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MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 30 7.84% (mh30-il)
Reynolds number: 100,000
Max Cl/Cd: 51.15 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh30-il-100000.txt
Download as CSV file: xf-mh30-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4890   0.10597   0.10111  -0.0144   1.0000   0.0778
  -9.000  -0.4791   0.10249   0.09764  -0.0139   1.0000   0.0810
  -8.750  -0.4767   0.09918   0.09430  -0.0154   1.0000   0.0842
  -8.500  -0.4852   0.09615   0.09144  -0.0198   1.0000   0.0876
  -8.250  -0.5064   0.09321   0.08865  -0.0270   1.0000   0.0886
  -8.000  -0.4834   0.08823   0.08357  -0.0220   1.0000   0.0914
  -7.750  -0.4768   0.08502   0.08040  -0.0215   1.0000   0.0951
  -7.500  -0.4827   0.08171   0.07717  -0.0240   1.0000   0.0987
  -7.250  -0.5095   0.07739   0.07276  -0.0384   1.0000   0.1021
  -7.000  -0.4868   0.07307   0.06861  -0.0314   1.0000   0.1047
  -6.750  -0.4795   0.06993   0.06549  -0.0309   1.0000   0.1092
  -6.500  -0.4856   0.06513   0.06057  -0.0365   1.0000   0.1168
  -6.250  -0.4747   0.06220   0.05772  -0.0340   1.0000   0.1203
  -6.000  -0.4742   0.05829   0.05365  -0.0363   1.0000   0.1305
  -5.750  -0.4638   0.05534   0.05075  -0.0344   1.0000   0.1346
  -5.500  -0.4581   0.05195   0.04724  -0.0346   1.0000   0.1454
  -5.250  -0.4355   0.03765   0.03122  -0.0373   1.0000   0.0486
  -5.000  -0.4215   0.03381   0.02715  -0.0360   1.0000   0.0448
  -4.750  -0.4033   0.02956   0.02204  -0.0341   1.0000   0.0394
  -4.500  -0.3819   0.02771   0.01964  -0.0322   1.0000   0.0376
  -4.250  -0.3613   0.02518   0.01673  -0.0308   1.0000   0.0378
  -4.000  -0.3414   0.02296   0.01441  -0.0299   1.0000   0.0430
  -3.750  -0.3186   0.02144   0.01259  -0.0285   1.0000   0.0477
  -3.500  -0.2950   0.01948   0.01044  -0.0270   1.0000   0.0515
  -3.250  -0.2733   0.01792   0.00899  -0.0258   1.0000   0.0676
  -3.000  -0.2516   0.01642   0.00770  -0.0245   1.0000   0.1114
  -2.750  -0.2321   0.01391   0.00655  -0.0233   1.0000   0.3371
  -2.500  -0.2168   0.01274   0.00651  -0.0207   1.0000   0.5908
  -2.250  -0.2039   0.01211   0.00655  -0.0159   1.0000   0.8102
  -2.000  -0.1359   0.01191   0.00610  -0.0230   1.0000   1.0000
  -1.750  -0.1179   0.01196   0.00587  -0.0218   1.0000   1.0000
  -1.500  -0.0989   0.01206   0.00571  -0.0208   1.0000   1.0000
  -1.250  -0.0793   0.01219   0.00562  -0.0198   1.0000   1.0000
  -1.000  -0.0595   0.01235   0.00560  -0.0190   1.0000   1.0000
  -0.750  -0.0397   0.01255   0.00559  -0.0181   1.0000   1.0000
  -0.500  -0.0198   0.01278   0.00567  -0.0174   1.0000   1.0000
  -0.250  -0.0001   0.01305   0.00582  -0.0167   1.0000   1.0000
   0.000   0.0193   0.01336   0.00601  -0.0160   1.0000   1.0000
   0.250   0.0686   0.01389   0.00641  -0.0211   0.9894   1.0000
   0.500   0.1196   0.01440   0.00683  -0.0264   0.9780   1.0000
   0.750   0.1707   0.01480   0.00719  -0.0315   0.9660   1.0000
   1.000   0.2218   0.01508   0.00747  -0.0364   0.9532   1.0000
   1.250   0.2719   0.01523   0.00764  -0.0409   0.9396   1.0000
   1.500   0.3220   0.01526   0.00771  -0.0452   0.9254   1.0000
   1.750   0.3739   0.01515   0.00770  -0.0495   0.9115   1.0000
   2.000   0.4196   0.01496   0.00760  -0.0524   0.8959   1.0000
   2.250   0.4615   0.01470   0.00743  -0.0543   0.8793   1.0000
   2.500   0.5005   0.01436   0.00718  -0.0552   0.8621   1.0000
   2.750   0.5296   0.01412   0.00709  -0.0543   0.8400   1.0000
   3.000   0.5584   0.01382   0.00687  -0.0531   0.8173   1.0000
   3.250   0.5844   0.01357   0.00668  -0.0514   0.7912   1.0000
   3.500   0.6088   0.01340   0.00654  -0.0495   0.7605   1.0000
   3.750   0.6335   0.01326   0.00640  -0.0476   0.7270   1.0000
   4.000   0.6569   0.01327   0.00644  -0.0456   0.6869   1.0000
   4.250   0.6796   0.01343   0.00652  -0.0437   0.6408   1.0000
   4.500   0.7018   0.01372   0.00666  -0.0418   0.5912   1.0000
   4.750   0.7232   0.01416   0.00693  -0.0400   0.5372   1.0000
   5.000   0.7438   0.01471   0.00730  -0.0382   0.4798   1.0000
   5.250   0.7638   0.01537   0.00775  -0.0366   0.4218   1.0000
   5.500   0.7831   0.01615   0.00828  -0.0349   0.3642   1.0000
   5.750   0.8022   0.01704   0.00894  -0.0334   0.3075   1.0000
   6.000   0.8207   0.01806   0.00984  -0.0319   0.2523   1.0000
   6.250   0.8386   0.01924   0.01077  -0.0304   0.1995   1.0000
   6.500   0.8555   0.02061   0.01186  -0.0289   0.1498   1.0000
   6.750   0.8726   0.02234   0.01337  -0.0273   0.1110   1.0000
   7.000   0.8906   0.02416   0.01504  -0.0258   0.0848   1.0000
   7.250   0.9122   0.02665   0.01750  -0.0245   0.0706   1.0000
   7.500   0.9335   0.02911   0.02003  -0.0234   0.0586   1.0000
   7.750   0.9545   0.03124   0.02250  -0.0218   0.0495   1.0000
   8.000   0.9716   0.03393   0.02553  -0.0202   0.0404   1.0000
   8.250   0.9884   0.03730   0.02908  -0.0189   0.0364   1.0000
   8.500   0.9984   0.04313   0.03536  -0.0172   0.0352   1.0000
   8.750   1.0057   0.04634   0.03918  -0.0147   0.0346   1.0000
   9.000   1.0085   0.04998   0.04337  -0.0123   0.0339   1.0000
   9.250   1.0063   0.05389   0.04775  -0.0100   0.0333   1.0000
   9.500   0.9991   0.05791   0.05218  -0.0078   0.0330   1.0000
   9.750   0.9872   0.06197   0.05654  -0.0058   0.0330   1.0000
  10.000   0.9698   0.06550   0.06030  -0.0037   0.0329   1.0000
  10.250   0.9517   0.06971   0.06466  -0.0029   0.0334   1.0000
  10.500   0.9331   0.07429   0.06939  -0.0037   0.0338   1.0000
  10.750   0.9201   0.07984   0.07497  -0.0053   0.0347   1.0000
  11.000   0.9107   0.08538   0.08061  -0.0072   0.0355   1.0000
  11.250   0.7609   0.09790   0.09372  -0.0182   0.0443   1.0000
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