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S4320 (s4320-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S4320 (s4320-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.19 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4320-il-1000000-n5.txt
Download as CSV file: xf-s4320-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4320                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3319   0.11713   0.11546  -0.0224   1.0000   0.0039
 -10.500  -0.3270   0.11368   0.11202  -0.0236   1.0000   0.0038
  -8.000  -0.4042   0.02051   0.01698  -0.0918   0.7822   0.0060
  -7.750  -0.3819   0.01765   0.01363  -0.0925   0.7735   0.0065
  -7.500  -0.3566   0.01626   0.01195  -0.0927   0.7651   0.0067
  -7.250  -0.3306   0.01511   0.01057  -0.0929   0.7567   0.0070
  -7.000  -0.3036   0.01458   0.00992  -0.0930   0.7486   0.0073
  -6.750  -0.2761   0.01429   0.00956  -0.0930   0.7406   0.0075
  -6.500  -0.2486   0.01400   0.00917  -0.0930   0.7330   0.0077
  -6.250  -0.2210   0.01358   0.00865  -0.0930   0.7253   0.0080
  -6.000  -0.1935   0.01308   0.00801  -0.0931   0.7182   0.0084
  -5.750  -0.1659   0.01252   0.00730  -0.0931   0.7108   0.0088
  -5.500  -0.1382   0.01203   0.00667  -0.0931   0.7041   0.0092
  -5.250  -0.1102   0.01170   0.00623  -0.0931   0.6970   0.0096
  -5.000  -0.0824   0.01119   0.00560  -0.0931   0.6906   0.0100
  -4.750  -0.0544   0.01081   0.00516  -0.0932   0.6837   0.0104
  -4.500  -0.0264   0.01054   0.00482  -0.0932   0.6773   0.0108
  -4.250   0.0018   0.01023   0.00444  -0.0932   0.6707   0.0111
  -4.000   0.0300   0.00993   0.00407  -0.0932   0.6642   0.0116
  -3.750   0.0583   0.00963   0.00370  -0.0932   0.6579   0.0121
  -3.500   0.0866   0.00942   0.00343  -0.0932   0.6512   0.0127
  -3.250   0.1150   0.00924   0.00319  -0.0932   0.6450   0.0131
  -3.000   0.1434   0.00905   0.00293  -0.0933   0.6380   0.0134
  -2.750   0.1717   0.00869   0.00250  -0.0933   0.6318   0.0138
  -2.500   0.2002   0.00842   0.00218  -0.0933   0.6247   0.0144
  -2.250   0.2286   0.00825   0.00195  -0.0934   0.6180   0.0150
  -2.000   0.2571   0.00811   0.00177  -0.0934   0.6107   0.0156
  -1.750   0.2855   0.00801   0.00163  -0.0934   0.6035   0.0165
  -1.500   0.3141   0.00791   0.00149  -0.0934   0.5955   0.0173
  -1.250   0.3425   0.00784   0.00137  -0.0934   0.5876   0.0179
  -1.000   0.3710   0.00778   0.00126  -0.0935   0.5790   0.0186
  -0.750   0.3994   0.00773   0.00117  -0.0935   0.5708   0.0205
  -0.500   0.4278   0.00769   0.00110  -0.0935   0.5618   0.0237
  -0.250   0.4562   0.00756   0.00105  -0.0936   0.5530   0.0582
   0.000   0.4845   0.00740   0.00103  -0.0937   0.5444   0.1181
   0.250   0.5127   0.00729   0.00103  -0.0938   0.5349   0.1720
   0.500   0.5410   0.00718   0.00104  -0.0939   0.5255   0.2339
   0.750   0.5690   0.00704   0.00108  -0.0941   0.5153   0.3173
   1.000   0.5970   0.00690   0.00113  -0.0942   0.5039   0.4114
   1.250   0.6244   0.00658   0.00122  -0.0944   0.4920   0.5906
   1.500   0.6510   0.00632   0.00133  -0.0941   0.4794   0.7426
   1.750   0.6749   0.00612   0.00141  -0.0932   0.4667   0.8655
   2.000   0.7035   0.00603   0.00144  -0.0931   0.4532   1.0000
   2.250   0.7313   0.00618   0.00150  -0.0931   0.4390   1.0000
   2.500   0.7590   0.00634   0.00158  -0.0931   0.4239   1.0000
   2.750   0.7865   0.00652   0.00167  -0.0930   0.4082   1.0000
   3.000   0.8140   0.00670   0.00177  -0.0930   0.3926   1.0000
   3.250   0.8413   0.00689   0.00188  -0.0929   0.3769   1.0000
   3.500   0.8684   0.00711   0.00202  -0.0928   0.3594   1.0000
   3.750   0.8955   0.00733   0.00215  -0.0928   0.3427   1.0000
   4.000   0.9225   0.00755   0.00230  -0.0927   0.3261   1.0000
   4.250   0.9493   0.00778   0.00245  -0.0926   0.3106   1.0000
   4.500   0.9760   0.00802   0.00263  -0.0924   0.2941   1.0000
   4.750   1.0026   0.00827   0.00280  -0.0923   0.2788   1.0000
   5.000   1.0290   0.00853   0.00299  -0.0922   0.2634   1.0000
   5.250   1.0554   0.00878   0.00318  -0.0920   0.2501   1.0000
   5.500   1.0816   0.00906   0.00340  -0.0918   0.2358   1.0000
   5.750   1.1076   0.00934   0.00362  -0.0917   0.2219   1.0000
   6.000   1.1334   0.00963   0.00386  -0.0914   0.2080   1.0000
   6.250   1.1593   0.00991   0.00409  -0.0912   0.1969   1.0000
   6.500   1.1849   0.01021   0.00435  -0.0910   0.1856   1.0000
   6.750   1.2101   0.01054   0.00463  -0.0907   0.1731   1.0000
   7.000   1.2351   0.01087   0.00491  -0.0904   0.1615   1.0000
   7.500   1.2836   0.01167   0.00559  -0.0896   0.1332   1.0000
   7.750   1.3075   0.01207   0.00593  -0.0892   0.1213   1.0000
   8.000   1.3310   0.01250   0.00631  -0.0887   0.1088   1.0000
   8.250   1.3534   0.01302   0.00674  -0.0880   0.0938   1.0000
   8.500   1.3756   0.01353   0.00720  -0.0874   0.0807   1.0000
   8.750   1.3976   0.01404   0.00766  -0.0867   0.0708   1.0000
   9.000   1.4190   0.01457   0.00815  -0.0859   0.0609   1.0000
   9.250   1.4400   0.01511   0.00865  -0.0851   0.0519   1.0000
   9.500   1.4601   0.01570   0.00921  -0.0842   0.0430   1.0000
   9.750   1.4771   0.01650   0.00993  -0.0829   0.0309   1.0000
  10.000   1.4930   0.01734   0.01070  -0.0814   0.0201   1.0000
  10.250   1.5024   0.01858   0.01185  -0.0790   0.0067   1.0000
  10.500   1.5168   0.01933   0.01263  -0.0772   0.0045   1.0000
  10.750   1.5290   0.01999   0.01334  -0.0750   0.0040   1.0000
  11.000   1.5393   0.02072   0.01412  -0.0727   0.0034   1.0000
  11.250   1.5497   0.02148   0.01496  -0.0705   0.0032   1.0000
  11.500   1.5601   0.02231   0.01585  -0.0685   0.0030   1.0000
  11.750   1.5700   0.02322   0.01683  -0.0666   0.0028   1.0000
  12.000   1.5788   0.02427   0.01795  -0.0648   0.0026   1.0000
  12.250   1.5871   0.02543   0.01917  -0.0631   0.0025   1.0000
  12.500   1.5940   0.02676   0.02058  -0.0615   0.0023   1.0000
  12.750   1.5999   0.02826   0.02216  -0.0599   0.0021   1.0000
  13.000   1.6048   0.02992   0.02391  -0.0585   0.0020   1.0000
  13.250   1.6097   0.03167   0.02574  -0.0573   0.0019   1.0000
  13.500   1.6147   0.03348   0.02765  -0.0563   0.0019   1.0000
  13.750   1.6199   0.03534   0.02960  -0.0554   0.0019   1.0000
  14.000   1.6233   0.03746   0.03181  -0.0547   0.0018   1.0000
  14.250   1.6267   0.03965   0.03408  -0.0541   0.0017   1.0000
  14.500   1.6281   0.04214   0.03667  -0.0536   0.0017   1.0000
  14.750   1.6287   0.04481   0.03944  -0.0533   0.0017   1.0000
  15.000   1.6279   0.04774   0.04247  -0.0532   0.0016   1.0000
  15.250   1.6255   0.05096   0.04580  -0.0533   0.0016   1.0000
  15.500   1.6239   0.05421   0.04915  -0.0535   0.0015   1.0000
  15.750   1.6209   0.05779   0.05284  -0.0540   0.0015   1.0000
  16.000   1.6152   0.06190   0.05706  -0.0548   0.0014   1.0000
  16.250   1.6112   0.06589   0.06116  -0.0558   0.0014   1.0000
  16.500   1.6041   0.07053   0.06593  -0.0571   0.0014   1.0000
  16.750   1.5956   0.07556   0.07109  -0.0587   0.0014   1.0000
  17.000   1.5880   0.08059   0.07623  -0.0605   0.0013   1.0000
  17.250   1.5776   0.08628   0.08205  -0.0627   0.0013   1.0000
  17.500   1.5662   0.09232   0.08821  -0.0652   0.0013   1.0000
  17.750   1.5513   0.09916   0.09519  -0.0682   0.0013   1.0000
  18.000   1.5376   0.10598   0.10215  -0.0713   0.0013   1.0000
  18.250   1.5243   0.11286   0.10915  -0.0746   0.0012   1.0000
  18.500   1.5085   0.12037   0.11680  -0.0784   0.0012   1.0000
  18.750   1.4931   0.12796   0.12452  -0.0824   0.0012   1.0000
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