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MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 30 7.84% (mh30-il)
Reynolds number: 50,000
Max Cl/Cd: 35.72 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh30-il-50000-n5.txt
Download as CSV file: xf-mh30-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 30  7.84%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4930   0.11274   0.10564  -0.0126   1.0000   0.0477
  -9.500  -0.4885   0.10873   0.10168  -0.0136   1.0000   0.0460
  -9.250  -0.4854   0.10471   0.09771  -0.0151   1.0000   0.0434
  -8.750  -0.4924   0.09458   0.08776  -0.0236   1.0000   0.0368
  -8.500  -0.4891   0.09081   0.08404  -0.0242   1.0000   0.0362
  -8.250  -0.4902   0.08653   0.07984  -0.0265   1.0000   0.0361
  -8.000  -0.4905   0.08266   0.07605  -0.0280   1.0000   0.0355
  -7.750  -0.4922   0.07813   0.07159  -0.0310   1.0000   0.0351
  -7.500  -0.4920   0.07357   0.06705  -0.0337   1.0000   0.0346
  -7.250  -0.4913   0.06904   0.06251  -0.0359   1.0000   0.0339
  -7.000  -0.4899   0.06460   0.05800  -0.0377   1.0000   0.0333
  -6.750  -0.4878   0.06001   0.05330  -0.0392   1.0000   0.0329
  -6.500  -0.4838   0.05556   0.04867  -0.0401   1.0000   0.0324
  -6.250  -0.4775   0.05130   0.04415  -0.0405   1.0000   0.0319
  -6.000  -0.4689   0.04715   0.03967  -0.0403   1.0000   0.0317
  -5.750  -0.4576   0.04329   0.03542  -0.0398   1.0000   0.0316
  -5.500  -0.4437   0.03967   0.03120  -0.0390   1.0000   0.0317
  -5.250  -0.4275   0.03637   0.02740  -0.0379   1.0000   0.0320
  -5.000  -0.4090   0.03341   0.02394  -0.0367   1.0000   0.0328
  -4.750  -0.3887   0.03075   0.02077  -0.0352   1.0000   0.0345
  -4.500  -0.3683   0.02857   0.01821  -0.0340   1.0000   0.0391
  -4.250  -0.3478   0.02693   0.01638  -0.0327   1.0000   0.0457
  -4.000  -0.3256   0.02499   0.01411  -0.0310   1.0000   0.0510
  -3.750  -0.3048   0.02353   0.01259  -0.0297   1.0000   0.0650
  -3.500  -0.2826   0.02204   0.01103  -0.0285   1.0000   0.0856
  -3.250  -0.2603   0.02050   0.00970  -0.0276   1.0000   0.1336
  -3.000  -0.2396   0.01893   0.00883  -0.0270   1.0000   0.2616
  -2.750  -0.2220   0.01769   0.00843  -0.0254   1.0000   0.4387
  -2.500  -0.2080   0.01680   0.00815  -0.0220   1.0000   0.6124
  -2.250  -0.1912   0.01624   0.00803  -0.0180   1.0000   0.7841
  -2.000  -0.1229   0.01594   0.00741  -0.0249   1.0000   1.0000
  -1.750  -0.1059   0.01595   0.00706  -0.0235   1.0000   1.0000
  -1.500  -0.0877   0.01600   0.00679  -0.0224   1.0000   1.0000
  -1.250  -0.0688   0.01608   0.00659  -0.0213   1.0000   1.0000
  -1.000  -0.0495   0.01620   0.00641  -0.0203   1.0000   1.0000
  -0.750  -0.0300   0.01636   0.00634  -0.0194   1.0000   1.0000
  -0.500  -0.0103   0.01654   0.00633  -0.0186   1.0000   1.0000
  -0.250   0.0132   0.01678   0.00640  -0.0186   0.9981   1.0000
   0.000   0.0554   0.01716   0.00660  -0.0221   0.9868   1.0000
   0.250   0.0973   0.01753   0.00679  -0.0256   0.9753   1.0000
   0.500   0.1392   0.01787   0.00704  -0.0289   0.9632   1.0000
   0.750   0.1807   0.01818   0.00729  -0.0320   0.9505   1.0000
   1.000   0.2217   0.01844   0.00753  -0.0349   0.9372   1.0000
   1.250   0.2624   0.01865   0.00774  -0.0377   0.9231   1.0000
   1.500   0.3034   0.01882   0.00795  -0.0403   0.9084   1.0000
   1.750   0.3437   0.01894   0.00813  -0.0426   0.8929   1.0000
   2.000   0.3828   0.01898   0.00828  -0.0445   0.8764   1.0000
   2.250   0.4173   0.01900   0.00839  -0.0453   0.8575   1.0000
   2.500   0.4506   0.01897   0.00847  -0.0457   0.8373   1.0000
   2.750   0.4814   0.01894   0.00854  -0.0456   0.8152   1.0000
   3.000   0.5123   0.01886   0.00867  -0.0452   0.7921   1.0000
   3.250   0.5411   0.01879   0.00873  -0.0445   0.7663   1.0000
   3.500   0.5679   0.01876   0.00882  -0.0434   0.7368   1.0000
   3.750   0.5948   0.01875   0.00890  -0.0421   0.7044   1.0000
   4.000   0.6211   0.01877   0.00899  -0.0408   0.6686   1.0000
   4.250   0.6464   0.01889   0.00921  -0.0392   0.6289   1.0000
   4.500   0.6705   0.01914   0.00944  -0.0376   0.5854   1.0000
   4.750   0.6935   0.01951   0.00975  -0.0360   0.5393   1.0000
   5.000   0.7151   0.02002   0.01021  -0.0343   0.4900   1.0000
   5.250   0.7358   0.02064   0.01074  -0.0326   0.4404   1.0000
   5.500   0.7557   0.02139   0.01137  -0.0310   0.3906   1.0000
   5.750   0.7750   0.02224   0.01213  -0.0295   0.3409   1.0000
   6.000   0.7937   0.02321   0.01314  -0.0281   0.2927   1.0000
   6.250   0.8120   0.02430   0.01414  -0.0267   0.2461   1.0000
   6.500   0.8296   0.02555   0.01526  -0.0254   0.2025   1.0000
   6.750   0.8471   0.02695   0.01654  -0.0242   0.1622   1.0000
   7.000   0.8647   0.02855   0.01811  -0.0230   0.1271   1.0000
   7.250   0.8810   0.03023   0.01971  -0.0217   0.0987   1.0000
   7.500   0.8989   0.03228   0.02181  -0.0203   0.0814   1.0000
   7.750   0.9164   0.03426   0.02394  -0.0189   0.0664   1.0000
   8.000   0.9333   0.03642   0.02623  -0.0176   0.0559   1.0000
   8.250   0.9524   0.03908   0.02916  -0.0163   0.0496   1.0000
   8.500   0.9701   0.04241   0.03273  -0.0150   0.0453   1.0000
   8.750   0.9822   0.04518   0.03600  -0.0135   0.0393   1.0000
   9.000   0.9904   0.04801   0.03884  -0.0123   0.0350   1.0000
   9.250   0.9957   0.05207   0.04355  -0.0104   0.0336   1.0000
   9.500   0.9946   0.05632   0.04831  -0.0085   0.0327   1.0000
   9.750   0.9877   0.06057   0.05298  -0.0068   0.0321   1.0000
  10.000   0.9750   0.06454   0.05726  -0.0051   0.0319   1.0000
  10.250   0.9583   0.06872   0.06167  -0.0042   0.0319   1.0000
  10.500   0.9407   0.07329   0.06644  -0.0048   0.0321   1.0000
  10.750   0.9228   0.07852   0.07183  -0.0069   0.0324   1.0000
  11.000   0.9040   0.08476   0.07818  -0.0105   0.0328   1.0000
  11.250   0.8869   0.09182   0.08532  -0.0153   0.0332   1.0000
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