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MH 22 7.2% (mh22-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 22 7.2% (mh22-il)
Reynolds number: 200,000
Max Cl/Cd: 60.27 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh22-il-200000-n5.txt
Download as CSV file: xf-mh22-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 22  7.2%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.5152   0.08618   0.08286   0.0003   1.0000   0.0060
  -7.750  -0.5159   0.08212   0.07884  -0.0020   1.0000   0.0059
  -7.500  -0.5187   0.07810   0.07489  -0.0045   1.0000   0.0058
  -7.250  -0.5190   0.07347   0.07029  -0.0083   1.0000   0.0057
  -7.000  -0.5153   0.06825   0.06506  -0.0128   1.0000   0.0056
  -6.750  -0.5089   0.06273   0.05950  -0.0171   1.0000   0.0054
  -6.500  -0.4999   0.05698   0.05366  -0.0208   1.0000   0.0053
  -6.250  -0.4888   0.05106   0.04759  -0.0237   1.0000   0.0052
  -6.000  -0.4755   0.04534   0.04165  -0.0256   1.0000   0.0051
  -5.750  -0.4608   0.03961   0.03562  -0.0265   1.0000   0.0049
  -5.500  -0.4447   0.03428   0.02991  -0.0266   1.0000   0.0048
  -5.250  -0.4270   0.02961   0.02476  -0.0260   1.0000   0.0048
  -5.000  -0.4075   0.02581   0.02045  -0.0250   1.0000   0.0048
  -4.750  -0.3863   0.02271   0.01683  -0.0238   1.0000   0.0049
  -4.500  -0.3640   0.02027   0.01396  -0.0226   1.0000   0.0052
  -4.250  -0.3380   0.01851   0.01185  -0.0221   0.9949   0.0058
  -4.000  -0.3045   0.01642   0.00932  -0.0236   0.9698   0.0092
  -3.750  -0.2695   0.01493   0.00762  -0.0248   0.9446   0.0103
  -3.500  -0.2361   0.01372   0.00620  -0.0256   0.9191   0.0111
  -3.250  -0.2060   0.01287   0.00511  -0.0256   0.8936   0.0124
  -3.000  -0.1782   0.01225   0.00423  -0.0251   0.8698   0.0155
  -2.750  -0.1536   0.01137   0.00359  -0.0243   0.8484   0.0766
  -2.500  -0.1296   0.01076   0.00333  -0.0237   0.8288   0.1669
  -2.250  -0.1047   0.01043   0.00306  -0.0230   0.8116   0.2245
  -2.000  -0.0803   0.01004   0.00283  -0.0224   0.7963   0.3039
  -1.750  -0.0564   0.00960   0.00258  -0.0216   0.7823   0.4043
  -1.500  -0.0345   0.00902   0.00244  -0.0204   0.7694   0.5474
  -1.250  -0.0149   0.00834   0.00237  -0.0181   0.7575   0.7318
  -1.000   0.0444   0.00798   0.00232  -0.0237   0.7462   0.9359
  -0.750   0.0910   0.00802   0.00218  -0.0275   0.7349   0.9842
  -0.500   0.1299   0.00806   0.00200  -0.0299   0.7239   1.0000
  -0.250   0.1548   0.00812   0.00192  -0.0293   0.7133   1.0000
   0.000   0.1799   0.00818   0.00187  -0.0287   0.7030   1.0000
   0.250   0.2052   0.00825   0.00183  -0.0281   0.6923   1.0000
   0.500   0.2306   0.00832   0.00182  -0.0276   0.6817   1.0000
   0.750   0.2560   0.00839   0.00183  -0.0270   0.6713   1.0000
   1.000   0.2815   0.00847   0.00184  -0.0265   0.6608   1.0000
   1.250   0.3070   0.00856   0.00186  -0.0259   0.6502   1.0000
   1.500   0.3326   0.00865   0.00191  -0.0254   0.6386   1.0000
   1.750   0.3583   0.00873   0.00196  -0.0249   0.6265   1.0000
   2.000   0.3839   0.00882   0.00203  -0.0244   0.6138   1.0000
   2.250   0.4096   0.00892   0.00215  -0.0239   0.6002   1.0000
   2.500   0.4353   0.00902   0.00223  -0.0234   0.5853   1.0000
   2.750   0.4610   0.00912   0.00233  -0.0229   0.5685   1.0000
   3.000   0.4867   0.00923   0.00244  -0.0224   0.5490   1.0000
   3.250   0.5122   0.00936   0.00255  -0.0219   0.5269   1.0000
   3.500   0.5375   0.00953   0.00276  -0.0213   0.5013   1.0000
   3.750   0.5626   0.00973   0.00292  -0.0207   0.4733   1.0000
   4.000   0.5876   0.00999   0.00312  -0.0202   0.4446   1.0000
   4.250   0.6124   0.01028   0.00337  -0.0196   0.4152   1.0000
   4.500   0.6372   0.01060   0.00365  -0.0190   0.3847   1.0000
   4.750   0.6618   0.01098   0.00398  -0.0185   0.3495   1.0000
   5.000   0.6849   0.01156   0.00435  -0.0179   0.2880   1.0000
   5.250   0.7022   0.01314   0.00501  -0.0171   0.1278   1.0000
   5.500   0.7180   0.01526   0.00625  -0.0160   0.0070   1.0000
   5.750   0.7414   0.01607   0.00736  -0.0151   0.0046   1.0000
   6.000   0.7642   0.01695   0.00847  -0.0142   0.0039   1.0000
   6.250   0.7860   0.01797   0.00972  -0.0132   0.0036   1.0000
   6.500   0.8065   0.01921   0.01115  -0.0121   0.0034   1.0000
   6.750   0.8259   0.02060   0.01273  -0.0109   0.0033   1.0000
   7.000   0.8448   0.02220   0.01450  -0.0096   0.0032   1.0000
   7.250   0.8635   0.02401   0.01650  -0.0082   0.0031   1.0000
   7.500   0.8820   0.02609   0.01883  -0.0069   0.0031   1.0000
   7.750   0.9000   0.02845   0.02148  -0.0055   0.0032   1.0000
   8.000   0.9162   0.03118   0.02456  -0.0040   0.0032   1.0000
   8.250   0.9296   0.03424   0.02802  -0.0024   0.0033   1.0000
   8.500   0.9392   0.03761   0.03182  -0.0008   0.0033   1.0000
   8.750   0.9442   0.04126   0.03589   0.0009   0.0034   1.0000
   9.000   0.9442   0.04503   0.04003   0.0026   0.0035   1.0000
   9.250   0.9394   0.04871   0.04404   0.0042   0.0035   1.0000
   9.500   0.9271   0.05218   0.04775   0.0061   0.0036   1.0000
   9.750   0.9120   0.05578   0.05155   0.0067   0.0036   1.0000
  10.000   0.8973   0.05998   0.05592   0.0053   0.0037   1.0000
  10.250   0.8822   0.06503   0.06113   0.0025   0.0037   1.0000
  10.500   0.8656   0.07128   0.06752  -0.0019   0.0037   1.0000
  10.750   0.8497   0.07862   0.07499  -0.0074   0.0037   1.0000
  11.000   0.8354   0.08703   0.08349  -0.0136   0.0037   1.0000
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