MH 93 15.98% (mh93-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 93 15.98% (mh93-il) Reynolds number: 50,000 Max Cl/Cd: 24.39 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh93-il-50000-n5.txt Download as CSV file: xf-mh93-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 93 15.98%
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6617 0.09526 0.08813 -0.0123 1.0000 0.0435
-12.250 -0.6899 0.08677 0.07950 -0.0179 1.0000 0.0430
-12.000 -0.7174 0.07969 0.07223 -0.0220 1.0000 0.0425
-11.750 -0.7408 0.07401 0.06636 -0.0243 1.0000 0.0423
-11.500 -0.7599 0.06933 0.06145 -0.0253 1.0000 0.0421
-11.250 -0.7762 0.06520 0.05708 -0.0252 1.0000 0.0421
-11.000 -0.7878 0.06163 0.05324 -0.0244 1.0000 0.0422
-10.750 -0.7955 0.05836 0.04972 -0.0231 1.0000 0.0425
-10.500 -0.7989 0.05535 0.04642 -0.0215 1.0000 0.0428
-10.250 -0.7975 0.05254 0.04332 -0.0198 1.0000 0.0433
-10.000 -0.7916 0.04983 0.04030 -0.0182 1.0000 0.0439
-9.750 -0.7818 0.04734 0.03748 -0.0168 1.0000 0.0451
-9.500 -0.7637 0.04542 0.03557 -0.0163 1.0000 0.0467
-9.250 -0.7460 0.04350 0.03350 -0.0156 1.0000 0.0490
-9.000 -0.7224 0.04140 0.03111 -0.0152 1.0000 0.0516
-8.750 -0.6960 0.03960 0.02938 -0.0154 1.0000 0.0543
-8.500 -0.6687 0.03793 0.02753 -0.0153 1.0000 0.0584
-8.250 -0.6469 0.03647 0.02615 -0.0149 1.0000 0.0626
-8.000 -0.6238 0.03507 0.02467 -0.0144 1.0000 0.0680
-7.750 -0.6063 0.03370 0.02333 -0.0135 1.0000 0.0752
-7.500 -0.5917 0.03237 0.02210 -0.0123 1.0000 0.0829
-7.250 -0.5799 0.03105 0.02088 -0.0108 1.0000 0.0944
-7.000 -0.5714 0.02979 0.01976 -0.0088 1.0000 0.1103
-6.750 -0.5695 0.02859 0.01887 -0.0060 1.0000 0.1313
-6.500 -0.5648 0.02721 0.01792 -0.0041 0.9841 0.1749
-6.000 -0.5211 0.02437 0.01636 -0.0051 0.9340 0.3897
-5.750 -0.4966 0.02398 0.01626 -0.0044 0.9139 0.4666
-5.500 -0.4719 0.02399 0.01642 -0.0028 0.8952 0.5292
-5.250 -0.4448 0.02429 0.01675 -0.0011 0.8775 0.5769
-4.750 -0.3897 0.02502 0.01724 0.0021 0.8436 0.6392
-4.500 -0.3617 0.02538 0.01745 0.0035 0.8273 0.6617
-4.250 -0.3321 0.02579 0.01768 0.0046 0.8114 0.6811
-4.000 -0.3038 0.02614 0.01784 0.0058 0.7959 0.6993
-3.750 -0.2765 0.02643 0.01793 0.0071 0.7810 0.7163
-3.500 -0.2503 0.02665 0.01797 0.0084 0.7667 0.7327
-3.250 -0.2256 0.02681 0.01792 0.0099 0.7533 0.7486
-3.000 -0.1941 0.02708 0.01801 0.0102 0.7382 0.7616
-2.750 -0.1625 0.02729 0.01805 0.0104 0.7239 0.7739
-2.500 -0.1359 0.02739 0.01797 0.0112 0.7105 0.7877
-2.250 -0.1122 0.02741 0.01781 0.0125 0.6982 0.8021
-2.000 -0.0762 0.02758 0.01782 0.0117 0.6834 0.8124
-1.750 -0.0460 0.02764 0.01773 0.0117 0.6698 0.8244
-1.500 -0.0218 0.02762 0.01755 0.0127 0.6581 0.8380
-1.250 0.0165 0.02767 0.01745 0.0113 0.6442 0.8474
-1.000 0.0460 0.02769 0.01736 0.0110 0.6307 0.8591
-0.750 0.0738 0.02768 0.01720 0.0112 0.6188 0.8712
-0.500 0.1111 0.02761 0.01699 0.0097 0.6062 0.8799
-0.250 0.1371 0.02764 0.01695 0.0098 0.5931 0.8920
0.000 0.1755 0.02757 0.01675 0.0079 0.5805 0.9001
0.250 0.2037 0.02750 0.01655 0.0079 0.5695 0.9105
0.500 0.2395 0.02748 0.01646 0.0061 0.5560 0.9189
0.750 0.2694 0.02745 0.01635 0.0054 0.5448 0.9281
1.000 0.3035 0.02735 0.01614 0.0041 0.5336 0.9364
1.250 0.3351 0.02739 0.01614 0.0029 0.5211 0.9447
1.500 0.3683 0.02733 0.01598 0.0016 0.5108 0.9527
1.750 0.4013 0.02731 0.01592 0.0002 0.4993 0.9602
2.000 0.4338 0.02737 0.01595 -0.0013 0.4879 0.9679
2.250 0.4680 0.02726 0.01573 -0.0028 0.4787 0.9747
2.500 0.5002 0.02743 0.01593 -0.0045 0.4667 0.9821
2.750 0.5354 0.02739 0.01584 -0.0064 0.4571 0.9884
3.000 0.5690 0.02749 0.01593 -0.0082 0.4468 0.9950
3.250 0.6000 0.02764 0.01610 -0.0095 0.4370 1.0000
3.500 0.6189 0.02788 0.01631 -0.0085 0.4288 1.0000
3.750 0.6376 0.02821 0.01664 -0.0075 0.4210 1.0000
4.000 0.6559 0.02858 0.01705 -0.0066 0.4127 1.0000
4.250 0.6746 0.02883 0.01724 -0.0053 0.4060 1.0000
4.500 0.6915 0.02941 0.01792 -0.0044 0.3973 1.0000
5.000 0.7255 0.03037 0.01896 -0.0019 0.3831 1.0000
5.250 0.7427 0.03076 0.01934 -0.0005 0.3765 1.0000
5.500 0.7589 0.03130 0.01990 0.0008 0.3702 1.0000
5.750 0.7723 0.03209 0.02081 0.0023 0.3628 1.0000
6.000 0.7901 0.03240 0.02107 0.0038 0.3575 1.0000
6.250 0.8007 0.03339 0.02221 0.0055 0.3506 1.0000
6.500 0.8133 0.03413 0.02301 0.0072 0.3443 1.0000
6.750 0.8316 0.03440 0.02323 0.0088 0.3397 1.0000
7.000 0.8347 0.03584 0.02487 0.0110 0.3329 1.0000
7.250 0.8445 0.03666 0.02576 0.0131 0.3271 1.0000
7.500 0.8635 0.03687 0.02591 0.0147 0.3228 1.0000
7.750 0.8576 0.03871 0.02797 0.0178 0.3167 1.0000
8.000 0.8596 0.03993 0.02928 0.0205 0.3113 1.0000
8.250 0.8778 0.04018 0.02949 0.0221 0.3070 1.0000
8.500 0.8682 0.04207 0.03151 0.0255 0.3018 1.0000
8.750 0.8481 0.04449 0.03406 0.0294 0.2963 1.0000
9.000 0.8590 0.04518 0.03476 0.0313 0.2919 1.0000
9.250 0.8784 0.04553 0.03509 0.0327 0.2880 1.0000
9.500 0.7316 0.05767 0.04733 0.0373 0.2790 1.0000
9.750 0.7525 0.05781 0.04749 0.0386 0.2752 1.0000
10.000 0.8047 0.05505 0.04475 0.0404 0.2730 1.0000
10.500 0.6354 0.08179 0.07149 0.0310 0.2488 1.0000
10.750 0.6437 0.08383 0.07355 0.0311 0.2442 1.0000
11.000 0.6671 0.08378 0.07356 0.0322 0.2416 1.0000
11.500 0.6356 0.09506 0.08487 0.0282 0.2281 1.0000
11.750 0.6607 0.09481 0.08469 0.0294 0.2255 1.0000
12.000 0.6203 0.10433 0.09420 0.0250 0.2169 1.0000
12.250 0.6332 0.10596 0.09589 0.0250 0.2128 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 93 15.98% (mh93-il)