MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 30 7.84% (mh30-il) Reynolds number: 50,000 Max Cl/Cd: 35.72 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh30-il-50000-n5.txt Download as CSV file: xf-mh30-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 30 7.84%
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4930 0.11274 0.10564 -0.0126 1.0000 0.0477
-9.500 -0.4885 0.10873 0.10168 -0.0136 1.0000 0.0460
-9.250 -0.4854 0.10471 0.09771 -0.0151 1.0000 0.0434
-8.750 -0.4924 0.09458 0.08776 -0.0236 1.0000 0.0368
-8.500 -0.4891 0.09081 0.08404 -0.0242 1.0000 0.0362
-8.250 -0.4902 0.08653 0.07984 -0.0265 1.0000 0.0361
-8.000 -0.4905 0.08266 0.07605 -0.0280 1.0000 0.0355
-7.750 -0.4922 0.07813 0.07159 -0.0310 1.0000 0.0351
-7.500 -0.4920 0.07357 0.06705 -0.0337 1.0000 0.0346
-7.250 -0.4913 0.06904 0.06251 -0.0359 1.0000 0.0339
-7.000 -0.4899 0.06460 0.05800 -0.0377 1.0000 0.0333
-6.750 -0.4878 0.06001 0.05330 -0.0392 1.0000 0.0329
-6.500 -0.4838 0.05556 0.04867 -0.0401 1.0000 0.0324
-6.250 -0.4775 0.05130 0.04415 -0.0405 1.0000 0.0319
-6.000 -0.4689 0.04715 0.03967 -0.0403 1.0000 0.0317
-5.750 -0.4576 0.04329 0.03542 -0.0398 1.0000 0.0316
-5.500 -0.4437 0.03967 0.03120 -0.0390 1.0000 0.0317
-5.250 -0.4275 0.03637 0.02740 -0.0379 1.0000 0.0320
-5.000 -0.4090 0.03341 0.02394 -0.0367 1.0000 0.0328
-4.750 -0.3887 0.03075 0.02077 -0.0352 1.0000 0.0345
-4.500 -0.3683 0.02857 0.01821 -0.0340 1.0000 0.0391
-4.250 -0.3478 0.02693 0.01638 -0.0327 1.0000 0.0457
-4.000 -0.3256 0.02499 0.01411 -0.0310 1.0000 0.0510
-3.750 -0.3048 0.02353 0.01259 -0.0297 1.0000 0.0650
-3.500 -0.2826 0.02204 0.01103 -0.0285 1.0000 0.0856
-3.250 -0.2603 0.02050 0.00970 -0.0276 1.0000 0.1336
-3.000 -0.2396 0.01893 0.00883 -0.0270 1.0000 0.2616
-2.750 -0.2220 0.01769 0.00843 -0.0254 1.0000 0.4387
-2.500 -0.2080 0.01680 0.00815 -0.0220 1.0000 0.6124
-2.250 -0.1912 0.01624 0.00803 -0.0180 1.0000 0.7841
-2.000 -0.1229 0.01594 0.00741 -0.0249 1.0000 1.0000
-1.750 -0.1059 0.01595 0.00706 -0.0235 1.0000 1.0000
-1.500 -0.0877 0.01600 0.00679 -0.0224 1.0000 1.0000
-1.250 -0.0688 0.01608 0.00659 -0.0213 1.0000 1.0000
-1.000 -0.0495 0.01620 0.00641 -0.0203 1.0000 1.0000
-0.750 -0.0300 0.01636 0.00634 -0.0194 1.0000 1.0000
-0.500 -0.0103 0.01654 0.00633 -0.0186 1.0000 1.0000
-0.250 0.0132 0.01678 0.00640 -0.0186 0.9981 1.0000
0.000 0.0554 0.01716 0.00660 -0.0221 0.9868 1.0000
0.250 0.0973 0.01753 0.00679 -0.0256 0.9753 1.0000
0.500 0.1392 0.01787 0.00704 -0.0289 0.9632 1.0000
0.750 0.1807 0.01818 0.00729 -0.0320 0.9505 1.0000
1.000 0.2217 0.01844 0.00753 -0.0349 0.9372 1.0000
1.250 0.2624 0.01865 0.00774 -0.0377 0.9231 1.0000
1.500 0.3034 0.01882 0.00795 -0.0403 0.9084 1.0000
1.750 0.3437 0.01894 0.00813 -0.0426 0.8929 1.0000
2.000 0.3828 0.01898 0.00828 -0.0445 0.8764 1.0000
2.250 0.4173 0.01900 0.00839 -0.0453 0.8575 1.0000
2.500 0.4506 0.01897 0.00847 -0.0457 0.8373 1.0000
2.750 0.4814 0.01894 0.00854 -0.0456 0.8152 1.0000
3.000 0.5123 0.01886 0.00867 -0.0452 0.7921 1.0000
3.250 0.5411 0.01879 0.00873 -0.0445 0.7663 1.0000
3.500 0.5679 0.01876 0.00882 -0.0434 0.7368 1.0000
3.750 0.5948 0.01875 0.00890 -0.0421 0.7044 1.0000
4.000 0.6211 0.01877 0.00899 -0.0408 0.6686 1.0000
4.250 0.6464 0.01889 0.00921 -0.0392 0.6289 1.0000
4.500 0.6705 0.01914 0.00944 -0.0376 0.5854 1.0000
4.750 0.6935 0.01951 0.00975 -0.0360 0.5393 1.0000
5.000 0.7151 0.02002 0.01021 -0.0343 0.4900 1.0000
5.250 0.7358 0.02064 0.01074 -0.0326 0.4404 1.0000
5.500 0.7557 0.02139 0.01137 -0.0310 0.3906 1.0000
5.750 0.7750 0.02224 0.01213 -0.0295 0.3409 1.0000
6.000 0.7937 0.02321 0.01314 -0.0281 0.2927 1.0000
6.250 0.8120 0.02430 0.01414 -0.0267 0.2461 1.0000
6.500 0.8296 0.02555 0.01526 -0.0254 0.2025 1.0000
6.750 0.8471 0.02695 0.01654 -0.0242 0.1622 1.0000
7.000 0.8647 0.02855 0.01811 -0.0230 0.1271 1.0000
7.250 0.8810 0.03023 0.01971 -0.0217 0.0987 1.0000
7.500 0.8989 0.03228 0.02181 -0.0203 0.0814 1.0000
7.750 0.9164 0.03426 0.02394 -0.0189 0.0664 1.0000
8.000 0.9333 0.03642 0.02623 -0.0176 0.0559 1.0000
8.250 0.9524 0.03908 0.02916 -0.0163 0.0496 1.0000
8.500 0.9701 0.04241 0.03273 -0.0150 0.0453 1.0000
8.750 0.9822 0.04518 0.03600 -0.0135 0.0393 1.0000
9.000 0.9904 0.04801 0.03884 -0.0123 0.0350 1.0000
9.250 0.9957 0.05207 0.04355 -0.0104 0.0336 1.0000
9.500 0.9946 0.05632 0.04831 -0.0085 0.0327 1.0000
9.750 0.9877 0.06057 0.05298 -0.0068 0.0321 1.0000
10.000 0.9750 0.06454 0.05726 -0.0051 0.0319 1.0000
10.250 0.9583 0.06872 0.06167 -0.0042 0.0319 1.0000
10.500 0.9407 0.07329 0.06644 -0.0048 0.0321 1.0000
10.750 0.9228 0.07852 0.07183 -0.0069 0.0324 1.0000
11.000 0.9040 0.08476 0.07818 -0.0105 0.0328 1.0000
11.250 0.8869 0.09182 0.08532 -0.0153 0.0332 1.0000
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Polar data table (+)
Polar graphs
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