MH 81 13% (mh81-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 81 13% (mh81-il) Reynolds number: 50,000 Max Cl/Cd: 22.96 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh81-il-50000-n5.txt Download as CSV file: xf-mh81-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 81 13%
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 -0.3998 0.09719 0.09146 -0.0009 1.0000 0.0494
-8.500 -0.3985 0.09250 0.08688 -0.0040 1.0000 0.0479
-8.250 -0.4114 0.08467 0.07913 -0.0121 1.0000 0.0449
-8.000 -0.4087 0.08034 0.07490 -0.0154 1.0000 0.0444
-7.750 -0.4082 0.07603 0.07068 -0.0185 1.0000 0.0438
-7.500 -0.4079 0.07120 0.06588 -0.0220 1.0000 0.0431
-7.250 -0.4079 0.06613 0.06079 -0.0256 1.0000 0.0424
-7.000 -0.4001 0.06051 0.05496 -0.0304 0.9307 0.0416
-6.750 -0.3908 0.05522 0.04926 -0.0335 0.8886 0.0409
-6.500 -0.3838 0.05090 0.04446 -0.0340 0.8583 0.0405
-6.250 -0.3751 0.04728 0.04034 -0.0332 0.8335 0.0404
-6.000 -0.3633 0.04428 0.03685 -0.0320 0.8120 0.0406
-5.750 -0.3484 0.04172 0.03385 -0.0307 0.7914 0.0414
-5.500 -0.3316 0.03930 0.03093 -0.0294 0.7727 0.0429
-5.250 -0.3127 0.03685 0.02784 -0.0279 0.7555 0.0446
-5.000 -0.2918 0.03503 0.02571 -0.0267 0.7386 0.0463
-4.750 -0.2694 0.03339 0.02377 -0.0255 0.7224 0.0481
-4.500 -0.2455 0.03173 0.02171 -0.0242 0.7073 0.0500
-4.250 -0.2212 0.03031 0.02000 -0.0229 0.6926 0.0535
-4.000 -0.1959 0.02918 0.01867 -0.0220 0.6773 0.0586
-3.750 -0.1704 0.02804 0.01740 -0.0211 0.6627 0.0641
-3.500 -0.1446 0.02707 0.01629 -0.0201 0.6489 0.0729
-3.250 -0.1189 0.02615 0.01528 -0.0192 0.6361 0.0866
-3.000 -0.0931 0.02519 0.01431 -0.0184 0.6234 0.1117
-2.750 -0.0680 0.02407 0.01346 -0.0178 0.6104 0.1697
-2.500 -0.0466 0.02296 0.01288 -0.0169 0.5990 0.2745
-2.250 -0.0297 0.02173 0.01253 -0.0147 0.5883 0.4475
-2.000 0.0010 0.02070 0.01278 -0.0121 0.5757 0.7580
-1.750 0.0548 0.02094 0.01268 -0.0142 0.5620 0.9078
-1.500 0.1229 0.02103 0.01218 -0.0205 0.5474 0.9714
-1.250 0.1794 0.02093 0.01157 -0.0258 0.5347 1.0000
-1.000 0.2017 0.02108 0.01149 -0.0253 0.5237 1.0000
-0.750 0.2232 0.02120 0.01129 -0.0242 0.5154 1.0000
-0.500 0.2460 0.02143 0.01132 -0.0236 0.5051 1.0000
-0.250 0.2684 0.02162 0.01123 -0.0227 0.4972 1.0000
0.000 0.2914 0.02190 0.01135 -0.0221 0.4876 1.0000
0.250 0.3139 0.02213 0.01131 -0.0211 0.4802 1.0000
0.500 0.3371 0.02249 0.01155 -0.0205 0.4712 1.0000
0.750 0.3597 0.02272 0.01153 -0.0194 0.4649 1.0000
1.000 0.3830 0.02319 0.01192 -0.0190 0.4558 1.0000
1.250 0.4058 0.02347 0.01200 -0.0181 0.4494 1.0000
1.500 0.4289 0.02397 0.01241 -0.0176 0.4418 1.0000
1.750 0.4519 0.02438 0.01270 -0.0168 0.4350 1.0000
2.000 0.4750 0.02473 0.01286 -0.0159 0.4295 1.0000
2.250 0.4976 0.02537 0.01352 -0.0155 0.4216 1.0000
2.500 0.5207 0.02575 0.01375 -0.0146 0.4161 1.0000
2.750 0.5434 0.02636 0.01430 -0.0141 0.4102 1.0000
3.000 0.5657 0.02703 0.01496 -0.0136 0.4036 1.0000
3.250 0.5890 0.02742 0.01522 -0.0127 0.3988 1.0000
3.500 0.6110 0.02820 0.01601 -0.0123 0.3928 1.0000
3.750 0.6328 0.02898 0.01679 -0.0118 0.3868 1.0000
4.000 0.6562 0.02944 0.01716 -0.0110 0.3825 1.0000
4.250 0.6778 0.03029 0.01803 -0.0106 0.3773 1.0000
4.500 0.6979 0.03135 0.01917 -0.0103 0.3712 1.0000
4.750 0.7208 0.03191 0.01967 -0.0096 0.3668 1.0000
5.000 0.7445 0.03242 0.02009 -0.0089 0.3632 1.0000
5.250 0.7595 0.03420 0.02209 -0.0089 0.3566 1.0000
5.500 0.7803 0.03508 0.02300 -0.0084 0.3520 1.0000
5.750 0.8046 0.03549 0.02333 -0.0076 0.3486 1.0000
6.000 0.8171 0.03745 0.02548 -0.0075 0.3429 1.0000
6.250 0.8311 0.03914 0.02729 -0.0072 0.3377 1.0000
6.500 0.8525 0.03990 0.02807 -0.0066 0.3341 1.0000
6.750 0.8788 0.04014 0.02822 -0.0059 0.3314 1.0000
7.000 0.8653 0.04479 0.03324 -0.0063 0.3234 1.0000
7.250 0.8788 0.04632 0.03482 -0.0059 0.3193 1.0000
7.500 0.9028 0.04677 0.03528 -0.0051 0.3166 1.0000
8.000 0.8403 0.05916 0.04793 -0.0075 0.3022 1.0000
8.250 0.8699 0.05875 0.04755 -0.0061 0.3003 1.0000
8.750 0.8007 0.07468 0.06355 -0.0126 0.2849 1.0000
9.250 0.7652 0.08657 0.07550 -0.0173 0.2725 1.0000
9.500 0.7817 0.08799 0.07697 -0.0169 0.2699 1.0000
9.750 0.7673 0.09360 0.08261 -0.0191 0.2646 1.0000
10.000 0.7610 0.09807 0.08712 -0.0208 0.2593 1.0000
10.250 0.7715 0.10038 0.08947 -0.0210 0.2562 1.0000
10.500 0.7895 0.10174 0.09087 -0.0205 0.2539 1.0000
10.750 0.7679 0.10850 0.09768 -0.0237 0.2482 1.0000
11.000 0.7693 0.11201 0.10123 -0.0248 0.2437 1.0000
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Polar data table (+)
Polar graphs
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