MH 45 9.85% (mh45-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 45 9.85% (mh45-il) Reynolds number: 500,000 Max Cl/Cd: 81.11 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh45-il-500000.txt Download as CSV file: xf-mh45-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 45 9.85%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5839 0.08336 0.08143 0.0067 1.0000 0.0165
-8.500 -0.5888 0.07782 0.07593 0.0028 1.0000 0.0166
-8.250 -0.6002 0.07106 0.06923 -0.0031 1.0000 0.0166
-8.000 -0.6191 0.06016 0.05822 -0.0135 1.0000 0.0163
-7.750 -0.6230 0.05357 0.05146 -0.0174 1.0000 0.0165
-5.750 -0.5286 0.01929 0.01361 -0.0111 0.8487 0.0093
-5.500 -0.5050 0.01728 0.01131 -0.0100 0.8406 0.0089
-5.250 -0.4806 0.01575 0.00956 -0.0091 0.8322 0.0086
-5.000 -0.4556 0.01459 0.00822 -0.0083 0.8242 0.0086
-4.750 -0.4306 0.01366 0.00716 -0.0075 0.8165 0.0089
-4.500 -0.4048 0.01288 0.00628 -0.0069 0.8085 0.0093
-4.250 -0.3788 0.01233 0.00559 -0.0063 0.8013 0.0100
-4.000 -0.3529 0.01148 0.00467 -0.0058 0.7932 0.0119
-3.750 -0.3261 0.01111 0.00419 -0.0053 0.7862 0.0142
-3.500 -0.2996 0.01038 0.00347 -0.0049 0.7780 0.0295
-3.250 -0.2755 0.00936 0.00295 -0.0044 0.7710 0.1373
-3.000 -0.2491 0.00888 0.00274 -0.0042 0.7628 0.2085
-2.750 -0.2227 0.00851 0.00256 -0.0039 0.7556 0.2723
-2.500 -0.1956 0.00823 0.00241 -0.0038 0.7475 0.3186
-2.250 -0.1686 0.00798 0.00227 -0.0035 0.7400 0.3681
-2.000 -0.1420 0.00768 0.00216 -0.0032 0.7318 0.4319
-1.750 -0.1155 0.00740 0.00206 -0.0029 0.7239 0.4946
-1.500 -0.0890 0.00717 0.00196 -0.0024 0.7157 0.5495
-1.250 -0.0625 0.00693 0.00188 -0.0020 0.7070 0.6063
-1.000 -0.0370 0.00668 0.00180 -0.0013 0.6988 0.6700
-0.750 -0.0119 0.00640 0.00175 -0.0005 0.6893 0.7418
-0.500 0.0124 0.00611 0.00172 0.0007 0.6802 0.8252
-0.250 0.0444 0.00592 0.00171 0.0005 0.6708 0.9122
0.000 0.0977 0.00593 0.00169 -0.0046 0.6589 0.9605
0.250 0.1414 0.00598 0.00167 -0.0078 0.6470 0.9824
0.500 0.1849 0.00603 0.00163 -0.0110 0.6344 0.9963
0.750 0.2191 0.00606 0.00158 -0.0124 0.6215 1.0000
1.000 0.2453 0.00610 0.00155 -0.0120 0.6085 1.0000
1.250 0.2717 0.00615 0.00153 -0.0116 0.5945 1.0000
1.500 0.2983 0.00621 0.00152 -0.0112 0.5798 1.0000
1.750 0.3249 0.00629 0.00152 -0.0109 0.5643 1.0000
2.000 0.3516 0.00638 0.00154 -0.0106 0.5478 1.0000
2.250 0.3783 0.00648 0.00157 -0.0103 0.5307 1.0000
2.750 0.4319 0.00673 0.00167 -0.0098 0.4945 1.0000
3.000 0.4587 0.00687 0.00174 -0.0096 0.4756 1.0000
3.250 0.4855 0.00703 0.00183 -0.0094 0.4572 1.0000
3.500 0.5123 0.00720 0.00193 -0.0092 0.4389 1.0000
3.750 0.5391 0.00737 0.00205 -0.0090 0.4200 1.0000
4.000 0.5658 0.00756 0.00218 -0.0088 0.4015 1.0000
4.250 0.5925 0.00777 0.00232 -0.0086 0.3828 1.0000
4.500 0.6192 0.00797 0.00248 -0.0084 0.3641 1.0000
4.750 0.6457 0.00820 0.00265 -0.0082 0.3444 1.0000
5.000 0.6722 0.00844 0.00284 -0.0080 0.3256 1.0000
5.250 0.6986 0.00869 0.00304 -0.0078 0.3052 1.0000
5.750 0.7511 0.00926 0.00350 -0.0075 0.2640 1.0000
6.250 0.8028 0.00994 0.00405 -0.0071 0.2210 1.0000
6.750 0.8537 0.01073 0.00470 -0.0066 0.1796 1.0000
7.000 0.8789 0.01116 0.00507 -0.0064 0.1614 1.0000
7.250 0.9037 0.01162 0.00547 -0.0061 0.1441 1.0000
7.500 0.9286 0.01206 0.00588 -0.0059 0.1295 1.0000
7.750 0.9532 0.01253 0.00631 -0.0056 0.1160 1.0000
8.000 0.9774 0.01302 0.00679 -0.0052 0.1033 1.0000
8.250 1.0013 0.01355 0.00728 -0.0049 0.0912 1.0000
8.500 1.0255 0.01400 0.00774 -0.0046 0.0817 1.0000
8.750 1.0493 0.01449 0.00826 -0.0042 0.0735 1.0000
9.000 1.0720 0.01511 0.00886 -0.0037 0.0652 1.0000
9.250 1.0949 0.01566 0.00942 -0.0033 0.0576 1.0000
9.500 1.1174 0.01624 0.01006 -0.0028 0.0511 1.0000
9.750 1.1372 0.01711 0.01091 -0.0021 0.0437 1.0000
10.000 1.1596 0.01762 0.01149 -0.0015 0.0389 1.0000
10.250 1.1776 0.01860 0.01249 -0.0006 0.0332 1.0000
10.500 1.1978 0.01926 0.01321 0.0001 0.0291 1.0000
10.750 1.2115 0.02053 0.01452 0.0013 0.0251 1.0000
11.000 1.2308 0.02117 0.01524 0.0021 0.0227 1.0000
11.250 1.2456 0.02213 0.01622 0.0032 0.0199 1.0000
11.500 1.2565 0.02331 0.01751 0.0046 0.0179 1.0000
11.750 1.2695 0.02414 0.01842 0.0060 0.0164 1.0000
12.000 1.2758 0.02522 0.01957 0.0079 0.0152 1.0000
12.250 1.2751 0.02700 0.02141 0.0096 0.0137 1.0000
12.500 1.2767 0.02889 0.02342 0.0107 0.0130 1.0000
12.750 1.2827 0.03055 0.02520 0.0113 0.0122 1.0000
13.000 1.2888 0.03230 0.02705 0.0117 0.0113 1.0000
13.250 1.2930 0.03434 0.02915 0.0118 0.0102 1.0000
13.500 1.2842 0.03788 0.03280 0.0115 0.0095 1.0000
13.750 1.2757 0.04164 0.03671 0.0109 0.0091 1.0000
14.000 1.2749 0.04469 0.03990 0.0101 0.0087 1.0000
14.250 1.2766 0.04755 0.04287 0.0092 0.0077 1.0000
14.500 1.2707 0.05155 0.04697 0.0076 0.0069 1.0000
14.750 1.2612 0.05615 0.05174 0.0059 0.0071 1.0000
15.000 1.2510 0.06107 0.05677 0.0037 0.0069 1.0000
15.250 1.2267 0.06833 0.06415 0.0002 0.0064 1.0000
15.500 1.2118 0.07461 0.07059 -0.0029 0.0059 1.0000
15.750 1.2008 0.08014 0.07621 -0.0055 0.0064 1.0000
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Polar data table (+)
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