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NLR-7223-43 AIRFOIL (nl722343-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NLR-7223-43 AIRFOIL (nl722343-il)
Reynolds number: 1,000,000
Max Cl/Cd: 78.1 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nl722343-il-1000000-n5.txt
Download as CSV file: xf-nl722343-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NLR-7223-43 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5303   0.08391   0.08221  -0.0271   1.0000   0.0051
  -9.250  -0.5340   0.07941   0.07773  -0.0295   1.0000   0.0052
  -9.000  -0.5451   0.07353   0.07189  -0.0336   1.0000   0.0051
  -8.750  -0.5689   0.06764   0.06601  -0.0378   1.0000   0.0051
  -8.500  -0.5908   0.06321   0.06154  -0.0381   1.0000   0.0051
  -8.250  -0.5882   0.05536   0.05351  -0.0446   0.9970   0.0050
  -8.000  -0.5817   0.04699   0.04487  -0.0493   0.9923   0.0049
  -7.750  -0.6092   0.01924   0.01514  -0.0510   0.9806   0.0056
  -7.500  -0.5831   0.01759   0.01321  -0.0513   0.9774   0.0058
  -7.250  -0.5547   0.01639   0.01182  -0.0519   0.9752   0.0058
  -6.750  -0.5023   0.01371   0.00876  -0.0523   0.9678   0.0061
  -6.500  -0.4734   0.01300   0.00797  -0.0528   0.9645   0.0063
  -6.250  -0.4432   0.01237   0.00727  -0.0536   0.9618   0.0064
  -6.000  -0.4129   0.01195   0.00680  -0.0543   0.9588   0.0067
  -5.750  -0.3848   0.01140   0.00618  -0.0546   0.9539   0.0069
  -5.500  -0.3550   0.01092   0.00564  -0.0551   0.9498   0.0072
  -5.250  -0.3250   0.01035   0.00500  -0.0557   0.9462   0.0074
  -5.000  -0.2973   0.00990   0.00450  -0.0558   0.9408   0.0077
  -4.750  -0.2689   0.00950   0.00404  -0.0560   0.9358   0.0079
  -4.250  -0.2139   0.00874   0.00319  -0.0560   0.9263   0.0086
  -4.000  -0.1863   0.00848   0.00290  -0.0560   0.9202   0.0090
  -3.750  -0.1589   0.00825   0.00264  -0.0559   0.9138   0.0094
  -3.500  -0.1321   0.00805   0.00240  -0.0557   0.9061   0.0098
  -3.250  -0.1048   0.00788   0.00218  -0.0555   0.9003   0.0103
  -3.000  -0.0781   0.00771   0.00199  -0.0552   0.8927   0.0110
  -2.750  -0.0521   0.00756   0.00180  -0.0547   0.8776   0.0123
  -2.500  -0.0268   0.00747   0.00161  -0.0540   0.8534   0.0138
  -2.250  -0.0021   0.00740   0.00144  -0.0532   0.8219   0.0169
  -2.000   0.0234   0.00732   0.00130  -0.0526   0.7977   0.0253
  -1.750   0.0493   0.00718   0.00119  -0.0521   0.7804   0.0489
  -1.500   0.0747   0.00695   0.00108  -0.0517   0.7619   0.1045
  -1.000   0.1155   0.00610   0.00082  -0.0494   0.6363   0.4428
  -0.750   0.1353   0.00586   0.00098  -0.0480   0.5712   0.6635
  -0.500   0.1595   0.00625   0.00113  -0.0472   0.5068   0.6829
  -0.250   0.1841   0.00658   0.00126  -0.0464   0.4483   0.6948
   0.000   0.2095   0.00687   0.00134  -0.0459   0.3957   0.6998
   0.250   0.2354   0.00712   0.00138  -0.0455   0.3501   0.7016
   0.500   0.2615   0.00733   0.00142  -0.0452   0.3094   0.7020
   0.750   0.2877   0.00753   0.00146  -0.0449   0.2736   0.7022
   1.000   0.3141   0.00773   0.00151  -0.0447   0.2412   0.7024
   1.250   0.3406   0.00791   0.00157  -0.0444   0.2142   0.7026
   1.500   0.3674   0.00806   0.00162  -0.0442   0.1959   0.7028
   2.000   0.4215   0.00830   0.00175  -0.0439   0.1727   0.7033
   2.250   0.4486   0.00841   0.00182  -0.0437   0.1652   0.7037
   2.500   0.4757   0.00851   0.00190  -0.0436   0.1594   0.7040
   2.750   0.5026   0.00864   0.00199  -0.0434   0.1525   0.7043
   3.000   0.5297   0.00874   0.00209  -0.0432   0.1470   0.7047
   3.250   0.5566   0.00886   0.00219  -0.0431   0.1426   0.7052
   3.500   0.5835   0.00899   0.00230  -0.0429   0.1381   0.7057
   3.750   0.6106   0.00909   0.00242  -0.0427   0.1353   0.7061
   4.000   0.6375   0.00920   0.00254  -0.0425   0.1322   0.7065
   4.250   0.6641   0.00935   0.00267  -0.0423   0.1279   0.7069
   4.500   0.6908   0.00949   0.00281  -0.0421   0.1235   0.7073
   4.750   0.7176   0.00961   0.00294  -0.0419   0.1183   0.7077
   5.000   0.7438   0.00979   0.00309  -0.0417   0.1109   0.7081
   5.250   0.7703   0.00993   0.00323  -0.0414   0.1026   0.7085
   5.500   0.7958   0.01019   0.00341  -0.0411   0.0873   0.7090
   5.750   0.8208   0.01051   0.00366  -0.0407   0.0708   0.7095
   6.000   0.8456   0.01086   0.00394  -0.0402   0.0574   0.7099
   6.250   0.8701   0.01123   0.00426  -0.0397   0.0451   0.7105
   6.500   0.8944   0.01164   0.00461  -0.0392   0.0321   0.7110
   6.750   0.9186   0.01207   0.00498  -0.0386   0.0228   0.7115
   7.000   0.9432   0.01243   0.00534  -0.0381   0.0184   0.7121
   7.250   0.9681   0.01275   0.00569  -0.0377   0.0164   0.7127
   7.500   0.9926   0.01313   0.00608  -0.0371   0.0144   0.7133
   7.750   1.0174   0.01344   0.00644  -0.0367   0.0135   0.7139
   8.000   1.0418   0.01380   0.00683  -0.0362   0.0126   0.7146
   8.250   1.0658   0.01421   0.00727  -0.0356   0.0116   0.7153
   8.500   1.0896   0.01463   0.00774  -0.0351   0.0108   0.7159
   8.750   1.1137   0.01501   0.00817  -0.0345   0.0104   0.7166
   9.000   1.1373   0.01542   0.00863  -0.0339   0.0099   0.7173
   9.250   1.1607   0.01585   0.00912  -0.0333   0.0094   0.7180
   9.500   1.1835   0.01633   0.00965  -0.0326   0.0090   0.7189
   9.750   1.2056   0.01687   0.01026  -0.0318   0.0087   0.7198
  10.000   1.2266   0.01752   0.01099  -0.0309   0.0083   0.7209
  10.250   1.2484   0.01804   0.01160  -0.0300   0.0081   0.7220
  10.500   1.2697   0.01858   0.01222  -0.0292   0.0079   0.7231
  10.750   1.2902   0.01918   0.01291  -0.0282   0.0078   0.7244
  11.000   1.3103   0.01980   0.01362  -0.0272   0.0075   0.7258
  11.250   1.3295   0.02046   0.01438  -0.0260   0.0074   0.7273
  11.500   1.3484   0.02112   0.01512  -0.0248   0.0072   0.7288
  11.750   1.3661   0.02185   0.01594  -0.0235   0.0070   0.7304
  12.000   1.3829   0.02260   0.01678  -0.0221   0.0069   0.7320
  12.500   1.4132   0.02419   0.01857  -0.0189   0.0066   0.7361
  12.750   1.4251   0.02504   0.01953  -0.0167   0.0065   0.7386
  13.000   1.4332   0.02595   0.02053  -0.0140   0.0063   0.7415
  13.250   1.4374   0.02707   0.02178  -0.0109   0.0062   0.7449
  13.750   1.4395   0.02979   0.02476  -0.0046   0.0060   0.7534
  14.000   1.4403   0.03124   0.02635  -0.0020   0.0060   0.7591
  14.250   1.4441   0.03256   0.02780   0.0001   0.0059   0.7660
  14.500   1.4424   0.03434   0.02975   0.0024   0.0059   0.7756
  14.750   1.4398   0.03629   0.03187   0.0043   0.0058   0.7918
  15.000   1.4340   0.03822   0.03429   0.0062   0.0058   0.9382
  15.250   1.4297   0.04151   0.03776   0.0058   0.0058   1.0000
  15.500   1.4184   0.04523   0.04163   0.0058   0.0058   1.0000
  15.750   1.4067   0.04961   0.04617   0.0046   0.0057   1.0000
  16.000   1.3894   0.05571   0.05243   0.0015   0.0057   1.0000
  16.250   1.3600   0.06547   0.06239  -0.0049   0.0058   1.0000
  16.500   1.3226   0.07795   0.07509  -0.0130   0.0058   1.0000
  16.750   1.2812   0.09075   0.08806  -0.0205   0.0058   1.0000
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