MH 20 9.01% (mh20-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 20 9.01% (mh20-il) Reynolds number: 50,000 Max Cl/Cd: 34.88 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh20-il-50000-n5.txt Download as CSV file: xf-mh20-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 20 9.01%
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 -0.5006 0.09558 0.08935 -0.0091 1.0000 0.0354
-8.500 -0.4997 0.09118 0.08502 -0.0117 1.0000 0.0351
-8.250 -0.4992 0.08677 0.08069 -0.0146 1.0000 0.0346
-8.000 -0.5008 0.08213 0.07614 -0.0181 1.0000 0.0343
-7.750 -0.5020 0.07762 0.07167 -0.0210 1.0000 0.0338
-7.500 -0.5012 0.07293 0.06698 -0.0238 1.0000 0.0331
-7.250 -0.5000 0.06805 0.06207 -0.0264 1.0000 0.0326
-7.000 -0.4974 0.06326 0.05719 -0.0285 1.0000 0.0321
-6.750 -0.4931 0.05859 0.05236 -0.0300 1.0000 0.0316
-6.500 -0.4872 0.05402 0.04757 -0.0309 1.0000 0.0312
-6.250 -0.4793 0.04970 0.04296 -0.0311 1.0000 0.0309
-6.000 -0.4703 0.04564 0.03855 -0.0306 1.0000 0.0308
-5.750 -0.4607 0.04216 0.03469 -0.0295 1.0000 0.0306
-5.500 -0.4527 0.03914 0.03115 -0.0274 1.0000 0.0309
-5.250 -0.4462 0.03660 0.02823 -0.0247 1.0000 0.0313
-5.000 -0.4384 0.03431 0.02554 -0.0219 1.0000 0.0319
-4.750 -0.4171 0.03169 0.02239 -0.0212 0.9941 0.0332
-4.500 -0.3819 0.02911 0.01915 -0.0223 0.9837 0.0372
-4.250 -0.3483 0.02715 0.01698 -0.0240 0.9742 0.0469
-4.000 -0.3116 0.02506 0.01467 -0.0254 0.9667 0.0582
-3.750 -0.2753 0.02329 0.01286 -0.0270 0.9586 0.0932
-3.500 -0.2388 0.02177 0.01155 -0.0292 0.9509 0.1679
-3.250 -0.2060 0.02051 0.01069 -0.0308 0.9428 0.2654
-3.000 -0.1797 0.01933 0.01012 -0.0310 0.9334 0.4013
-2.750 -0.1471 0.01787 0.00981 -0.0305 0.9282 0.6887
-2.500 -0.0264 0.01758 0.00918 -0.0454 0.9372 0.9741
-2.250 0.0284 0.01747 0.00857 -0.0513 0.9313 1.0000
-2.000 0.0593 0.01752 0.00822 -0.0525 0.9197 1.0000
-1.750 0.0885 0.01761 0.00801 -0.0533 0.9083 1.0000
-1.500 0.1161 0.01773 0.00788 -0.0537 0.8974 1.0000
-1.250 0.1428 0.01788 0.00780 -0.0538 0.8869 1.0000
-1.000 0.1674 0.01806 0.00778 -0.0534 0.8760 1.0000
-0.750 0.1905 0.01826 0.00778 -0.0528 0.8650 1.0000
-0.500 0.2136 0.01848 0.00785 -0.0521 0.8544 1.0000
-0.250 0.2367 0.01870 0.00794 -0.0513 0.8443 1.0000
0.000 0.2602 0.01890 0.00803 -0.0504 0.8346 1.0000
0.250 0.2818 0.01916 0.00821 -0.0494 0.8236 1.0000
0.500 0.3037 0.01942 0.00839 -0.0484 0.8130 1.0000
0.750 0.3259 0.01968 0.00858 -0.0473 0.8027 1.0000
1.000 0.3486 0.01990 0.00875 -0.0462 0.7930 1.0000
1.250 0.3706 0.02015 0.00897 -0.0451 0.7823 1.0000
1.500 0.3926 0.02043 0.00924 -0.0440 0.7711 1.0000
1.750 0.4148 0.02070 0.00954 -0.0429 0.7601 1.0000
2.000 0.4372 0.02095 0.00980 -0.0417 0.7492 1.0000
2.250 0.4598 0.02117 0.01002 -0.0405 0.7386 1.0000
2.500 0.4824 0.02137 0.01026 -0.0392 0.7275 1.0000
2.750 0.5044 0.02164 0.01058 -0.0380 0.7152 1.0000
3.000 0.5264 0.02188 0.01098 -0.0367 0.7026 1.0000
3.250 0.5485 0.02212 0.01131 -0.0353 0.6898 1.0000
3.500 0.5707 0.02233 0.01162 -0.0340 0.6767 1.0000
3.750 0.5930 0.02253 0.01193 -0.0326 0.6631 1.0000
4.000 0.6154 0.02271 0.01223 -0.0312 0.6491 1.0000
4.250 0.6379 0.02285 0.01259 -0.0297 0.6346 1.0000
4.500 0.6606 0.02296 0.01284 -0.0282 0.6196 1.0000
4.750 0.6818 0.02322 0.01330 -0.0269 0.6012 1.0000
5.000 0.7041 0.02334 0.01359 -0.0254 0.5832 1.0000
5.250 0.7266 0.02338 0.01381 -0.0237 0.5647 1.0000
5.500 0.7481 0.02352 0.01416 -0.0222 0.5428 1.0000
5.750 0.7697 0.02361 0.01444 -0.0205 0.5194 1.0000
6.000 0.7914 0.02367 0.01481 -0.0187 0.4940 1.0000
6.250 0.8125 0.02379 0.01506 -0.0168 0.4653 1.0000
6.500 0.8329 0.02396 0.01530 -0.0148 0.4328 1.0000
6.750 0.8507 0.02439 0.01576 -0.0127 0.3928 1.0000
7.000 0.8648 0.02508 0.01639 -0.0105 0.3413 1.0000
7.250 0.8746 0.02615 0.01725 -0.0082 0.2776 1.0000
7.500 0.8795 0.02779 0.01849 -0.0059 0.2027 1.0000
7.750 0.8805 0.03009 0.02028 -0.0036 0.1340 1.0000
8.000 0.8806 0.03269 0.02245 -0.0013 0.0916 1.0000
8.250 0.8822 0.03515 0.02470 0.0010 0.0693 1.0000
8.500 0.8854 0.03748 0.02702 0.0033 0.0594 1.0000
8.750 0.8885 0.03977 0.02932 0.0055 0.0504 1.0000
9.000 0.8954 0.04183 0.03156 0.0074 0.0419 1.0000
9.250 0.9041 0.04430 0.03402 0.0091 0.0373 1.0000
9.500 0.9273 0.04692 0.03707 0.0108 0.0336 1.0000
9.750 0.9403 0.04956 0.04000 0.0122 0.0310 1.0000
10.000 0.9433 0.05221 0.04295 0.0134 0.0282 1.0000
10.250 0.9454 0.05570 0.04659 0.0145 0.0262 1.0000
10.500 0.9424 0.05896 0.05026 0.0154 0.0250 1.0000
10.750 0.9371 0.06267 0.05431 0.0158 0.0243 1.0000
11.000 0.9303 0.06658 0.05849 0.0157 0.0243 1.0000
11.250 0.9187 0.07113 0.06331 0.0149 0.0241 1.0000
11.500 0.9044 0.07624 0.06865 0.0132 0.0240 1.0000
11.750 0.8904 0.08157 0.07416 0.0109 0.0241 1.0000
12.000 0.8741 0.08773 0.08048 0.0077 0.0242 1.0000
12.250 0.8604 0.09390 0.08677 0.0042 0.0247 1.0000
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Polar data table (+)
Polar graphs
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