MH 92 15.49% (mh92-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 92 15.49% (mh92-il) Reynolds number: 50,000 Max Cl/Cd: 24.85 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh92-il-50000-n5.txt Download as CSV file: xf-mh92-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 92 15.49%
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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6227 0.10119 0.09420 -0.0076 1.0000 0.0441
-12.000 -0.6490 0.09156 0.08449 -0.0142 1.0000 0.0432
-11.750 -0.6822 0.08262 0.07539 -0.0203 1.0000 0.0424
-11.500 -0.7111 0.07585 0.06840 -0.0240 1.0000 0.0419
-11.250 -0.7358 0.07044 0.06276 -0.0257 1.0000 0.0416
-11.000 -0.7545 0.06615 0.05823 -0.0260 1.0000 0.0414
-10.750 -0.7677 0.06256 0.05442 -0.0253 1.0000 0.0416
-10.500 -0.7773 0.05931 0.05094 -0.0239 1.0000 0.0418
-10.250 -0.7828 0.05635 0.04773 -0.0221 1.0000 0.0421
-10.000 -0.7840 0.05356 0.04468 -0.0202 1.0000 0.0424
-9.750 -0.7794 0.05081 0.04165 -0.0186 1.0000 0.0430
-9.500 -0.7699 0.04815 0.03870 -0.0173 1.0000 0.0436
-9.250 -0.7568 0.04561 0.03582 -0.0161 1.0000 0.0447
-9.000 -0.7398 0.04336 0.03334 -0.0153 1.0000 0.0464
-8.750 -0.7201 0.04158 0.03154 -0.0148 1.0000 0.0487
-8.500 -0.6976 0.03967 0.02942 -0.0143 1.0000 0.0516
-8.250 -0.6716 0.03788 0.02757 -0.0141 1.0000 0.0540
-8.000 -0.6472 0.03631 0.02598 -0.0138 1.0000 0.0576
-7.750 -0.6244 0.03484 0.02448 -0.0133 1.0000 0.0624
-7.500 -0.6035 0.03351 0.02309 -0.0125 1.0000 0.0682
-7.250 -0.5864 0.03220 0.02186 -0.0115 1.0000 0.0745
-7.000 -0.5721 0.03091 0.02063 -0.0101 1.0000 0.0837
-6.750 -0.5614 0.02973 0.01956 -0.0082 1.0000 0.0950
-6.500 -0.5574 0.02866 0.01866 -0.0054 1.0000 0.1099
-6.250 -0.5541 0.02752 0.01780 -0.0028 0.9911 0.1345
-6.000 -0.5300 0.02530 0.01640 -0.0045 0.9658 0.2322
-5.750 -0.5060 0.02395 0.01574 -0.0052 0.9441 0.3598
-5.500 -0.4811 0.02337 0.01556 -0.0048 0.9237 0.4508
-5.250 -0.4559 0.02326 0.01566 -0.0035 0.9044 0.5225
-5.000 -0.4279 0.02349 0.01598 -0.0020 0.8864 0.5780
-4.750 -0.3976 0.02385 0.01629 -0.0007 0.8692 0.6172
-4.500 -0.3693 0.02416 0.01645 0.0006 0.8522 0.6465
-4.250 -0.3385 0.02455 0.01667 0.0017 0.8358 0.6701
-4.000 -0.3115 0.02484 0.01677 0.0032 0.8196 0.6920
-3.750 -0.2864 0.02507 0.01681 0.0048 0.8039 0.7125
-3.500 -0.2599 0.02531 0.01685 0.0063 0.7889 0.7309
-3.250 -0.2299 0.02559 0.01693 0.0071 0.7738 0.7465
-3.000 -0.1991 0.02584 0.01700 0.0077 0.7582 0.7609
-2.750 -0.1696 0.02603 0.01701 0.0083 0.7430 0.7752
-2.500 -0.1419 0.02615 0.01694 0.0091 0.7284 0.7896
-2.250 -0.1158 0.02622 0.01683 0.0101 0.7147 0.8045
-2.000 -0.0898 0.02627 0.01670 0.0110 0.7010 0.8190
-1.750 -0.0520 0.02642 0.01669 0.0100 0.6857 0.8291
-1.250 0.0031 0.02646 0.01642 0.0108 0.6583 0.8561
-1.000 0.0436 0.02645 0.01622 0.0091 0.6448 0.8653
-0.750 0.0745 0.02646 0.01611 0.0086 0.6301 0.8774
-0.500 0.1052 0.02646 0.01600 0.0081 0.6162 0.8895
-0.250 0.1430 0.02639 0.01579 0.0065 0.6027 0.8987
0.000 0.1714 0.02633 0.01558 0.0064 0.5908 0.9103
0.250 0.2090 0.02628 0.01545 0.0044 0.5762 0.9193
0.500 0.2411 0.02626 0.01533 0.0034 0.5631 0.9291
0.750 0.2747 0.02618 0.01512 0.0022 0.5511 0.9385
1.000 0.3095 0.02611 0.01496 0.0006 0.5384 0.9469
1.250 0.3404 0.02616 0.01496 -0.0005 0.5256 0.9564
1.500 0.3777 0.02606 0.01478 -0.0026 0.5134 0.9638
1.750 0.4106 0.02602 0.01464 -0.0039 0.5023 0.9720
2.000 0.4461 0.02605 0.01466 -0.0060 0.4895 0.9797
2.250 0.4810 0.02603 0.01457 -0.0078 0.4783 0.9869
2.500 0.5157 0.02602 0.01450 -0.0096 0.4675 0.9942
2.750 0.5486 0.02615 0.01464 -0.0114 0.4559 1.0000
3.000 0.5679 0.02624 0.01462 -0.0102 0.4482 1.0000
3.250 0.5869 0.02663 0.01510 -0.0095 0.4379 1.0000
3.500 0.6063 0.02676 0.01512 -0.0082 0.4308 1.0000
3.750 0.6245 0.02725 0.01569 -0.0074 0.4208 1.0000
4.000 0.6436 0.02743 0.01578 -0.0061 0.4138 1.0000
4.250 0.6609 0.02801 0.01648 -0.0052 0.4047 1.0000
4.500 0.6795 0.02827 0.01669 -0.0038 0.3977 1.0000
4.750 0.6960 0.02887 0.01737 -0.0027 0.3895 1.0000
5.000 0.7135 0.02928 0.01779 -0.0013 0.3823 1.0000
5.250 0.7304 0.02979 0.01831 0.0000 0.3756 1.0000
5.500 0.7453 0.03047 0.01908 0.0014 0.3679 1.0000
5.750 0.7639 0.03074 0.01927 0.0029 0.3623 1.0000
6.000 0.7752 0.03173 0.02045 0.0045 0.3546 1.0000
6.250 0.7907 0.03228 0.02101 0.0061 0.3485 1.0000
6.500 0.8067 0.03280 0.02152 0.0078 0.3430 1.0000
6.750 0.8145 0.03393 0.02284 0.0098 0.3358 1.0000
7.000 0.8305 0.03441 0.02330 0.0115 0.3304 1.0000
7.250 0.8411 0.03532 0.02428 0.0135 0.3249 1.0000
7.500 0.8455 0.03656 0.02568 0.0158 0.3184 1.0000
7.750 0.8618 0.03702 0.02613 0.0175 0.3135 1.0000
8.000 0.8679 0.03818 0.02738 0.0198 0.3081 1.0000
8.250 0.8654 0.03984 0.02920 0.0226 0.3022 1.0000
8.500 0.8808 0.04040 0.02975 0.0242 0.2973 1.0000
8.750 0.8883 0.04150 0.03089 0.0263 0.2926 1.0000
9.000 0.8667 0.04433 0.03392 0.0297 0.2866 1.0000
9.250 0.8770 0.04528 0.03490 0.0314 0.2818 1.0000
9.500 0.9027 0.04542 0.03500 0.0322 0.2777 1.0000
9.750 0.7792 0.05632 0.04608 0.0355 0.2700 1.0000
10.000 0.7895 0.05767 0.04748 0.0362 0.2653 1.0000
10.250 0.8526 0.05399 0.04379 0.0382 0.2627 1.0000
10.500 0.7127 0.07328 0.06312 0.0311 0.2488 1.0000
10.750 0.7449 0.07175 0.06165 0.0331 0.2467 1.0000
11.250 0.7014 0.08491 0.07484 0.0281 0.2316 1.0000
11.750 0.6688 0.09684 0.08681 0.0235 0.2179 1.0000
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Polar data table (+)
Polar graphs
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