MH 150 23.89% (mh150-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 150 23.89% (mh150-il) Reynolds number: 100,000 Max Cl/Cd: 38.49 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh150-il-100000-n5.txt Download as CSV file: xf-mh150-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 150 23.89%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.4223 0.11724 0.11157 -0.0716 1.0001 0.0571
-16.500 -0.4111 0.11582 0.11026 -0.0726 1.0001 0.0591
-16.250 -0.4422 0.10710 0.10136 -0.0770 1.0001 0.0623
-16.000 -0.4276 0.10541 0.09976 -0.0792 0.9886 0.0650
-15.750 -0.4410 0.09815 0.09231 -0.0846 0.9797 0.0688
-15.500 -0.4243 0.09595 0.09020 -0.0875 0.9684 0.0722
-15.250 -0.4284 0.09058 0.08471 -0.0916 0.9582 0.0764
-15.000 -0.4227 0.08722 0.08134 -0.0944 0.9462 0.0806
-14.750 -0.4228 0.08338 0.07747 -0.0969 0.9340 0.0849
-14.500 -0.4258 0.07929 0.07329 -0.0994 0.9230 0.0897
-14.250 -0.4232 0.07647 0.07047 -0.1008 0.9109 0.0941
-14.000 -0.4321 0.07200 0.06584 -0.1031 0.9005 0.0993
-13.750 -0.4270 0.06986 0.06375 -0.1039 0.8895 0.1040
-13.500 -0.4336 0.06597 0.05974 -0.1058 0.8800 0.1095
-13.250 -0.4311 0.06352 0.05730 -0.1068 0.8697 0.1147
-13.000 -0.4352 0.06021 0.05387 -0.1082 0.8612 0.1203
-12.750 -0.4347 0.05745 0.05109 -0.1097 0.8512 0.1262
-12.500 -0.4358 0.05465 0.04822 -0.1108 0.8430 0.1320
-12.250 -0.4372 0.05174 0.04524 -0.1125 0.8342 0.1384
-12.000 -0.4354 0.04938 0.04286 -0.1137 0.8254 0.1445
-11.750 -0.4390 0.04645 0.03980 -0.1150 0.8182 0.1512
-11.500 -0.4337 0.04452 0.03789 -0.1162 0.8090 0.1578
-11.250 -0.4368 0.04162 0.03486 -0.1179 0.8010 0.1652
-11.000 -0.4287 0.04012 0.03337 -0.1185 0.7941 0.1721
-10.750 -0.4307 0.03741 0.03053 -0.1205 0.7850 0.1800
-10.500 -0.4187 0.03637 0.02952 -0.1207 0.7779 0.1871
-10.250 -0.4196 0.03415 0.02714 -0.1220 0.7707 0.1951
-10.000 -0.4086 0.03349 0.02653 -0.1219 0.7625 0.2019
-9.750 -0.4028 0.03170 0.02455 -0.1235 0.7556 0.2106
-9.500 -0.3837 0.03115 0.02400 -0.1241 0.7495 0.2180
-9.250 -0.3694 0.02986 0.02255 -0.1263 0.7413 0.2271
-9.000 -0.3460 0.02945 0.02212 -0.1270 0.7350 0.2346
-8.750 -0.3225 0.02839 0.02081 -0.1293 0.7299 0.2440
-8.500 -0.2992 0.02828 0.02074 -0.1296 0.7220 0.2509
-8.250 -0.2745 0.02741 0.01963 -0.1318 0.7154 0.2605
-8.000 -0.2466 0.02736 0.01956 -0.1317 0.7103 0.2667
-7.750 -0.2202 0.02687 0.01890 -0.1332 0.7040 0.2753
-7.250 -0.1659 0.02646 0.01837 -0.1341 0.6914 0.2886
-7.000 -0.1343 0.02579 0.01740 -0.1363 0.6869 0.2974
-6.750 -0.1099 0.02589 0.01759 -0.1357 0.6797 0.3023
-6.500 -0.0820 0.02573 0.01735 -0.1362 0.6733 0.3088
-6.250 -0.0496 0.02516 0.01651 -0.1383 0.6682 0.3169
-6.000 -0.0224 0.02517 0.01653 -0.1379 0.6632 0.3216
-5.750 0.0042 0.02512 0.01648 -0.1382 0.6564 0.3274
-5.500 0.0359 0.02473 0.01588 -0.1399 0.6506 0.3349
-5.250 0.0655 0.02456 0.01563 -0.1402 0.6459 0.3400
-5.000 0.0927 0.02456 0.01563 -0.1402 0.6402 0.3452
-4.750 0.1215 0.02443 0.01541 -0.1410 0.6338 0.3515
-4.500 0.1537 0.02414 0.01495 -0.1425 0.6286 0.3581
-4.250 0.1827 0.02407 0.01485 -0.1424 0.6243 0.3627
-4.000 0.2099 0.02408 0.01485 -0.1427 0.6183 0.3683
-3.750 0.2403 0.02394 0.01460 -0.1439 0.6121 0.3749
-3.500 0.2708 0.02379 0.01436 -0.1446 0.6071 0.3803
-3.250 0.3006 0.02373 0.01425 -0.1448 0.6031 0.3851
-3.000 0.3279 0.02378 0.01429 -0.1452 0.5972 0.3906
-2.750 0.3587 0.02369 0.01409 -0.1464 0.5913 0.3972
-2.500 0.3882 0.02363 0.01398 -0.1468 0.5864 0.4023
-2.250 0.4184 0.02359 0.01388 -0.1472 0.5825 0.4074
-2.000 0.4459 0.02368 0.01398 -0.1476 0.5770 0.4132
-1.750 0.4766 0.02368 0.01388 -0.1488 0.5714 0.4201
-1.500 0.5044 0.02372 0.01392 -0.1488 0.5666 0.4250
-1.250 0.5347 0.02371 0.01385 -0.1492 0.5627 0.4310
-1.000 0.5634 0.02382 0.01393 -0.1499 0.5577 0.4379
-0.750 0.5915 0.02396 0.01406 -0.1505 0.5523 0.4443
-0.500 0.6183 0.02410 0.01422 -0.1504 0.5478 0.4497
-0.250 0.6488 0.02414 0.01420 -0.1510 0.5438 0.4570
0.000 0.6817 0.02417 0.01411 -0.1523 0.5399 0.4655
0.250 0.7034 0.02452 0.01459 -0.1516 0.5343 0.4708
0.500 0.7299 0.02473 0.01482 -0.1517 0.5295 0.4777
0.750 0.7617 0.02482 0.01481 -0.1528 0.5256 0.4866
1.000 0.7904 0.02493 0.01491 -0.1529 0.5223 0.4931
1.250 0.8156 0.02525 0.01528 -0.1528 0.5180 0.5008
1.500 0.8417 0.02561 0.01564 -0.1533 0.5128 0.5102
1.750 0.8653 0.02588 0.01598 -0.1527 0.5085 0.5162
2.000 0.8936 0.02604 0.01611 -0.1529 0.5048 0.5242
2.250 0.9269 0.02614 0.01609 -0.1541 0.5017 0.5342
2.500 0.9455 0.02669 0.01678 -0.1530 0.4974 0.5405
2.750 0.9665 0.02720 0.01737 -0.1524 0.4929 0.5490
3.000 0.9930 0.02753 0.01769 -0.1528 0.4888 0.5582
3.250 1.0181 0.02777 0.01795 -0.1523 0.4854 0.5652
3.500 1.0491 0.02792 0.01802 -0.1530 0.4824 0.5748
3.750 1.0681 0.02854 0.01873 -0.1523 0.4782 0.5830
4.000 1.0825 0.02926 0.01958 -0.1508 0.4738 0.5898
4.250 1.1048 0.02978 0.02013 -0.1505 0.4701 0.5993
4.500 1.1293 0.03013 0.02049 -0.1503 0.4669 0.6074
4.750 1.1561 0.03035 0.02069 -0.1501 0.4641 0.6154
5.000 1.1837 0.03075 0.02105 -0.1507 0.4610 0.6258
5.250 1.1814 0.03198 0.02250 -0.1472 0.4562 0.6314
5.500 1.1917 0.03291 0.02353 -0.1454 0.4521 0.6387
5.750 1.2148 0.03349 0.02410 -0.1455 0.4488 0.6487
6.000 1.2382 0.03383 0.02447 -0.1449 0.4461 0.6557
6.250 1.2678 0.03396 0.02456 -0.1451 0.4439 0.6643
6.500 1.2704 0.03567 0.02640 -0.1435 0.4396 0.6733
6.750 1.2578 0.03802 0.02897 -0.1400 0.4345 0.6781
7.000 1.2676 0.03921 0.03024 -0.1387 0.4307 0.6853
7.250 1.2945 0.03961 0.03061 -0.1391 0.4280 0.6957
7.500 1.3200 0.03970 0.03070 -0.1385 0.4259 0.7021
7.750 1.3540 0.03953 0.03048 -0.1390 0.4241 0.7110
8.000 1.2512 0.04952 0.04101 -0.1323 0.4128 0.7122
8.250 1.2713 0.05017 0.04169 -0.1319 0.4100 0.7204
8.500 1.2996 0.04990 0.04140 -0.1315 0.4082 0.7281
8.750 1.3367 0.04930 0.04076 -0.1322 0.4068 0.7383
9.000 1.3703 0.04864 0.04007 -0.1319 0.4055 0.7456
9.250 1.1933 0.06963 0.06163 -0.1274 0.3853 0.7406
9.500 1.2399 0.06677 0.05875 -0.1268 0.3862 0.7499
9.750 1.2938 0.06374 0.05564 -0.1271 0.3871 0.7610
12.250 1.0574 0.12965 0.12267 -0.1309 0.3046 0.8003
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