MH 82 13.31% (mh82-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 82 13.31% (mh82-il) Reynolds number: 50,000 Max Cl/Cd: 23.42 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh82-il-50000-n5.txt Download as CSV file: xf-mh82-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 82 13.31%
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3330 0.09712 0.09163 -0.0089 1.0000 0.0546
-8.250 -0.3283 0.09281 0.08745 -0.0120 1.0000 0.0524
-8.000 -0.3350 0.08642 0.08117 -0.0192 1.0000 0.0487
-7.750 -0.3256 0.08242 0.07726 -0.0231 0.9443 0.0479
-7.500 -0.3166 0.07752 0.07229 -0.0287 0.8913 0.0469
-7.250 -0.3139 0.07308 0.06774 -0.0322 0.8590 0.0459
-7.000 -0.3147 0.06839 0.06289 -0.0350 0.8353 0.0449
-6.750 -0.3162 0.06328 0.05754 -0.0376 0.8161 0.0438
-6.250 -0.3126 0.05291 0.04626 -0.0408 0.7838 0.0418
-6.000 -0.3018 0.04940 0.04236 -0.0407 0.7679 0.0417
-5.750 -0.2883 0.04608 0.03859 -0.0404 0.7528 0.0416
-5.500 -0.2728 0.04283 0.03481 -0.0399 0.7384 0.0420
-5.250 -0.2538 0.04112 0.03294 -0.0391 0.7235 0.0435
-5.000 -0.2341 0.03905 0.03050 -0.0383 0.7100 0.0453
-4.750 -0.2130 0.03678 0.02770 -0.0373 0.6973 0.0470
-4.500 -0.1893 0.03457 0.02493 -0.0365 0.6836 0.0485
-4.250 -0.1649 0.03277 0.02279 -0.0357 0.6706 0.0500
-4.000 -0.1405 0.03144 0.02126 -0.0347 0.6584 0.0526
-3.750 -0.1146 0.03015 0.01957 -0.0337 0.6462 0.0571
-3.500 -0.0890 0.02907 0.01846 -0.0331 0.6334 0.0619
-3.250 -0.0627 0.02800 0.01716 -0.0321 0.6220 0.0684
-3.000 -0.0365 0.02712 0.01612 -0.0312 0.6109 0.0788
-2.750 -0.0098 0.02627 0.01529 -0.0307 0.5988 0.0955
-2.500 0.0163 0.02535 0.01439 -0.0301 0.5887 0.1300
-2.250 0.0406 0.02436 0.01371 -0.0294 0.5780 0.2010
-2.000 0.0625 0.02334 0.01331 -0.0286 0.5677 0.3172
-1.750 0.0790 0.02212 0.01308 -0.0261 0.5589 0.5200
-1.500 0.1213 0.02137 0.01320 -0.0251 0.5471 0.8578
-1.250 0.1951 0.02138 0.01263 -0.0321 0.5339 0.9801
-1.000 0.2348 0.02142 0.01222 -0.0344 0.5240 1.0000
-0.750 0.2576 0.02168 0.01221 -0.0338 0.5144 1.0000
-0.500 0.2800 0.02186 0.01205 -0.0328 0.5068 1.0000
-0.250 0.3031 0.02219 0.01216 -0.0322 0.4976 1.0000
0.000 0.3260 0.02242 0.01210 -0.0313 0.4903 1.0000
0.250 0.3492 0.02281 0.01229 -0.0307 0.4819 1.0000
0.500 0.3724 0.02311 0.01236 -0.0298 0.4747 1.0000
0.750 0.3957 0.02349 0.01254 -0.0291 0.4675 1.0000
1.000 0.4191 0.02390 0.01280 -0.0285 0.4598 1.0000
1.250 0.4428 0.02416 0.01279 -0.0275 0.4546 1.0000
1.500 0.4661 0.02481 0.01340 -0.0273 0.4463 1.0000
1.750 0.4899 0.02516 0.01356 -0.0265 0.4404 1.0000
2.000 0.5135 0.02569 0.01398 -0.0260 0.4341 1.0000
2.250 0.5368 0.02629 0.01451 -0.0256 0.4273 1.0000
2.500 0.5612 0.02665 0.01468 -0.0248 0.4226 1.0000
2.750 0.5840 0.02742 0.01544 -0.0246 0.4161 1.0000
3.000 0.6072 0.02806 0.01602 -0.0241 0.4101 1.0000
3.250 0.6320 0.02841 0.01621 -0.0234 0.4058 1.0000
3.500 0.6535 0.02940 0.01724 -0.0232 0.3995 1.0000
3.750 0.6760 0.03019 0.01802 -0.0229 0.3940 1.0000
4.000 0.7006 0.03062 0.01833 -0.0223 0.3900 1.0000
4.250 0.7216 0.03163 0.01937 -0.0220 0.3846 1.0000
4.500 0.7416 0.03276 0.02056 -0.0218 0.3788 1.0000
4.750 0.7653 0.03334 0.02109 -0.0213 0.3748 1.0000
5.000 0.7906 0.03376 0.02138 -0.0206 0.3717 1.0000
5.250 0.8023 0.03593 0.02380 -0.0208 0.3648 1.0000
5.500 0.8227 0.03689 0.02477 -0.0203 0.3603 1.0000
5.750 0.8475 0.03733 0.02513 -0.0197 0.3571 1.0000
6.000 0.8580 0.03950 0.02748 -0.0197 0.3517 1.0000
6.250 0.8673 0.04171 0.02982 -0.0195 0.3463 1.0000
6.500 0.8882 0.04254 0.03065 -0.0190 0.3428 1.0000
6.750 0.9154 0.04273 0.03075 -0.0183 0.3402 1.0000
7.000 0.8819 0.04933 0.03771 -0.0191 0.3312 1.0000
7.250 0.8941 0.05102 0.03946 -0.0188 0.3275 1.0000
7.500 0.9198 0.05129 0.03970 -0.0180 0.3251 1.0000
8.000 0.8460 0.06582 0.05443 -0.0220 0.3095 1.0000
8.500 0.8006 0.07913 0.06779 -0.0270 0.2956 1.0000
8.750 0.8230 0.07967 0.06836 -0.0261 0.2935 1.0000
9.250 0.7878 0.09177 0.08054 -0.0307 0.2816 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 82 13.31% (mh82-il)