860 -0.0214 1.0000 1.0000
-1.750 -0.1160 0.01691 0.00846 -0.0191 1.0000 1.0000
-1.500 -0.1055 0.01712 0.00839 -0.0174 1.0000 1.0000
-1.250 -0.0929 0.01738 0.00839 -0.0160 1.0000 1.0000
-1.000 -0.0789 0.01768 0.00845 -0.0149 1.0000 1.0000
-0.750 -0.0640 0.01802 0.00857 -0.0139 1.0000 1.0000
-0.500 -0.0485 0.01841 0.00873 -0.0131 1.0000 1.0000
-0.250 -0.0327 0.01884 0.00898 -0.0125 1.0000 1.0000
0.000 -0.0165 0.01931 0.00929 -0.0120 1.0000 1.0000
0.250 0.0006 0.01984 0.00966 -0.0117 0.9997 1.0000
0.500 0.0535 0.02088 0.01055 -0.0181 0.9843 1.0000
0.750 0.1058 0.02190 0.01142 -0.0242 0.9691 1.0000
1.000 0.1532 0.02278 0.01222 -0.0292 0.9531 1.0000
1.250 0.1973 0.02359 0.01299 -0.0333 0.9363 1.0000
1.500 0.2419 0.02438 0.01376 -0.0374 0.9195 1.0000
1.750 0.2887 0.02512 0.01452 -0.0417 0.9028 1.0000
2.000 0.3363 0.02579 0.01526 -0.0458 0.8861 1.0000
2.250 0.3709 0.02644 0.01596 -0.0476 0.8677 1.0000
2.500 0.4149 0.02698 0.01660 -0.0506 0.8498 1.0000
2.750 0.4614 0.02738 0.01711 -0.0535 0.8326 1.0000
3.000 0.4891 0.02799 0.01787 -0.0535 0.8130 1.0000
3.250 0.5250 0.02835 0.01836 -0.0541 0.7942 1.0000
3.500 0.5601 0.02860 0.01875 -0.0543 0.7755 1.0000
3.750 0.5858 0.02905 0.01934 -0.0532 0.7545 1.0000
4.000 0.6217 0.02894 0.01944 -0.0525 0.7358 1.0000
4.250 0.6428 0.02942 0.02005 -0.0506 0.7129 1.0000
4.500 0.6705 0.02942 0.02021 -0.0487 0.6914 1.0000
4.750 0.6982 0.02925 0.02019 -0.0464 0.6689 1.0000
5.000 0.7218 0.02927 0.02044 -0.0439 0.6439 1.0000
5.250 0.7466 0.02906 0.02037 -0.0412 0.6179 1.0000
5.500 0.7718 0.02868 0.02013 -0.0382 0.5903 1.0000
5.750 0.7975 0.02812 0.01966 -0.0351 0.5603 1.0000
6.000 0.8211 0.02773 0.01935 -0.0320 0.5260 1.0000
6.250 0.8455 0.02718 0.01877 -0.0288 0.4880 1.0000
6.500 0.8665 0.02708 0.01874 -0.0258 0.4435 1.0000
6.750 0.8874 0.02710 0.01855 -0.0227 0.3945 1.0000
7.000 0.9049 0.02779 0.01902 -0.0200 0.3413 1.0000
7.250 0.9212 0.02902 0.02002 -0.0176 0.2895 1.0000
7.500 0.9373 0.03059 0.02124 -0.0154 0.2426 1.0000
7.750 0.9549 0.03270 0.02307 -0.0136 0.2033 1.0000
8.000 0.9703 0.03503 0.02549 -0.0118 0.1714 1.0000
8.250 0.9893 0.03781 0.02820 -0.0104 0.1479 1.0000
8.500 1.0046 0.04058 0.03123 -0.0088 0.1294 1.0000
8.750 1.0214 0.04445 0.03541 -0.0074 0.1197 1.0000
9.000 1.0365 0.04792 0.03900 -0.0062 0.1093 1.0000
9.250 1.0403 0.05140 0.04306 -0.0043 0.1018 1.0000
9.500 1.0529 0.05596 0.04781 -0.0034 0.0970 1.0000
9.750 1.0487 0.06066 0.05307 -0.0017 0.0963 1.0000
10.000 1.0403 0.06553 0.05836 -0.0004 0.0962 1.0000
10.250 1.0282 0.07040 0.06354 0.0006 0.0963 1.0000
10.500 1.0135 0.07525 0.06860 0.0012 0.0967 1.0000
10.750 0.9975 0.08000 0.07348 0.0017 0.0972 1.0000
11.250 0.8484 0.10814 0.10162 -0.0221 0.1330 1.0000
11.500 0.8443 0.11509 0.10853 -0.0247 0.1355 1.0000
11.750 0.8450 0.12143 0.11487 -0.0263 0.1366 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 42 8.94% (mh42-il)