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MH 22 7.2% (mh22-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 22 7.2% (mh22-il)
Reynolds number: 100,000
Max Cl/Cd: 48.54 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh22-il-100000.txt
Download as CSV file: xf-mh22-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.5232   0.09233   0.08792  -0.0029   1.0000   0.0769
  -7.500  -0.5250   0.08859   0.08424  -0.0071   1.0000   0.0772
  -7.250  -0.5266   0.08440   0.08001  -0.0156   1.0000   0.0779
  -7.000  -0.4485   0.07194   0.06801  -0.0070   1.0000   0.0964
  -6.750  -0.4500   0.06778   0.06388  -0.0098   1.0000   0.1004
  -6.500  -0.4636   0.06265   0.05858  -0.0212   1.0000   0.1043
  -5.500  -0.4540   0.05563   0.05106  -0.0229   1.0000   0.1251
  -5.250  -0.4392   0.05162   0.04694  -0.0243   1.0000   0.1356
  -5.000  -0.4229   0.04800   0.04318  -0.0252   1.0000   0.1480
  -4.750  -0.3896   0.03652   0.03041  -0.0283   1.0000   0.0616
  -4.500  -0.3672   0.03128   0.02449  -0.0272   1.0000   0.0486
  -4.250  -0.3450   0.02736   0.01999  -0.0259   1.0000   0.0443
  -4.000  -0.3208   0.02422   0.01614  -0.0242   1.0000   0.0416
  -3.750  -0.2971   0.02185   0.01342  -0.0229   1.0000   0.0416
  -3.500  -0.2743   0.01985   0.01125  -0.0215   1.0000   0.0433
  -3.250  -0.2528   0.01827   0.00958  -0.0199   1.0000   0.0473
  -3.000  -0.2343   0.01701   0.00834  -0.0182   1.0000   0.0605
  -2.750  -0.2194   0.01552   0.00714  -0.0160   1.0000   0.1143
  -2.500  -0.2069   0.01412   0.00639  -0.0138   1.0000   0.2314
  -2.250  -0.0893   0.01066   0.00526  -0.0279   1.0000   1.0000
  -2.000  -0.0840   0.01084   0.00522  -0.0248   1.0000   1.0000
  -1.750  -0.0833   0.01115   0.00533  -0.0211   1.0000   1.0000
  -1.500  -0.0672   0.01144   0.00529  -0.0202   0.9972   1.0000
  -1.250  -0.0137   0.01162   0.00514  -0.0260   0.9842   1.0000
  -1.000   0.0392   0.01174   0.00501  -0.0315   0.9719   1.0000
  -0.750   0.0926   0.01179   0.00486  -0.0370   0.9602   1.0000
  -0.500   0.1426   0.01180   0.00465  -0.0417   0.9475   1.0000
  -0.250   0.1877   0.01181   0.00455  -0.0452   0.9335   1.0000
   0.000   0.2273   0.01185   0.00450  -0.0474   0.9185   1.0000
   0.250   0.2610   0.01193   0.00450  -0.0484   0.9030   1.0000
   0.500   0.2883   0.01208   0.00460  -0.0480   0.8864   1.0000
   0.750   0.3123   0.01226   0.00472  -0.0469   0.8695   1.0000
   1.000   0.3352   0.01245   0.00486  -0.0455   0.8532   1.0000
   1.250   0.3573   0.01264   0.00501  -0.0438   0.8375   1.0000
   1.500   0.3790   0.01285   0.00517  -0.0421   0.8219   1.0000
   1.750   0.4007   0.01308   0.00539  -0.0405   0.8049   1.0000
   2.000   0.4227   0.01330   0.00566  -0.0389   0.7883   1.0000
   2.250   0.4448   0.01350   0.00584  -0.0372   0.7721   1.0000
   2.500   0.4671   0.01370   0.00603  -0.0356   0.7557   1.0000
   2.750   0.4898   0.01392   0.00628  -0.0342   0.7369   1.0000
   3.000   0.5126   0.01410   0.00647  -0.0326   0.7191   1.0000
   3.250   0.5356   0.01430   0.00670  -0.0311   0.6999   1.0000
   3.500   0.5588   0.01447   0.00701  -0.0296   0.6798   1.0000
   3.750   0.5822   0.01464   0.00724  -0.0282   0.6585   1.0000
   4.000   0.6057   0.01475   0.00737  -0.0267   0.6375   1.0000
   4.250   0.6294   0.01488   0.00758  -0.0253   0.6128   1.0000
   4.500   0.6531   0.01497   0.00776  -0.0239   0.5868   1.0000
   4.750   0.6769   0.01502   0.00789  -0.0225   0.5590   1.0000
   5.000   0.7004   0.01509   0.00806  -0.0211   0.5262   1.0000
   5.250   0.7235   0.01517   0.00819  -0.0195   0.4879   1.0000
   5.500   0.7451   0.01535   0.00849  -0.0177   0.4372   1.0000
   5.750   0.7622   0.01583   0.00865  -0.0156   0.3258   1.0000
   6.000   0.7603   0.02092   0.01149  -0.0124   0.0476   1.0000
   6.250   0.7755   0.02325   0.01386  -0.0103   0.0357   1.0000
   6.500   0.7956   0.02470   0.01542  -0.0090   0.0273   1.0000
   6.750   0.8131   0.02738   0.01813  -0.0075   0.0237   1.0000
   7.000   0.8355   0.02971   0.02066  -0.0061   0.0227   1.0000
   7.250   0.8575   0.03255   0.02380  -0.0048   0.0225   1.0000
   7.500   0.8773   0.03582   0.02746  -0.0034   0.0226   1.0000
   7.750   0.8935   0.03948   0.03154  -0.0021   0.0231   1.0000
   8.000   0.9054   0.04371   0.03620  -0.0007   0.0237   1.0000
   8.250   0.9153   0.04871   0.04154   0.0003   0.0246   1.0000
   8.500   0.9297   0.05024   0.04363   0.0023   0.0266   1.0000
   8.750   0.9226   0.05559   0.04972   0.0041   0.0294   1.0000
   9.000   0.9153   0.06036   0.05483   0.0050   0.0312   1.0000
   9.250   0.9055   0.06471   0.05940   0.0055   0.0324   1.0000
   9.500   0.8901   0.06869   0.06353   0.0061   0.0332   1.0000
   9.750   0.8731   0.07296   0.06792   0.0049   0.0335   1.0000
  10.000   0.8566   0.07792   0.07298   0.0021   0.0338   1.0000
  10.250   0.8394   0.08384   0.07898  -0.0023   0.0339   1.0000
  10.500   0.8226   0.09104   0.08624  -0.0079   0.0340   1.0000
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