MH 92 15.49% (mh92-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 92 15.49% (mh92-il) Reynolds number: 500,000 Max Cl/Cd: 76.64 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh92-il-500000.txt Download as CSV file: xf-mh92-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 92 15.49%
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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.7675 0.08448 0.08178 -0.0168 1.0000 0.0255
-12.750 -0.7914 0.07858 0.07575 -0.0203 1.0000 0.0254
-12.500 -0.9798 0.04553 0.04103 -0.0225 1.0000 0.0127
-12.250 -0.9844 0.04378 0.03910 -0.0207 1.0000 0.0126
-11.750 -0.9847 0.03879 0.03381 -0.0171 1.0000 0.0125
-11.500 -0.9811 0.03631 0.03119 -0.0153 1.0000 0.0123
-11.250 -0.9792 0.03415 0.02883 -0.0129 1.0000 0.0123
-11.000 -0.9720 0.03228 0.02679 -0.0108 1.0000 0.0123
-10.750 -0.9619 0.03050 0.02486 -0.0090 1.0000 0.0123
-10.500 -0.9518 0.02898 0.02314 -0.0069 1.0000 0.0124
-10.250 -0.9370 0.02754 0.02158 -0.0054 1.0000 0.0124
-10.000 -0.9228 0.02644 0.02033 -0.0036 1.0000 0.0125
-9.750 -0.9024 0.02463 0.01843 -0.0029 1.0000 0.0127
-9.500 -0.8829 0.02321 0.01700 -0.0021 1.0000 0.0130
-9.250 -0.8639 0.02219 0.01594 -0.0011 1.0000 0.0130
-9.000 -0.8434 0.02129 0.01505 -0.0004 0.9802 0.0134
-8.750 -0.8158 0.02050 0.01416 -0.0007 0.9284 0.0138
-8.500 -0.8026 0.01993 0.01345 0.0020 0.8972 0.0141
-8.250 -0.7873 0.01929 0.01270 0.0043 0.8752 0.0142
-8.000 -0.7702 0.01869 0.01199 0.0062 0.8566 0.0147
-7.750 -0.7518 0.01812 0.01131 0.0079 0.8399 0.0150
-7.500 -0.7333 0.01752 0.01059 0.0096 0.8247 0.0154
-7.250 -0.7164 0.01674 0.00975 0.0115 0.8100 0.0158
-7.000 -0.6965 0.01617 0.00913 0.0128 0.7960 0.0165
-6.750 -0.6751 0.01569 0.00860 0.0140 0.7828 0.0172
-6.500 -0.6528 0.01529 0.00809 0.0151 0.7703 0.0181
-6.250 -0.6320 0.01470 0.00746 0.0164 0.7574 0.0195
-6.000 -0.6084 0.01433 0.00703 0.0172 0.7450 0.0214
-5.750 -0.5861 0.01383 0.00648 0.0183 0.7331 0.0235
-5.500 -0.5629 0.01338 0.00599 0.0193 0.7210 0.0275
-5.250 -0.5398 0.01288 0.00550 0.0202 0.7091 0.0362
-5.000 -0.5182 0.01226 0.00500 0.0213 0.6979 0.0628
-4.750 -0.4977 0.01150 0.00453 0.0225 0.6861 0.1207
-4.500 -0.4775 0.01075 0.00413 0.0236 0.6750 0.1971
-4.250 -0.4569 0.01008 0.00379 0.0247 0.6639 0.2792
-4.000 -0.4341 0.00960 0.00355 0.0256 0.6524 0.3437
-3.750 -0.4109 0.00920 0.00333 0.0264 0.6417 0.3988
-3.500 -0.3873 0.00884 0.00315 0.0273 0.6303 0.4526
-3.250 -0.3634 0.00853 0.00300 0.0281 0.6194 0.5050
-2.750 -0.3141 0.00805 0.00277 0.0296 0.5972 0.5947
-2.500 -0.2892 0.00786 0.00269 0.0304 0.5865 0.6379
-2.250 -0.2636 0.00774 0.00265 0.0311 0.5754 0.6757
-2.000 -0.2367 0.00767 0.00263 0.0315 0.5644 0.7021
-1.750 -0.2096 0.00767 0.00261 0.0319 0.5532 0.7239
-1.500 -0.1819 0.00766 0.00260 0.0323 0.5419 0.7430
-1.250 -0.1542 0.00769 0.00260 0.0326 0.5313 0.7598
-1.000 -0.1265 0.00774 0.00261 0.0328 0.5199 0.7748
-0.750 -0.0985 0.00778 0.00263 0.0331 0.5086 0.7882
-0.500 -0.0707 0.00786 0.00264 0.0333 0.4981 0.8003
-0.250 -0.0425 0.00792 0.00268 0.0335 0.4867 0.8098
0.000 -0.0146 0.00799 0.00269 0.0337 0.4758 0.8200
0.250 0.0134 0.00810 0.00275 0.0339 0.4652 0.8279
0.500 0.0413 0.00817 0.00278 0.0340 0.4544 0.8370
0.750 0.0694 0.00826 0.00284 0.0342 0.4439 0.8437
1.000 0.0971 0.00837 0.00290 0.0344 0.4333 0.8516
1.250 0.1249 0.00846 0.00295 0.0346 0.4234 0.8584
1.750 0.1800 0.00869 0.00310 0.0351 0.4035 0.8721
2.000 0.2072 0.00883 0.00319 0.0354 0.3943 0.8779
2.250 0.2344 0.00895 0.00330 0.0357 0.3848 0.8846
2.500 0.2609 0.00909 0.00339 0.0361 0.3761 0.8919
2.750 0.2880 0.00921 0.00350 0.0365 0.3675 0.8970
3.000 0.3147 0.00936 0.00361 0.0368 0.3596 0.9027
3.250 0.3412 0.00946 0.00369 0.0372 0.3513 0.9088
3.500 0.3678 0.00962 0.00381 0.0375 0.3435 0.9130
3.750 0.3949 0.00973 0.00392 0.0378 0.3361 0.9178
4.000 0.4203 0.00990 0.00403 0.0383 0.3290 0.9237
4.250 0.4471 0.00999 0.00414 0.0386 0.3224 0.9282
4.500 0.4741 0.01014 0.00427 0.0388 0.3153 0.9325
4.750 0.4998 0.01030 0.00440 0.0392 0.3088 0.9378
5.000 0.5256 0.01041 0.00452 0.0397 0.3024 0.9431
5.250 0.5540 0.01062 0.00468 0.0395 0.2959 0.9469
5.500 0.5822 0.01075 0.00484 0.0395 0.2900 0.9517
5.750 0.6078 0.01090 0.00498 0.0398 0.2838 0.9575
6.000 0.6408 0.01115 0.00519 0.0386 0.2773 0.9602
6.250 0.6741 0.01131 0.00538 0.0374 0.2715 0.9632
6.500 0.7048 0.01153 0.00557 0.0366 0.2653 0.9669
6.750 0.7341 0.01174 0.00578 0.0361 0.2596 0.9710
7.000 0.7705 0.01193 0.00599 0.0341 0.2535 0.9723
7.250 0.8062 0.01225 0.00626 0.0320 0.2469 0.9738
7.500 0.8422 0.01242 0.00648 0.0302 0.2414 0.9755
7.750 0.8757 0.01265 0.00670 0.0286 0.2351 0.9779
8.000 0.9055 0.01294 0.00698 0.0278 0.2294 0.9816
8.250 0.9399 0.01312 0.00720 0.0261 0.2237 0.9836
8.500 0.9746 0.01344 0.00749 0.0242 0.2179 0.9852
8.750 1.0086 0.01371 0.00779 0.0225 0.2127 0.9872
9.000 1.0420 0.01395 0.00806 0.0209 0.2073 0.9897
9.250 1.0729 0.01434 0.00842 0.0196 0.2019 0.9928
9.500 1.1069 0.01459 0.00874 0.0179 0.1969 0.9948
9.750 1.1404 0.01488 0.00906 0.0161 0.1917 0.9970
10.000 1.1720 0.01538 0.00952 0.0145 0.1861 0.9995
10.250 1.1916 0.01557 0.00980 0.0155 0.1824 1.0000
10.500 1.2016 0.01583 0.01010 0.0183 0.1787 1.0000
10.750 1.2077 0.01617 0.01043 0.0216 0.1751 1.0000
11.000 1.2109 0.01657 0.01083 0.0254 0.1716 1.0000
11.250 1.2220 0.01681 0.01114 0.0279 0.1682 1.0000
11.500 1.2327 0.01717 0.01154 0.0303 0.1643 1.0000
11.750 1.2402 0.01769 0.01204 0.0331 0.1603 1.0000
12.000 1.2477 0.01822 0.01261 0.0357 0.1568 1.0000
12.250 1.2597 0.01873 0.01319 0.0374 0.1529 1.0000
12.500 1.2688 0.01946 0.01393 0.0390 0.1486 1.0000
12.750 1.2753 0.02046 0.01493 0.0407 0.1445 1.0000
13.000 1.2890 0.02117 0.01573 0.0415 0.1406 1.0000
13.250 1.2978 0.02222 0.01681 0.0425 0.1361 1.0000
13.500 1.3021 0.02364 0.01823 0.0435 0.1319 1.0000
13.750 1.3142 0.02464 0.01932 0.0441 0.1278 1.0000
14.000 1.3201 0.02614 0.02084 0.0446 0.1235 1.0000
14.250 1.3220 0.02802 0.02274 0.0451 0.1196 1.0000
14.500 1.3307 0.02946 0.02426 0.0453 0.1154 1.0000
14.750 1.3324 0.03154 0.02637 0.0454 0.1115 1.0000
15.000 1.3309 0.03397 0.02883 0.0454 0.1079 1.0000
15.250 1.3359 0.03590 0.03085 0.0453 0.1046 1.0000
15.500 1.3348 0.03846 0.03346 0.0450 0.1014 1.0000
15.750 1.3285 0.04160 0.03662 0.0445 0.0985 1.0000
16.000 1.3275 0.04428 0.03938 0.0440 0.0959 1.0000
16.250 1.3264 0.04705 0.04224 0.0433 0.0933 1.0000
16.500 1.3215 0.05035 0.04560 0.0424 0.0909 1.0000
16.750 1.3121 0.05426 0.04954 0.0412 0.0886 1.0000
17.000 1.3066 0.05781 0.05316 0.0400 0.0864 1.0000
17.250 1.3044 0.06110 0.05655 0.0388 0.0843 1.0000
17.500 1.2983 0.06492 0.06044 0.0373 0.0820 1.0000
17.750 1.2897 0.06911 0.06468 0.0357 0.0801 1.0000
18.000 1.2793 0.07354 0.06912 0.0339 0.0779 1.0000
18.250 1.2750 0.07740 0.07309 0.0322 0.0761 1.0000
18.500 1.2697 0.08142 0.07721 0.0304 0.0743 1.0000
18.750 1.2623 0.08581 0.08166 0.0284 0.0724 1.0000
19.000 1.2537 0.09038 0.08626 0.0263 0.0706 1.0000
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Polar data table (+)
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