MH 114 13.02% (mh114-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 114 13.02% (mh114-il) Reynolds number: 50,000 Max Cl/Cd: 25.99 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh114-il-50000-n5.txt Download as CSV file: xf-mh114-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 114 13.02%
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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.1437 0.11164 0.10533 -0.0679 0.9343 0.1014
-7.250 -0.1442 0.10939 0.10312 -0.0682 0.9262 0.1010
-7.000 -0.1405 0.10281 0.09645 -0.0735 0.9206 0.0581
-6.750 -0.1438 0.10074 0.09443 -0.0721 0.9117 0.0566
-6.500 -0.1516 0.09600 0.08972 -0.0777 0.9035 0.0503
-6.250 -0.1508 0.09347 0.08723 -0.0776 0.8951 0.0500
-6.000 -0.1364 0.08956 0.08331 -0.0814 0.8901 0.0496
-5.750 -0.1385 0.08701 0.08079 -0.0815 0.8808 0.0494
-5.500 -0.1232 0.08266 0.07642 -0.0864 0.8752 0.0490
-5.250 -0.1200 0.07906 0.07281 -0.0890 0.8666 0.0490
-5.000 -0.1014 0.07406 0.06774 -0.0951 0.8607 0.0485
-4.750 -0.0811 0.06872 0.06227 -0.1017 0.8548 0.0480
-4.500 -0.0607 0.06339 0.05673 -0.1078 0.8477 0.0475
-4.250 -0.0189 0.05652 0.04938 -0.1183 0.8440 0.0470
-4.000 0.0348 0.04982 0.04186 -0.1292 0.8417 0.0480
-3.750 0.0653 0.04624 0.03747 -0.1332 0.8345 0.0502
-3.500 0.0992 0.04444 0.03552 -0.1358 0.8299 0.0539
-3.250 0.1455 0.04164 0.03201 -0.1401 0.8271 0.0583
-3.000 0.1716 0.04055 0.03070 -0.1407 0.8206 0.0635
-2.750 0.2047 0.03927 0.02894 -0.1419 0.8152 0.0708
-2.500 0.2417 0.03810 0.02761 -0.1436 0.8115 0.0824
-2.250 0.2669 0.03755 0.02698 -0.1436 0.8051 0.0952
-2.000 0.2963 0.03693 0.02632 -0.1443 0.7990 0.1153
-1.750 0.3363 0.03606 0.02543 -0.1465 0.7954 0.1527
-1.500 0.3612 0.03586 0.02535 -0.1467 0.7880 0.2000
-1.250 0.3941 0.03544 0.02514 -0.1481 0.7823 0.2799
-1.000 0.4329 0.03487 0.02488 -0.1499 0.7788 0.3874
-0.750 0.4490 0.03524 0.02546 -0.1484 0.7696 0.4642
-0.500 0.4787 0.03498 0.02539 -0.1481 0.7646 0.5613
-0.250 0.4993 0.03498 0.02555 -0.1463 0.7582 0.6464
0.000 0.5130 0.03503 0.02576 -0.1433 0.7503 0.7308
0.250 0.5313 0.03422 0.02511 -0.1398 0.7462 0.8845
0.500 0.5465 0.03497 0.02563 -0.1389 0.7350 1.0000
0.750 0.5863 0.03494 0.02523 -0.1408 0.7310 1.0000
1.000 0.6034 0.03585 0.02595 -0.1400 0.7208 1.0000
1.250 0.6392 0.03587 0.02569 -0.1412 0.7160 1.0000
1.750 0.6902 0.03681 0.02627 -0.1412 0.7008 1.0000
2.000 0.7261 0.03669 0.02596 -0.1421 0.6966 1.0000
2.250 0.7398 0.03776 0.02694 -0.1408 0.6856 1.0000
2.500 0.7785 0.03740 0.02642 -0.1419 0.6822 1.0000
2.750 0.7884 0.03871 0.02767 -0.1402 0.6702 1.0000
3.000 0.8263 0.03832 0.02715 -0.1411 0.6666 1.0000
3.250 0.8360 0.03967 0.02847 -0.1394 0.6547 1.0000
3.500 0.8734 0.03924 0.02794 -0.1401 0.6510 1.0000
3.750 0.8826 0.04064 0.02932 -0.1384 0.6390 1.0000
4.000 0.9197 0.04017 0.02878 -0.1391 0.6352 1.0000
4.250 0.9282 0.04163 0.03025 -0.1373 0.6232 1.0000
4.500 0.9655 0.04108 0.02965 -0.1379 0.6193 1.0000
4.750 0.9730 0.04264 0.03122 -0.1360 0.6072 1.0000
5.000 1.0108 0.04199 0.03053 -0.1366 0.6034 1.0000
5.250 1.0167 0.04369 0.03229 -0.1347 0.5911 1.0000
5.500 1.0554 0.04292 0.03150 -0.1352 0.5874 1.0000
6.000 1.0994 0.04385 0.03247 -0.1337 0.5712 1.0000
6.500 1.1431 0.04477 0.03349 -0.1322 0.5551 1.0000
6.750 1.1438 0.04695 0.03574 -0.1300 0.5422 1.0000
7.000 1.1867 0.04566 0.03450 -0.1306 0.5388 1.0000
7.500 1.1910 0.04992 0.03892 -0.1266 0.5145 1.0000
7.750 1.2257 0.04917 0.03823 -0.1265 0.5091 1.0000
8.250 1.2663 0.05025 0.03948 -0.1247 0.4925 1.0000
8.750 1.3076 0.05124 0.04065 -0.1229 0.4757 1.0000
9.000 1.2998 0.05441 0.04394 -0.1207 0.4629 1.0000
9.500 1.3366 0.05577 0.04549 -0.1187 0.4457 1.0000
9.750 1.3314 0.05890 0.04874 -0.1169 0.4337 1.0000
10.000 1.3749 0.05693 0.04687 -0.1167 0.4285 1.0000
10.250 1.3613 0.06095 0.05103 -0.1148 0.4159 1.0000
10.500 1.3690 0.06279 0.05298 -0.1136 0.4062 1.0000
10.750 1.3936 0.06268 0.05301 -0.1127 0.3982 1.0000
11.000 1.3813 0.06686 0.05732 -0.1113 0.3863 1.0000
11.250 1.4282 0.06410 0.05465 -0.1106 0.3807 1.0000
11.500 1.4047 0.06963 0.06033 -0.1092 0.3682 1.0000
11.750 1.3984 0.07332 0.06416 -0.1082 0.3574 1.0000
12.000 1.4324 0.07181 0.06277 -0.1072 0.3505 1.0000
12.250 1.4074 0.07803 0.06914 -0.1065 0.3383 1.0000
12.500 1.4510 0.07508 0.06628 -0.1053 0.3321 1.0000
12.750 1.4263 0.08140 0.07276 -0.1049 0.3205 1.0000
13.000 1.4016 0.08817 0.07968 -0.1051 0.3088 1.0000
13.250 1.4496 0.08407 0.07569 -0.1032 0.3031 1.0000
13.500 1.4095 0.09336 0.08513 -0.1043 0.2908 1.0000
13.750 1.3911 0.09974 0.09164 -0.1051 0.2801 1.0000
14.000 1.4243 0.09744 0.08948 -0.1033 0.2737 1.0000
14.250 1.3844 0.10778 0.09994 -0.1059 0.2617 1.0000
14.500 1.4419 0.10102 0.09330 -0.1024 0.2571 1.0000
14.750 1.3891 0.11390 0.10631 -0.1064 0.2449 1.0000
15.000 1.3558 0.12406 0.11656 -0.1100 0.2336 1.0000
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Polar data table (+)
Polar graphs
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