MH 45 9.85% (mh45-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 45 9.85% (mh45-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.46 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh45-il-1000000-n5.txt Download as CSV file: xf-mh45-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.8066 0.03828 0.03579 -0.0118 0.8322 0.0024
-8.750 -0.8152 0.03143 0.02834 -0.0111 0.8213 0.0023
-8.500 -0.8081 0.02701 0.02340 -0.0101 0.8126 0.0023
-8.250 -0.7941 0.02377 0.01973 -0.0091 0.8043 0.0023
-8.000 -0.7756 0.02142 0.01702 -0.0083 0.7970 0.0023
-7.750 -0.7546 0.01962 0.01491 -0.0075 0.7894 0.0023
-7.500 -0.7323 0.01807 0.01311 -0.0069 0.7824 0.0023
-7.250 -0.7089 0.01680 0.01163 -0.0063 0.7752 0.0023
-7.000 -0.6847 0.01572 0.01036 -0.0057 0.7685 0.0023
-6.750 -0.6598 0.01481 0.00928 -0.0052 0.7613 0.0023
-6.500 -0.6346 0.01398 0.00830 -0.0048 0.7547 0.0023
-6.250 -0.6089 0.01325 0.00744 -0.0043 0.7476 0.0023
-6.000 -0.5828 0.01263 0.00669 -0.0040 0.7409 0.0024
-5.750 -0.5565 0.01206 0.00603 -0.0036 0.7337 0.0024
-5.500 -0.5298 0.01156 0.00543 -0.0033 0.7271 0.0025
-5.250 -0.5029 0.01111 0.00490 -0.0031 0.7198 0.0025
-5.000 -0.4758 0.01074 0.00444 -0.0028 0.7129 0.0026
-4.750 -0.4484 0.01040 0.00403 -0.0026 0.7054 0.0026
-4.500 -0.4212 0.00999 0.00353 -0.0024 0.6982 0.0029
-4.250 -0.3936 0.00969 0.00318 -0.0022 0.6904 0.0033
-4.000 -0.3658 0.00946 0.00290 -0.0021 0.6827 0.0039
-3.750 -0.3379 0.00926 0.00264 -0.0019 0.6744 0.0045
-3.500 -0.3100 0.00904 0.00239 -0.0018 0.6666 0.0059
-3.250 -0.2821 0.00885 0.00218 -0.0017 0.6581 0.0091
-3.000 -0.2542 0.00864 0.00199 -0.0016 0.6497 0.0167
-2.750 -0.2264 0.00843 0.00179 -0.0015 0.6411 0.0295
-2.500 -0.1998 0.00793 0.00154 -0.0013 0.6319 0.0927
-2.250 -0.1730 0.00751 0.00137 -0.0012 0.6227 0.1628
-2.000 -0.1450 0.00737 0.00126 -0.0012 0.6129 0.1869
-1.750 -0.1173 0.00717 0.00116 -0.0011 0.6022 0.2263
-1.500 -0.0896 0.00699 0.00108 -0.0011 0.5913 0.2659
-1.250 -0.0618 0.00683 0.00101 -0.0010 0.5800 0.3043
-1.000 -0.0337 0.00674 0.00095 -0.0010 0.5677 0.3318
-0.750 -0.0056 0.00667 0.00090 -0.0010 0.5549 0.3579
-0.500 0.0224 0.00660 0.00086 -0.0009 0.5414 0.3870
-0.250 0.0505 0.00655 0.00083 -0.0009 0.5270 0.4151
0.000 0.0785 0.00649 0.00081 -0.0009 0.5125 0.4467
0.250 0.1064 0.00643 0.00080 -0.0009 0.4974 0.4792
0.500 0.1342 0.00639 0.00080 -0.0008 0.4817 0.5149
0.750 0.1619 0.00634 0.00081 -0.0008 0.4658 0.5527
1.000 0.1894 0.00628 0.00083 -0.0007 0.4499 0.5950
1.250 0.2166 0.00622 0.00086 -0.0005 0.4340 0.6429
1.500 0.2433 0.00613 0.00090 -0.0002 0.4180 0.6991
1.750 0.2692 0.00603 0.00094 0.0002 0.4020 0.7622
2.000 0.2941 0.00590 0.00100 0.0010 0.3863 0.8338
2.250 0.3207 0.00579 0.00108 0.0015 0.3699 0.9151
2.500 0.3724 0.00590 0.00118 -0.0037 0.3489 0.9680
2.750 0.4122 0.00606 0.00126 -0.0063 0.3305 0.9844
3.000 0.4453 0.00622 0.00135 -0.0075 0.3139 0.9939
3.250 0.4809 0.00639 0.00145 -0.0092 0.2966 0.9992
3.500 0.5101 0.00655 0.00154 -0.0095 0.2805 1.0000
3.750 0.5369 0.00673 0.00165 -0.0094 0.2636 1.0000
4.000 0.5636 0.00691 0.00177 -0.0092 0.2479 1.0000
4.250 0.5903 0.00713 0.00191 -0.0090 0.2295 1.0000
4.500 0.6169 0.00734 0.00205 -0.0088 0.2143 1.0000
4.750 0.6435 0.00757 0.00222 -0.0086 0.1967 1.0000
5.000 0.6700 0.00780 0.00239 -0.0085 0.1821 1.0000
5.250 0.6965 0.00804 0.00257 -0.0083 0.1673 1.0000
5.500 0.7228 0.00830 0.00277 -0.0081 0.1517 1.0000
5.750 0.7492 0.00855 0.00298 -0.0079 0.1400 1.0000
6.000 0.7754 0.00881 0.00320 -0.0077 0.1275 1.0000
6.250 0.8014 0.00910 0.00343 -0.0075 0.1152 1.0000
6.500 0.8274 0.00938 0.00368 -0.0073 0.1050 1.0000
6.750 0.8534 0.00967 0.00393 -0.0070 0.0951 1.0000
7.000 0.8793 0.00994 0.00420 -0.0068 0.0872 1.0000
7.250 0.9049 0.01028 0.00449 -0.0066 0.0777 1.0000
7.500 0.9302 0.01064 0.00481 -0.0063 0.0677 1.0000
7.750 0.9557 0.01096 0.00512 -0.0061 0.0601 1.0000
8.000 0.9809 0.01132 0.00547 -0.0058 0.0538 1.0000
8.250 1.0061 0.01166 0.00581 -0.0056 0.0482 1.0000
8.500 1.0309 0.01205 0.00618 -0.0053 0.0424 1.0000
8.750 1.0555 0.01244 0.00657 -0.0050 0.0373 1.0000
9.000 1.0799 0.01285 0.00698 -0.0046 0.0328 1.0000
9.250 1.1041 0.01327 0.00741 -0.0043 0.0288 1.0000
9.500 1.1276 0.01376 0.00791 -0.0039 0.0241 1.0000
9.750 1.1507 0.01428 0.00842 -0.0035 0.0201 1.0000
10.000 1.1735 0.01480 0.00895 -0.0030 0.0167 1.0000
10.250 1.1953 0.01543 0.00956 -0.0025 0.0129 1.0000
10.500 1.2174 0.01597 0.01013 -0.0020 0.0111 1.0000
10.750 1.2386 0.01658 0.01077 -0.0013 0.0095 1.0000
11.000 1.2600 0.01713 0.01138 -0.0008 0.0086 1.0000
11.250 1.2804 0.01774 0.01202 -0.0001 0.0076 1.0000
11.500 1.2994 0.01844 0.01276 0.0007 0.0066 1.0000
11.750 1.3185 0.01909 0.01347 0.0015 0.0060 1.0000
12.000 1.3364 0.01978 0.01421 0.0024 0.0052 1.0000
12.250 1.3522 0.02058 0.01506 0.0035 0.0044 1.0000
12.500 1.3669 0.02140 0.01593 0.0046 0.0037 1.0000
12.750 1.3779 0.02226 0.01686 0.0063 0.0032 1.0000
13.000 1.3830 0.02330 0.01798 0.0084 0.0027 1.0000
13.250 1.3882 0.02459 0.01933 0.0099 0.0022 1.0000
13.500 1.3947 0.02597 0.02079 0.0110 0.0019 1.0000
13.750 1.4006 0.02753 0.02243 0.0117 0.0017 1.0000
14.000 1.4053 0.02932 0.02431 0.0122 0.0015 1.0000
14.250 1.4087 0.03135 0.02643 0.0125 0.0013 1.0000
14.500 1.4099 0.03373 0.02891 0.0125 0.0010 1.0000
14.750 1.4148 0.03582 0.03110 0.0124 0.0012 1.0000
15.000 1.4150 0.03852 0.03390 0.0119 0.0011 1.0000
15.250 1.4103 0.04193 0.03742 0.0111 0.0009 1.0000
15.500 1.4031 0.04583 0.04144 0.0099 0.0008 1.0000
15.750 1.4047 0.04867 0.04438 0.0090 0.0009 1.0000
16.000 1.3955 0.05310 0.04893 0.0073 0.0009 1.0000
16.250 1.3826 0.05819 0.05415 0.0051 0.0008 1.0000
16.500 1.3745 0.06281 0.05888 0.0031 0.0008 1.0000
16.750 1.3584 0.06884 0.06505 0.0003 0.0008 1.0000
17.000 1.3351 0.07629 0.07264 -0.0033 0.0007 1.0000
17.250 1.3252 0.08164 0.07810 -0.0058 0.0008 1.0000
17.500 1.3012 0.08962 0.08622 -0.0098 0.0007 1.0000
17.750 1.2741 0.09837 0.09512 -0.0142 0.0007 1.0000
18.000 1.2628 0.10436 0.10121 -0.0171 0.0008 1.0000
18.250 1.2300 0.11475 0.11175 -0.0225 0.0008 1.0000
18.500 1.2116 0.12255 0.11966 -0.0265 0.0009 1.0000
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Polar data table (+)
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