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AH21 7% version (Andrew Hollom) (ah21-7-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: AH21 7% version (Andrew Hollom) (ah21-7-il)
Reynolds number: 500,000
Max Cl/Cd: 111.5 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah21-7-il-500000.txt
Download as CSV file: xf-ah21-7-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH21 7% version (Andrew Hollom)                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5192   0.08588   0.08371  -0.0281   1.0000   0.0227
  -8.500  -0.5325   0.08237   0.08025  -0.0281   1.0000   0.0233
  -8.250  -0.5517   0.07913   0.07705  -0.0274   1.0000   0.0233
  -8.000  -0.5700   0.07481   0.07276  -0.0298   0.9992   0.0231
  -7.750  -0.5543   0.05887   0.05645  -0.0500   0.9933   0.0253
  -7.500  -0.5461   0.05242   0.04961  -0.0545   0.9884   0.0255
  -7.250  -0.5430   0.04328   0.04023  -0.0587   0.9853   0.0266
  -7.000  -0.5176   0.04153   0.03844  -0.0608   0.9840   0.0275
  -6.750  -0.5011   0.03978   0.03661  -0.0606   0.9799   0.0290
  -6.500  -0.4719   0.03896   0.03529  -0.0610   0.9766   0.0331
  -6.250  -0.4618   0.02676   0.02217  -0.0618   0.9739   0.0245
  -6.000  -0.4371   0.02194   0.01674  -0.0622   0.9727   0.0223
  -5.750  -0.4066   0.01994   0.01442  -0.0631   0.9719   0.0225
  -5.500  -0.3821   0.01877   0.01306  -0.0626   0.9690   0.0233
  -5.250  -0.3577   0.01746   0.01155  -0.0619   0.9660   0.0235
  -5.000  -0.3288   0.01638   0.01033  -0.0622   0.9639   0.0239
  -4.750  -0.2983   0.01554   0.00938  -0.0629   0.9622   0.0244
  -4.500  -0.2663   0.01482   0.00858  -0.0638   0.9608   0.0249
  -4.250  -0.2329   0.01430   0.00800  -0.0650   0.9596   0.0256
  -4.000  -0.2007   0.01328   0.00693  -0.0662   0.9587   0.0278
  -3.750  -0.1736   0.01287   0.00649  -0.0662   0.9558   0.0292
  -3.500  -0.1490   0.01251   0.00611  -0.0655   0.9516   0.0309
  -3.250  -0.1173   0.01219   0.00574  -0.0664   0.9493   0.0330
  -3.000  -0.0838   0.01174   0.00529  -0.0676   0.9476   0.0401
  -2.750  -0.0501   0.01109   0.00493  -0.0690   0.9463   0.1017
  -2.500  -0.0159   0.01049   0.00472  -0.0708   0.9451   0.2057
  -2.250   0.0191   0.00992   0.00457  -0.0727   0.9442   0.3265
  -2.000   0.0362   0.00950   0.00452  -0.0707   0.9375   0.4330
  -1.750   0.0668   0.00891   0.00444  -0.0715   0.9350   0.5770
  -1.500   0.0990   0.00843   0.00437  -0.0723   0.9332   0.6963
  -1.250   0.1335   0.00810   0.00428  -0.0734   0.9318   0.7696
  -1.000   0.1698   0.00784   0.00415  -0.0748   0.9308   0.8206
  -0.750   0.1883   0.00773   0.00414  -0.0723   0.9239   0.8613
  -0.500   0.2209   0.00752   0.00398  -0.0728   0.9212   0.8910
  -0.250   0.2572   0.00729   0.00378  -0.0742   0.9192   0.9150
   0.000   0.2954   0.00705   0.00355  -0.0758   0.9174   0.9332
   0.250   0.3233   0.00689   0.00341  -0.0753   0.9113   0.9515
   0.500   0.3611   0.00670   0.00322  -0.0771   0.9067   0.9644
   0.750   0.4052   0.00646   0.00296  -0.0802   0.9029   0.9727
   1.000   0.4446   0.00635   0.00285  -0.0824   0.8944   0.9805
   1.250   0.4891   0.00617   0.00266  -0.0857   0.8871   0.9845
   1.500   0.5319   0.00606   0.00254  -0.0888   0.8748   0.9881
   1.750   0.5734   0.00597   0.00243  -0.0916   0.8595   0.9922
   2.000   0.6132   0.00593   0.00235  -0.0940   0.8368   0.9968
   2.250   0.6520   0.00593   0.00226  -0.0963   0.8052   1.0000
   2.500   0.6712   0.00602   0.00219  -0.0943   0.7635   1.0000
   2.750   0.6848   0.00625   0.00220  -0.0911   0.7132   1.0000
   3.000   0.6937   0.00659   0.00227  -0.0870   0.6530   1.0000
   3.250   0.7009   0.00703   0.00239  -0.0826   0.5848   1.0000
   3.500   0.7104   0.00758   0.00258  -0.0788   0.5097   1.0000
   3.750   0.7231   0.00818   0.00282  -0.0758   0.4313   1.0000
   4.000   0.7386   0.00880   0.00310  -0.0735   0.3548   1.0000
   4.250   0.7564   0.00941   0.00338  -0.0717   0.2877   1.0000
   4.500   0.7755   0.00999   0.00367  -0.0702   0.2295   1.0000
   4.750   0.7958   0.01052   0.00398  -0.0689   0.1813   1.0000
   5.000   0.8168   0.01102   0.00431  -0.0678   0.1446   1.0000
   5.250   0.8383   0.01151   0.00464  -0.0667   0.1158   1.0000
   5.500   0.8603   0.01195   0.00498  -0.0657   0.0946   1.0000
   5.750   0.8823   0.01240   0.00536  -0.0646   0.0796   1.0000
   6.000   0.9044   0.01284   0.00576  -0.0636   0.0687   1.0000
   6.250   0.9259   0.01334   0.00624  -0.0625   0.0600   1.0000
   6.500   0.9481   0.01376   0.00665  -0.0615   0.0538   1.0000
   6.750   0.9686   0.01434   0.00725  -0.0602   0.0488   1.0000
   7.000   0.9909   0.01475   0.00770  -0.0592   0.0452   1.0000
   7.250   1.0110   0.01535   0.00830  -0.0579   0.0413   1.0000
   7.500   1.0303   0.01603   0.00904  -0.0564   0.0386   1.0000
   7.750   1.0516   0.01651   0.00958  -0.0553   0.0364   1.0000
   8.000   1.0723   0.01702   0.01013  -0.0541   0.0343   1.0000
   8.250   1.0903   0.01780   0.01094  -0.0525   0.0320   1.0000
   8.500   1.1068   0.01883   0.01206  -0.0507   0.0302   1.0000
   8.750   1.1267   0.01937   0.01268  -0.0493   0.0290   1.0000
   9.000   1.1458   0.01993   0.01331  -0.0479   0.0274   1.0000
   9.250   1.1642   0.02049   0.01391  -0.0464   0.0260   1.0000
   9.500   1.1801   0.02136   0.01483  -0.0446   0.0245   1.0000
   9.750   1.1948   0.02292   0.01651  -0.0428   0.0232   1.0000
  10.000   1.2125   0.02344   0.01713  -0.0412   0.0222   1.0000
  10.250   1.2289   0.02410   0.01790  -0.0394   0.0211   1.0000
  10.500   1.2443   0.02475   0.01861  -0.0377   0.0201   1.0000
  10.750   1.2585   0.02546   0.01935  -0.0358   0.0191   1.0000
  11.000   1.2663   0.02780   0.02184  -0.0333   0.0179   1.0000
  11.250   1.2787   0.02874   0.02295  -0.0312   0.0174   1.0000
  11.500   1.2905   0.02957   0.02392  -0.0290   0.0166   1.0000
  11.750   1.3007   0.03057   0.02505  -0.0268   0.0158   1.0000
  12.000   1.3103   0.03148   0.02605  -0.0246   0.0151   1.0000
  12.250   1.3198   0.03228   0.02691  -0.0226   0.0145   1.0000
  12.500   1.3246   0.03370   0.02839  -0.0203   0.0139   1.0000
  12.750   1.3160   0.03709   0.03203  -0.0169   0.0133   1.0000
  13.000   1.3188   0.03871   0.03384  -0.0147   0.0131   1.0000
  13.250   1.3184   0.04074   0.03608  -0.0125   0.0128   1.0000
  13.500   1.3162   0.04301   0.03855  -0.0105   0.0124   1.0000
  13.750   1.3115   0.04565   0.04139  -0.0088   0.0122   1.0000
  14.000   1.3046   0.04863   0.04456  -0.0074   0.0119   1.0000
  14.250   1.2969   0.05185   0.04795  -0.0067   0.0116   1.0000
  14.500   1.2845   0.05596   0.05226  -0.0065   0.0115   1.0000
  14.750   1.2729   0.06025   0.05672  -0.0071   0.0113   1.0000
  15.000   1.2580   0.06548   0.06213  -0.0087   0.0112   1.0000
  15.250   1.2352   0.07260   0.06948  -0.0119   0.0113   1.0000
  15.500   1.2163   0.07988   0.07693  -0.0160   0.0112   1.0000
  15.750   1.1836   0.09092   0.08823  -0.0228   0.0114   1.0000
  16.000   1.1382   0.10633   0.10390  -0.0329   0.0118   1.0000
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