MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 30 7.84% (mh30-il) Reynolds number: 50,000 Max Cl/Cd: 34.78 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh30-il-50000.txt Download as CSV file: xf-mh30-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4972 0.11899 0.11218 -0.0052 1.0000 0.1951
-9.250 -0.4807 0.11385 0.10694 -0.0044 1.0000 0.2018
-9.000 -0.4973 0.11308 0.10631 -0.0073 1.0000 0.2091
-8.750 -0.4750 0.10749 0.10070 -0.0057 1.0000 0.2190
-8.500 -0.4735 0.10418 0.09746 -0.0064 1.0000 0.2264
-8.250 -0.4894 0.10304 0.09647 -0.0084 1.0000 0.2362
-8.000 -0.4707 0.09816 0.09159 -0.0071 1.0000 0.2478
-7.750 -0.4628 0.09429 0.08777 -0.0066 1.0000 0.2584
-7.500 -0.4604 0.09106 0.08462 -0.0065 1.0000 0.2694
-7.250 -0.4611 0.08811 0.08176 -0.0063 1.0000 0.2810
-6.500 -0.4590 0.07912 0.07305 -0.0039 1.0000 0.3220
-6.250 -0.4610 0.07659 0.07061 -0.0030 1.0000 0.3424
-5.750 -0.4665 0.05534 0.04844 -0.0378 1.0000 0.1277
-5.500 -0.4525 0.04984 0.04272 -0.0382 1.0000 0.1105
-5.250 -0.4379 0.04472 0.03701 -0.0386 1.0000 0.0988
-5.000 -0.4217 0.04033 0.03209 -0.0381 1.0000 0.0925
-4.750 -0.4017 0.03669 0.02753 -0.0371 1.0000 0.0883
-4.500 -0.3836 0.03379 0.02461 -0.0360 1.0000 0.0944
-4.250 -0.3619 0.03124 0.02145 -0.0347 1.0000 0.1006
-4.000 -0.3390 0.02838 0.01830 -0.0334 1.0000 0.1061
-3.750 -0.3145 0.02599 0.01552 -0.0319 1.0000 0.1171
-3.500 -0.2923 0.02408 0.01370 -0.0305 1.0000 0.1478
-3.250 -0.2664 0.02179 0.01147 -0.0290 1.0000 0.1949
-3.000 -0.2469 0.01909 0.00999 -0.0271 1.0000 0.3713
-2.750 -0.2436 0.01689 0.00968 -0.0199 1.0000 0.6728
-2.500 -0.1462 0.01617 0.00843 -0.0287 1.0000 1.0000
-2.250 -0.1375 0.01600 0.00785 -0.0265 1.0000 1.0000
-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 0.0094 0.01676 0.00638 -0.0178 1.0000 1.0000
0.000 0.0290 0.01701 0.00649 -0.0171 1.0000 1.0000
0.250 0.0484 0.01731 0.00662 -0.0164 1.0000 1.0000
0.500 0.0676 0.01764 0.00685 -0.0157 1.0000 1.0000
0.750 0.0865 0.01802 0.00715 -0.0151 1.0000 1.0000
1.000 0.1050 0.01844 0.00751 -0.0146 1.0000 1.0000
1.250 0.1232 0.01893 0.00796 -0.0141 1.0000 1.0000
1.500 0.1409 0.01947 0.00847 -0.0137 1.0000 1.0000
1.750 0.1581 0.02008 0.00907 -0.0134 1.0000 1.0000
2.000 0.1747 0.02077 0.00976 -0.0131 1.0000 1.0000
2.250 0.1908 0.02154 0.01055 -0.0130 1.0000 1.0000
2.500 0.2480 0.02303 0.01214 -0.0206 0.9814 1.0000
2.750 0.3146 0.02433 0.01364 -0.0294 0.9539 1.0000
3.000 0.3753 0.02523 0.01475 -0.0363 0.9245 1.0000
3.250 0.4351 0.02579 0.01557 -0.0423 0.8940 1.0000
3.500 0.5017 0.02586 0.01608 -0.0485 0.8629 1.0000
3.750 0.5609 0.02549 0.01607 -0.0523 0.8296 1.0000
4.000 0.6166 0.02459 0.01554 -0.0541 0.7955 1.0000
4.250 0.6575 0.02371 0.01504 -0.0531 0.7574 1.0000
4.500 0.6937 0.02275 0.01429 -0.0507 0.7157 1.0000
4.750 0.7221 0.02215 0.01378 -0.0475 0.6675 1.0000
5.000 0.7471 0.02192 0.01352 -0.0440 0.6126 1.0000
5.250 0.7697 0.02213 0.01355 -0.0406 0.5529 1.0000
5.500 0.7890 0.02279 0.01402 -0.0374 0.4892 1.0000
5.750 0.8077 0.02372 0.01467 -0.0345 0.4257 1.0000
6.000 0.8260 0.02492 0.01567 -0.0319 0.3636 1.0000
6.250 0.8428 0.02638 0.01692 -0.0295 0.3028 1.0000
6.500 0.8602 0.02817 0.01843 -0.0273 0.2474 1.0000
6.750 0.8792 0.03037 0.02034 -0.0254 0.2007 1.0000
7.000 0.8971 0.03248 0.02223 -0.0237 0.1622 1.0000
7.250 0.9191 0.03557 0.02563 -0.0221 0.1394 1.0000
7.500 0.9364 0.03818 0.02840 -0.0206 0.1191 1.0000
7.750 0.9559 0.04180 0.03226 -0.0192 0.1082 1.0000
8.000 0.9688 0.04611 0.03733 -0.0170 0.1034 1.0000
8.250 0.9804 0.05050 0.04216 -0.0153 0.0999 1.0000
8.500 0.9868 0.05490 0.04690 -0.0136 0.0948 1.0000
8.750 0.9830 0.05937 0.05196 -0.0117 0.0921 1.0000
9.000 0.9772 0.06397 0.05697 -0.0103 0.0903 1.0000
9.250 0.9652 0.06901 0.06234 -0.0092 0.0908 1.0000
9.500 0.9495 0.07417 0.06773 -0.0087 0.0925 1.0000
9.750 0.9325 0.07904 0.07272 -0.0083 0.0940 1.0000
10.000 0.9179 0.08402 0.07776 -0.0088 0.0953 1.0000
10.250 0.9078 0.08961 0.08336 -0.0099 0.0963 1.0000
10.500 0.7317 0.10380 0.09782 -0.0232 0.1325 1.0000
10.750 0.7377 0.10965 0.10373 -0.0235 0.1363 1.0000
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Polar data table (+)
Polar graphs
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