MH 42 8.94% (mh42-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 42 8.94% (mh42-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.03 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh42-il-1000000.txt Download as CSV file: xf-mh42-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5070 0.08388 0.08237 -0.0109 1.0000 0.0078
-8.500 -0.5084 0.07947 0.07798 -0.0134 1.0000 0.0078
-8.250 -0.5135 0.07444 0.07298 -0.0165 1.0000 0.0079
-8.000 -0.5237 0.06953 0.06811 -0.0202 1.0000 0.0078
-7.750 -0.5312 0.06289 0.06145 -0.0269 1.0000 0.0076
-5.000 -0.3749 0.01274 0.00773 -0.0315 0.8749 0.0045
-4.750 -0.3512 0.01140 0.00616 -0.0305 0.8602 0.0043
-4.500 -0.3266 0.01044 0.00501 -0.0296 0.8460 0.0042
-4.250 -0.3013 0.00972 0.00411 -0.0289 0.8321 0.0042
-4.000 -0.2751 0.00921 0.00346 -0.0284 0.8186 0.0042
-3.750 -0.2484 0.00880 0.00290 -0.0279 0.8055 0.0045
-3.500 -0.2214 0.00851 0.00248 -0.0276 0.7928 0.0049
-3.250 -0.1949 0.00798 0.00196 -0.0271 0.7804 0.0240
-3.000 -0.1681 0.00769 0.00174 -0.0269 0.7684 0.0526
-2.750 -0.1417 0.00730 0.00155 -0.0267 0.7568 0.1090
-2.500 -0.1148 0.00705 0.00141 -0.0266 0.7454 0.1548
-2.250 -0.0882 0.00675 0.00128 -0.0264 0.7345 0.2149
-2.000 -0.0614 0.00648 0.00117 -0.0263 0.7234 0.2774
-1.750 -0.0347 0.00621 0.00108 -0.0262 0.7126 0.3455
-1.500 -0.0083 0.00590 0.00101 -0.0260 0.7022 0.4319
-1.250 0.0178 0.00559 0.00094 -0.0257 0.6919 0.5249
-1.000 0.0440 0.00535 0.00090 -0.0254 0.6815 0.6048
-0.750 0.0700 0.00511 0.00088 -0.0249 0.6710 0.6818
-0.500 0.0960 0.00495 0.00087 -0.0245 0.6607 0.7447
-0.250 0.1217 0.00481 0.00086 -0.0238 0.6506 0.8013
0.000 0.1472 0.00471 0.00087 -0.0231 0.6402 0.8503
0.250 0.1729 0.00462 0.00088 -0.0224 0.6296 0.8982
0.500 0.2018 0.00459 0.00090 -0.0223 0.6186 0.9402
0.750 0.2398 0.00463 0.00092 -0.0244 0.6068 0.9659
1.000 0.2786 0.00470 0.00092 -0.0268 0.5941 0.9807
1.250 0.3180 0.00477 0.00094 -0.0293 0.5809 0.9899
1.500 0.3564 0.00484 0.00095 -0.0316 0.5669 0.9969
1.750 0.3915 0.00491 0.00097 -0.0332 0.5521 1.0000
2.000 0.4170 0.00499 0.00099 -0.0327 0.5376 1.0000
2.250 0.4427 0.00509 0.00103 -0.0323 0.5224 1.0000
2.500 0.4684 0.00519 0.00107 -0.0318 0.5066 1.0000
3.000 0.5201 0.00543 0.00121 -0.0310 0.4714 1.0000
3.250 0.5460 0.00558 0.00129 -0.0307 0.4517 1.0000
3.500 0.5719 0.00574 0.00139 -0.0303 0.4304 1.0000
3.750 0.5976 0.00593 0.00150 -0.0299 0.4077 1.0000
4.000 0.6233 0.00613 0.00162 -0.0295 0.3824 1.0000
4.250 0.6488 0.00637 0.00176 -0.0291 0.3548 1.0000
4.500 0.6744 0.00661 0.00191 -0.0288 0.3285 1.0000
4.750 0.6998 0.00689 0.00211 -0.0284 0.2994 1.0000
5.000 0.7250 0.00721 0.00231 -0.0280 0.2682 1.0000
5.250 0.7502 0.00754 0.00253 -0.0277 0.2374 1.0000
5.500 0.7745 0.00800 0.00280 -0.0272 0.1956 1.0000
5.750 0.7992 0.00841 0.00308 -0.0269 0.1652 1.0000
6.000 0.8237 0.00885 0.00338 -0.0265 0.1346 1.0000
6.250 0.8483 0.00928 0.00372 -0.0261 0.1100 1.0000
6.500 0.8730 0.00968 0.00405 -0.0257 0.0899 1.0000
6.750 0.8975 0.01012 0.00440 -0.0253 0.0711 1.0000
7.000 0.9216 0.01059 0.00478 -0.0248 0.0531 1.0000
7.250 0.9452 0.01113 0.00522 -0.0243 0.0355 1.0000
7.500 0.9690 0.01162 0.00567 -0.0239 0.0246 1.0000
7.750 0.9924 0.01217 0.00619 -0.0233 0.0172 1.0000
8.000 1.0170 0.01253 0.00659 -0.0229 0.0149 1.0000
8.250 1.0396 0.01315 0.00722 -0.0222 0.0104 1.0000
8.500 1.0634 0.01356 0.00763 -0.0218 0.0073 1.0000
8.750 1.0846 0.01434 0.00840 -0.0210 0.0037 1.0000
9.000 1.1046 0.01526 0.00945 -0.0199 0.0029 1.0000
9.250 1.1263 0.01590 0.01017 -0.0191 0.0027 1.0000
9.500 1.1468 0.01664 0.01101 -0.0182 0.0025 1.0000
9.750 1.1671 0.01736 0.01181 -0.0173 0.0023 1.0000
10.000 1.1855 0.01824 0.01280 -0.0162 0.0022 1.0000
10.250 1.2039 0.01906 0.01370 -0.0151 0.0021 1.0000
10.500 1.2214 0.01990 0.01466 -0.0139 0.0019 1.0000
10.750 1.2367 0.02090 0.01576 -0.0125 0.0018 1.0000
11.000 1.2498 0.02199 0.01695 -0.0109 0.0017 1.0000
11.250 1.2559 0.02356 0.01868 -0.0085 0.0016 1.0000
11.500 1.2524 0.02530 0.02060 -0.0046 0.0015 1.0000
11.750 1.2376 0.02790 0.02344 -0.0004 0.0014 1.0000
12.000 1.2400 0.02950 0.02515 0.0014 0.0014 1.0000
12.250 1.2510 0.03047 0.02620 0.0023 0.0013 1.0000
12.500 1.2536 0.03231 0.02816 0.0035 0.0012 1.0000
12.750 1.2486 0.03505 0.03106 0.0044 0.0012 1.0000
13.000 1.2451 0.03789 0.03405 0.0047 0.0012 1.0000
13.250 1.2414 0.04099 0.03729 0.0045 0.0011 1.0000
13.500 1.2340 0.04473 0.04119 0.0038 0.0012 1.0000
13.750 1.2287 0.04846 0.04505 0.0027 0.0011 1.0000
14.000 1.2161 0.05344 0.05020 0.0009 0.0011 1.0000
14.250 1.2020 0.05900 0.05592 -0.0016 0.0010 1.0000
14.500 1.1832 0.06561 0.06271 -0.0048 0.0012 1.0000
14.750 1.1718 0.07147 0.06869 -0.0079 0.0011 1.0000
15.000 1.1556 0.07855 0.07591 -0.0118 0.0011 1.0000
15.250 1.1384 0.08625 0.08375 -0.0161 0.0010 1.0000
15.500 1.1136 0.09587 0.09352 -0.0215 0.0011 1.0000
15.750 1.0945 0.10467 0.10245 -0.0263 0.0012 1.0000
16.000 1.0757 0.11385 0.11174 -0.0314 0.0011 1.0000
16.250 1.0546 0.12382 0.12182 -0.0368 0.0012 1.0000
16.500 1.0315 0.13473 0.13284 -0.0427 0.0012 1.0000
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Polar data table (+)
Polar graphs
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