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MH 22 7.2% (mh22-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: MH 22 7.2% (mh22-il)
Reynolds number: 1,000,000
Max Cl/Cd: 81.94 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh22-il-1000000-n5.txt
Download as CSV file: xf-mh22-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4553   0.08400   0.08258   0.0042   1.0000   0.0022
  -8.250  -0.4563   0.07922   0.07781   0.0024   1.0000   0.0021
  -8.000  -0.4603   0.07406   0.07266   0.0004   1.0000   0.0020
  -7.750  -0.5223   0.07913   0.07764  -0.0022   1.0000   0.0021
  -7.500  -0.5189   0.07635   0.07489  -0.0038   1.0000   0.0024
  -7.250  -0.5256   0.07071   0.06926  -0.0087   1.0000   0.0022
  -7.000  -0.5238   0.06457   0.06310  -0.0141   1.0000   0.0020
  -6.750  -0.5179   0.05810   0.05656  -0.0190   1.0000   0.0019
  -6.500  -0.5087   0.05147   0.04982  -0.0228   1.0000   0.0018
  -6.250  -0.4875   0.04299   0.04094  -0.0282   0.8966   0.0016
  -6.000  -0.4774   0.03666   0.03420  -0.0281   0.8515   0.0016
  -5.750  -0.4656   0.02910   0.02611  -0.0271   0.8231   0.0014
  -5.500  -0.4525   0.02156   0.01781  -0.0251   0.8015   0.0012
  -5.250  -0.4341   0.01672   0.01223  -0.0231   0.7829   0.0011
  -5.000  -0.4113   0.01417   0.00920  -0.0219   0.7660   0.0011
  -4.750  -0.3869   0.01254   0.00722  -0.0209   0.7505   0.0011
  -4.500  -0.3617   0.01146   0.00589  -0.0202   0.7355   0.0011
  -4.250  -0.3360   0.01065   0.00488  -0.0196   0.7216   0.0012
  -4.000  -0.3099   0.01002   0.00409  -0.0191   0.7092   0.0014
  -3.750  -0.2833   0.00957   0.00347  -0.0187   0.6985   0.0017
  -3.500  -0.2565   0.00928   0.00308  -0.0185   0.6885   0.0021
  -3.250  -0.2293   0.00907   0.00281  -0.0183   0.6790   0.0023
  -3.000  -0.2021   0.00887   0.00256  -0.0181   0.6705   0.0024
  -2.750  -0.1752   0.00846   0.00199  -0.0178   0.6628   0.0033
  -2.500  -0.1479   0.00823   0.00170  -0.0176   0.6551   0.0046
  -2.250  -0.1204   0.00807   0.00146  -0.0174   0.6482   0.0052
  -2.000  -0.0934   0.00775   0.00122  -0.0171   0.6411   0.0355
  -1.750  -0.0667   0.00744   0.00108  -0.0170   0.6344   0.0882
  -1.500  -0.0397   0.00720   0.00095  -0.0169   0.6271   0.1351
  -1.250  -0.0127   0.00697   0.00086  -0.0167   0.6202   0.1868
  -1.000   0.0144   0.00679   0.00079  -0.0166   0.6126   0.2349
  -0.750   0.0417   0.00662   0.00073  -0.0165   0.6051   0.2794
  -0.500   0.0689   0.00649   0.00067  -0.0165   0.5972   0.3222
  -0.250   0.0956   0.00625   0.00061  -0.0163   0.5885   0.3968
   0.000   0.1219   0.00597   0.00058  -0.0161   0.5797   0.4892
   0.250   0.1478   0.00569   0.00056  -0.0158   0.5695   0.5873
   0.500   0.1728   0.00538   0.00055  -0.0153   0.5580   0.6943
   0.750   0.1964   0.00506   0.00056  -0.0143   0.5453   0.8049
   1.000   0.2213   0.00478   0.00061  -0.0133   0.5297   0.9220
   1.250   0.2697   0.00487   0.00066  -0.0179   0.5059   0.9733
   1.500   0.3045   0.00500   0.00069  -0.0194   0.4817   0.9854
   1.750   0.3377   0.00515   0.00074  -0.0207   0.4561   0.9929
   2.000   0.3758   0.00530   0.00079  -0.0231   0.4297   0.9979
   2.250   0.4087   0.00545   0.00086  -0.0243   0.4054   1.0000
   2.500   0.4344   0.00561   0.00094  -0.0239   0.3834   1.0000
   2.750   0.4602   0.00576   0.00102  -0.0235   0.3625   1.0000
   3.000   0.4859   0.00593   0.00111  -0.0231   0.3404   1.0000
   3.250   0.5091   0.00660   0.00132  -0.0226   0.2384   1.0000
   3.500   0.5332   0.00708   0.00157  -0.0221   0.1765   1.0000
   3.750   0.5567   0.00771   0.00186  -0.0216   0.1018   1.0000
   4.000   0.5799   0.00839   0.00222  -0.0210   0.0346   1.0000
   4.250   0.6040   0.00891   0.00259  -0.0204   0.0015   1.0000
   4.500   0.6295   0.00912   0.00282  -0.0199   0.0012   1.0000
   4.750   0.6550   0.00935   0.00309  -0.0195   0.0010   1.0000
   5.000   0.6803   0.00962   0.00341  -0.0190   0.0010   1.0000
   5.250   0.7054   0.00993   0.00379  -0.0184   0.0010   1.0000
   5.500   0.7302   0.01033   0.00432  -0.0178   0.0010   1.0000
   5.750   0.7545   0.01084   0.00492  -0.0171   0.0010   1.0000
   6.000   0.7781   0.01150   0.00572  -0.0163   0.0010   1.0000
   6.250   0.8006   0.01236   0.00672  -0.0153   0.0010   1.0000
   6.500   0.8216   0.01350   0.00803  -0.0140   0.0011   1.0000
   6.750   0.8414   0.01489   0.00959  -0.0126   0.0012   1.0000
   7.000   0.8603   0.01664   0.01152  -0.0110   0.0013   1.0000
   7.250   0.8789   0.01871   0.01380  -0.0094   0.0014   1.0000
   7.500   0.8959   0.02150   0.01688  -0.0077   0.0016   1.0000
   8.000   0.9263   0.02976   0.02593  -0.0029   0.0037   1.0000
   8.250   0.9379   0.03294   0.02941  -0.0012   0.0037   1.0000
   8.500   0.9475   0.03595   0.03268   0.0004   0.0035   1.0000
   8.750   0.9530   0.03934   0.03633   0.0022   0.0034   1.0000
   9.000   0.9543   0.04280   0.04004   0.0039   0.0034   1.0000
   9.250   0.9526   0.04589   0.04333   0.0055   0.0032   1.0000
   9.500   0.9430   0.04928   0.04691   0.0076   0.0032   1.0000
   9.750   0.9247   0.05239   0.05016   0.0099   0.0032   1.0000
  10.000   0.9103   0.05560   0.05349   0.0096   0.0031   1.0000
  10.250   0.8947   0.05992   0.05793   0.0075   0.0031   1.0000
  10.500   0.8738   0.06636   0.06450   0.0033   0.0032   1.0000
  10.750   0.8530   0.07428   0.07255  -0.0027   0.0034   1.0000
  11.000   0.8368   0.08295   0.08131  -0.0096   0.0034   1.0000
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