MH 121 8.76% (mh121-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 121 8.76% (mh121-il) Reynolds number: 50,000 Max Cl/Cd: 35.77 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh121-il-50000-n5.txt Download as CSV file: xf-mh121-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 121 8.76%
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3654 0.09560 0.08933 -0.0397 1.0000 0.0371
-8.500 -0.4332 0.09876 0.09206 -0.0410 1.0000 0.0371
-8.250 -0.4368 0.09584 0.08923 -0.0403 1.0000 0.0361
-8.000 -0.4431 0.09301 0.08651 -0.0396 1.0000 0.0354
-7.750 -0.4522 0.09028 0.08389 -0.0386 1.0000 0.0347
-7.500 -0.4642 0.08762 0.08134 -0.0375 1.0000 0.0342
-7.250 -0.4744 0.08458 0.07841 -0.0373 1.0000 0.0335
-7.000 -0.4821 0.08082 0.07472 -0.0385 1.0000 0.0329
-6.750 -0.4880 0.07654 0.07048 -0.0406 1.0000 0.0322
-6.500 -0.4924 0.07222 0.06614 -0.0424 1.0000 0.0314
-6.250 -0.4937 0.06763 0.06147 -0.0445 1.0000 0.0306
-6.000 -0.4909 0.06274 0.05640 -0.0469 1.0000 0.0297
-5.750 -0.4826 0.05765 0.05099 -0.0495 1.0000 0.0287
-5.500 -0.4676 0.05269 0.04551 -0.0520 1.0000 0.0276
-5.250 -0.4492 0.04879 0.04114 -0.0534 1.0000 0.0271
-5.000 -0.4282 0.04522 0.03707 -0.0545 1.0000 0.0269
-4.750 -0.4053 0.04176 0.03311 -0.0554 1.0000 0.0268
-4.500 -0.3805 0.03833 0.02917 -0.0564 1.0000 0.0269
-4.250 -0.3560 0.03531 0.02582 -0.0573 1.0000 0.0290
-4.000 -0.3309 0.03331 0.02327 -0.0576 1.0000 0.0331
-3.750 -0.3045 0.03142 0.02090 -0.0573 1.0000 0.0367
-3.500 -0.2791 0.02975 0.01882 -0.0563 1.0000 0.0386
-3.250 -0.2554 0.02791 0.01690 -0.0554 1.0000 0.0418
-3.000 -0.2311 0.02659 0.01536 -0.0546 1.0000 0.0477
-2.750 -0.2049 0.02539 0.01404 -0.0548 1.0000 0.0673
-2.500 -0.1641 0.02190 0.01218 -0.0592 1.0000 0.3273
-2.250 -0.1487 0.02165 0.01269 -0.0558 1.0000 0.5977
-2.000 -0.1395 0.02174 0.01296 -0.0507 1.0000 0.6922
-1.750 -0.1301 0.02170 0.01294 -0.0460 1.0000 0.7524
-1.500 -0.1133 0.02159 0.01266 -0.0437 1.0000 0.7862
-1.250 -0.0896 0.02154 0.01240 -0.0431 0.9975 0.8143
-1.000 -0.0621 0.02157 0.01211 -0.0433 0.9937 0.8487
-0.750 -0.0329 0.02145 0.01186 -0.0440 0.9893 0.8991
-0.500 0.0066 0.02141 0.01158 -0.0476 0.9836 1.0000
-0.250 0.0439 0.02182 0.01165 -0.0509 0.9800 1.0000
0.000 0.0777 0.02217 0.01172 -0.0532 0.9754 1.0000
0.250 0.1129 0.02263 0.01184 -0.0557 0.9712 1.0000
0.500 0.1459 0.02306 0.01208 -0.0577 0.9667 1.0000
0.750 0.1775 0.02346 0.01234 -0.0594 0.9613 1.0000
1.000 0.2129 0.02399 0.01275 -0.0617 0.9569 1.0000
1.250 0.2416 0.02437 0.01306 -0.0627 0.9506 1.0000
1.500 0.2759 0.02487 0.01352 -0.0648 0.9454 1.0000
1.750 0.3055 0.02530 0.01392 -0.0659 0.9389 1.0000
2.000 0.3393 0.02579 0.01442 -0.0678 0.9328 1.0000
2.250 0.3689 0.02623 0.01489 -0.0688 0.9255 1.0000
2.500 0.4040 0.02672 0.01546 -0.0709 0.9191 1.0000
2.750 0.4324 0.02714 0.01604 -0.0716 0.9105 1.0000
3.000 0.4676 0.02760 0.01662 -0.0735 0.9032 1.0000
3.250 0.4992 0.02799 0.01717 -0.0747 0.8939 1.0000
3.500 0.5293 0.02837 0.01773 -0.0756 0.8836 1.0000
3.750 0.5620 0.02871 0.01828 -0.0767 0.8729 1.0000
4.000 0.5965 0.02896 0.01896 -0.0780 0.8613 1.0000
4.250 0.6311 0.02909 0.01941 -0.0791 0.8479 1.0000
4.500 0.6673 0.02899 0.01968 -0.0800 0.8316 1.0000
4.750 0.7092 0.02829 0.01943 -0.0809 0.8096 1.0000
5.000 0.7540 0.02635 0.01802 -0.0802 0.7708 1.0000
5.250 0.7778 0.02475 0.01680 -0.0761 0.7126 1.0000
5.500 0.8305 0.02322 0.01384 -0.0730 0.3326 1.0000
5.750 0.8287 0.02608 0.01543 -0.0689 0.1684 1.0000
6.000 0.8394 0.02862 0.01729 -0.0668 0.0983 1.0000
6.250 0.8592 0.03108 0.01973 -0.0652 0.0716 1.0000
6.500 0.8895 0.03362 0.02234 -0.0652 0.0447 1.0000
6.750 0.9293 0.03669 0.02560 -0.0662 0.0336 1.0000
7.000 0.9552 0.03928 0.02834 -0.0661 0.0256 1.0000
7.250 0.9889 0.04323 0.03279 -0.0662 0.0238 1.0000
7.500 1.0126 0.04705 0.03721 -0.0649 0.0229 1.0000
7.750 1.0286 0.05098 0.04169 -0.0630 0.0224 1.0000
8.000 1.0384 0.05493 0.04617 -0.0605 0.0221 1.0000
8.250 1.0430 0.05892 0.05064 -0.0578 0.0220 1.0000
8.500 1.0432 0.06289 0.05503 -0.0549 0.0220 1.0000
8.750 1.0393 0.06681 0.05932 -0.0520 0.0220 1.0000
9.000 1.0316 0.07065 0.06347 -0.0492 0.0221 1.0000
9.250 1.0193 0.07426 0.06734 -0.0462 0.0221 1.0000
9.500 1.0045 0.07802 0.07131 -0.0437 0.0222 1.0000
9.750 0.9886 0.08202 0.07549 -0.0422 0.0224 1.0000
10.000 0.9715 0.08644 0.08008 -0.0417 0.0226 1.0000
10.250 0.9543 0.09135 0.08513 -0.0423 0.0227 1.0000
10.500 0.9383 0.09673 0.09061 -0.0442 0.0230 1.0000
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Polar data table (+)
Polar graphs
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