MH 80 12.72% (mh80-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 80 12.72% (mh80-il) Reynolds number: 500,000 Max Cl/Cd: 85.66 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh80-il-500000-n5.txt Download as CSV file: xf-mh80-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 80 12.72%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4559 0.09412 0.09132 0.0227 0.6475 0.0078
-9.500 -0.6863 0.05347 0.05075 -0.0072 0.7592 0.0062
-9.250 -0.7193 0.04721 0.04417 -0.0068 0.7414 0.0061
-9.000 -0.7416 0.04068 0.03716 -0.0059 0.7264 0.0061
-8.750 -0.7467 0.03590 0.03190 -0.0044 0.7108 0.0060
-8.500 -0.7420 0.03220 0.02774 -0.0029 0.6948 0.0060
-8.250 -0.7316 0.02910 0.02419 -0.0014 0.6790 0.0060
-8.000 -0.7166 0.02663 0.02130 -0.0001 0.6635 0.0060
-7.750 -0.6982 0.02467 0.01899 0.0010 0.6481 0.0060
-7.500 -0.6778 0.02302 0.01702 0.0020 0.6330 0.0060
-7.250 -0.6558 0.02164 0.01537 0.0028 0.6184 0.0060
-7.000 -0.6328 0.02042 0.01389 0.0037 0.6043 0.0060
-6.750 -0.6088 0.01940 0.01265 0.0044 0.5903 0.0061
-6.500 -0.5843 0.01848 0.01152 0.0051 0.5769 0.0061
-6.250 -0.5592 0.01770 0.01058 0.0056 0.5635 0.0062
-6.000 -0.5337 0.01698 0.00971 0.0062 0.5510 0.0062
-5.750 -0.5089 0.01612 0.00872 0.0069 0.5390 0.0063
-5.250 -0.4571 0.01493 0.00732 0.0078 0.5152 0.0067
-5.000 -0.4306 0.01447 0.00678 0.0083 0.5038 0.0069
-4.750 -0.4039 0.01406 0.00627 0.0087 0.4928 0.0071
-4.500 -0.3769 0.01366 0.00580 0.0090 0.4822 0.0074
-4.250 -0.3499 0.01331 0.00535 0.0094 0.4717 0.0078
-4.000 -0.3226 0.01299 0.00494 0.0098 0.4611 0.0082
-3.750 -0.2954 0.01264 0.00453 0.0101 0.4520 0.0088
-3.250 -0.2403 0.01215 0.00391 0.0107 0.4331 0.0102
-3.000 -0.2126 0.01193 0.00362 0.0109 0.4239 0.0114
-2.750 -0.1847 0.01173 0.00338 0.0112 0.4148 0.0136
-2.500 -0.1570 0.01152 0.00315 0.0114 0.4070 0.0188
-2.250 -0.1294 0.01129 0.00294 0.0116 0.3990 0.0300
-2.000 -0.1020 0.01103 0.00275 0.0119 0.3911 0.0528
-1.750 -0.0750 0.01070 0.00259 0.0121 0.3828 0.1005
-1.500 -0.0479 0.01042 0.00246 0.0123 0.3751 0.1522
-1.250 -0.0211 0.01008 0.00236 0.0125 0.3680 0.2178
-1.000 0.0057 0.00979 0.00226 0.0127 0.3611 0.2883
-0.750 0.0314 0.00934 0.00218 0.0130 0.3550 0.3986
-0.500 0.0556 0.00879 0.00210 0.0137 0.3482 0.5401
-0.250 0.0802 0.00841 0.00204 0.0144 0.3418 0.6462
0.000 0.1038 0.00805 0.00206 0.0156 0.3356 0.7552
0.250 0.1284 0.00794 0.00214 0.0168 0.3297 0.8310
0.500 0.1551 0.00797 0.00221 0.0176 0.3246 0.8688
0.750 0.1824 0.00804 0.00226 0.0181 0.3189 0.8919
1.000 0.2098 0.00814 0.00231 0.0185 0.3130 0.9083
1.250 0.2379 0.00823 0.00236 0.0188 0.3079 0.9214
1.500 0.2661 0.00833 0.00242 0.0191 0.3025 0.9353
1.750 0.2954 0.00846 0.00250 0.0192 0.2977 0.9497
2.000 0.3270 0.00858 0.00259 0.0188 0.2934 0.9612
2.250 0.3603 0.00871 0.00267 0.0180 0.2882 0.9700
2.500 0.3980 0.00886 0.00274 0.0161 0.2828 0.9746
2.750 0.4355 0.00898 0.00282 0.0142 0.2786 0.9779
3.000 0.4696 0.00909 0.00289 0.0130 0.2745 0.9813
3.250 0.5022 0.00921 0.00296 0.0121 0.2701 0.9841
3.500 0.5366 0.00935 0.00304 0.0107 0.2657 0.9856
3.750 0.5700 0.00944 0.00313 0.0096 0.2621 0.9873
4.000 0.6025 0.00955 0.00321 0.0086 0.2585 0.9891
4.250 0.6342 0.00968 0.00331 0.0078 0.2548 0.9911
4.500 0.6652 0.00984 0.00344 0.0071 0.2510 0.9931
4.750 0.6968 0.00996 0.00355 0.0063 0.2478 0.9947
5.000 0.7291 0.01007 0.00366 0.0053 0.2445 0.9963
5.250 0.7609 0.01022 0.00380 0.0044 0.2411 0.9980
5.500 0.7922 0.01039 0.00395 0.0035 0.2376 0.9995
5.750 0.8187 0.01057 0.00411 0.0037 0.2346 1.0000
6.000 0.8430 0.01070 0.00428 0.0043 0.2319 1.0000
6.250 0.8671 0.01086 0.00445 0.0050 0.2291 1.0000
6.500 0.8910 0.01104 0.00463 0.0057 0.2263 1.0000
6.750 0.9148 0.01125 0.00484 0.0063 0.2233 1.0000
7.000 0.9385 0.01147 0.00505 0.0070 0.2204 1.0000
7.250 0.9627 0.01164 0.00526 0.0076 0.2178 1.0000
7.500 0.9870 0.01183 0.00548 0.0082 0.2150 1.0000
7.750 1.0112 0.01204 0.00571 0.0087 0.2122 1.0000
8.000 1.0351 0.01228 0.00596 0.0093 0.2092 1.0000
8.250 1.0591 0.01256 0.00623 0.0098 0.2062 1.0000
8.500 1.0838 0.01275 0.00648 0.0102 0.2037 1.0000
8.750 1.1086 0.01298 0.00675 0.0106 0.2009 1.0000
9.000 1.1332 0.01324 0.00704 0.0110 0.1977 1.0000
9.250 1.1575 0.01355 0.00735 0.0113 0.1944 1.0000
9.500 1.1820 0.01384 0.00768 0.0117 0.1915 1.0000
9.750 1.2069 0.01409 0.00800 0.0119 0.1885 1.0000
10.000 1.2315 0.01439 0.00833 0.0122 0.1850 1.0000
10.250 1.2554 0.01474 0.00870 0.0125 0.1815 1.0000
10.500 1.2792 0.01510 0.00910 0.0128 0.1784 1.0000
10.750 1.3035 0.01541 0.00948 0.0130 0.1752 1.0000
11.000 1.3270 0.01577 0.00989 0.0133 0.1712 1.0000
11.250 1.3495 0.01622 0.01036 0.0136 0.1675 1.0000
11.500 1.3723 0.01662 0.01082 0.0140 0.1642 1.0000
11.750 1.3948 0.01702 0.01129 0.0143 0.1605 1.0000
12.000 1.4158 0.01752 0.01182 0.0147 0.1563 1.0000
12.250 1.4357 0.01808 0.01243 0.0153 0.1527 1.0000
12.500 1.4562 0.01856 0.01298 0.0158 0.1489 1.0000
12.750 1.4743 0.01917 0.01364 0.0164 0.1446 1.0000
13.000 1.4895 0.01993 0.01444 0.0173 0.1407 1.0000
13.250 1.5056 0.02057 0.01516 0.0181 0.1369 1.0000
13.500 1.5136 0.02144 0.01609 0.0198 0.1328 1.0000
13.750 1.5148 0.02282 0.01751 0.0213 0.1290 1.0000
14.000 1.5221 0.02410 0.01888 0.0219 0.1250 1.0000
14.250 1.5240 0.02602 0.02085 0.0222 0.1199 1.0000
14.500 1.5241 0.02833 0.02322 0.0220 0.1154 1.0000
14.750 1.5240 0.03080 0.02577 0.0216 0.1105 1.0000
15.000 1.5162 0.03422 0.02923 0.0207 0.1061 1.0000
15.250 1.5113 0.03745 0.03254 0.0198 0.1011 1.0000
15.500 1.5005 0.04139 0.03655 0.0186 0.0973 1.0000
15.750 1.4871 0.04574 0.04097 0.0172 0.0939 1.0000
16.000 1.4758 0.04992 0.04524 0.0158 0.0908 1.0000
16.250 1.4575 0.05503 0.05043 0.0140 0.0874 1.0000
16.500 1.4391 0.06033 0.05581 0.0119 0.0853 1.0000
16.750 1.4239 0.06543 0.06100 0.0098 0.0821 1.0000
17.000 1.4068 0.07099 0.06664 0.0074 0.0792 1.0000
17.250 1.3889 0.07683 0.07256 0.0048 0.0769 1.0000
17.500 1.3709 0.08279 0.07859 0.0021 0.0743 1.0000
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Polar data table (+)
Polar graphs
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