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S4320 (s4320-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S4320 (s4320-il)
Reynolds number: 500,000
Max Cl/Cd: 106.44 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4320-il-500000-n5.txt
Download as CSV file: xf-s4320-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3071   0.10516   0.10289  -0.0276   1.0000   0.0065
  -9.500  -0.3058   0.10068   0.09844  -0.0294   1.0000   0.0067
  -9.250  -0.3031   0.09687   0.09465  -0.0309   1.0000   0.0067
  -8.750  -0.2771   0.08729   0.08507  -0.0405   0.9561   0.0068
  -8.500  -0.2565   0.08216   0.07989  -0.0476   0.9301   0.0070
  -8.250  -0.2376   0.08048   0.07811  -0.0501   0.9021   0.0074
  -8.000  -0.2301   0.07809   0.07564  -0.0514   0.8773   0.0078
  -7.750  -0.2308   0.07448   0.07196  -0.0526   0.8557   0.0076
  -7.500  -0.2280   0.07202   0.06944  -0.0533   0.8380   0.0082
  -7.250  -0.2286   0.06900   0.06638  -0.0546   0.8221   0.0085
  -7.000  -0.2250   0.06500   0.06233  -0.0581   0.8085   0.0085
  -6.750  -0.2186   0.06027   0.05755  -0.0630   0.7961   0.0084
  -6.500  -0.2087   0.05413   0.05133  -0.0699   0.7850   0.0084
  -6.250  -0.1944   0.04604   0.04309  -0.0785   0.7754   0.0085
  -6.000  -0.1853   0.02001   0.01521  -0.0927   0.7687   0.0097
  -5.750  -0.1600   0.01829   0.01321  -0.0932   0.7608   0.0101
  -5.500  -0.1332   0.01784   0.01264  -0.0933   0.7527   0.0105
  -5.250  -0.1061   0.01722   0.01188  -0.0934   0.7451   0.0112
  -5.000  -0.0790   0.01623   0.01062  -0.0935   0.7375   0.0120
  -4.750  -0.0514   0.01507   0.00916  -0.0935   0.7304   0.0126
  -4.500  -0.0237   0.01428   0.00812  -0.0935   0.7231   0.0131
  -4.250   0.0042   0.01367   0.00731  -0.0934   0.7162   0.0134
  -4.000   0.0314   0.01256   0.00605  -0.0935   0.7091   0.0142
  -3.750   0.0592   0.01214   0.00558  -0.0935   0.7024   0.0151
  -3.500   0.0871   0.01172   0.00506  -0.0935   0.6954   0.0159
  -3.250   0.1151   0.01126   0.00450  -0.0934   0.6889   0.0165
  -3.000   0.1432   0.01086   0.00401  -0.0934   0.6820   0.0171
  -2.750   0.1713   0.01053   0.00360  -0.0933   0.6756   0.0176
  -2.500   0.1996   0.01025   0.00325  -0.0933   0.6685   0.0181
  -2.250   0.2277   0.00992   0.00284  -0.0933   0.6621   0.0191
  -2.000   0.2561   0.00965   0.00253  -0.0934   0.6550   0.0204
  -1.500   0.3128   0.00933   0.00209  -0.0933   0.6410   0.0226
  -1.000   0.3695   0.00912   0.00178  -0.0933   0.6263   0.0276
  -0.750   0.3976   0.00895   0.00167  -0.0933   0.6188   0.0562
  -0.500   0.4259   0.00870   0.00161  -0.0934   0.6106   0.1195
  -0.250   0.4539   0.00850   0.00158  -0.0936   0.6027   0.1931
   0.000   0.4820   0.00835   0.00156  -0.0937   0.5940   0.2577
   0.250   0.5099   0.00816   0.00157  -0.0938   0.5857   0.3416
   0.500   0.5371   0.00774   0.00164  -0.0939   0.5769   0.5292
   0.750   0.5610   0.00715   0.00176  -0.0931   0.5684   0.7704
   1.000   0.5880   0.00678   0.00172  -0.0923   0.5596   1.0000
   1.250   0.6162   0.00687   0.00173  -0.0923   0.5500   1.0000
   1.500   0.6442   0.00698   0.00176  -0.0923   0.5400   1.0000
   1.750   0.6721   0.00709   0.00180  -0.0923   0.5295   1.0000
   2.000   0.6998   0.00722   0.00184  -0.0922   0.5179   1.0000
   2.250   0.7276   0.00734   0.00190  -0.0921   0.5054   1.0000
   2.500   0.7552   0.00748   0.00197  -0.0921   0.4925   1.0000
   2.750   0.7826   0.00764   0.00205  -0.0920   0.4793   1.0000
   3.000   0.8100   0.00780   0.00215  -0.0919   0.4649   1.0000
   3.250   0.8371   0.00798   0.00225  -0.0918   0.4502   1.0000
   3.500   0.8641   0.00818   0.00239  -0.0917   0.4348   1.0000
   3.750   0.8910   0.00840   0.00253  -0.0915   0.4188   1.0000
   4.250   0.9441   0.00887   0.00285  -0.0912   0.3850   1.0000
   4.500   0.9705   0.00913   0.00305  -0.0910   0.3673   1.0000
   4.750   0.9966   0.00941   0.00325  -0.0908   0.3493   1.0000
   5.000   1.0224   0.00971   0.00347  -0.0906   0.3320   1.0000
   5.250   1.0481   0.01002   0.00371  -0.0903   0.3145   1.0000
   5.500   1.0737   0.01034   0.00398  -0.0901   0.2975   1.0000
   5.750   1.0991   0.01067   0.00425  -0.0898   0.2811   1.0000
   6.000   1.1243   0.01100   0.00453  -0.0895   0.2655   1.0000
   6.250   1.1493   0.01136   0.00483  -0.0892   0.2501   1.0000
   6.500   1.1740   0.01172   0.00516  -0.0888   0.2352   1.0000
   6.750   1.1985   0.01210   0.00549  -0.0884   0.2207   1.0000
   7.000   1.2230   0.01246   0.00582  -0.0881   0.2086   1.0000
   7.250   1.2471   0.01285   0.00618  -0.0876   0.1960   1.0000
   7.500   1.2707   0.01327   0.00658  -0.0871   0.1828   1.0000
   7.750   1.2942   0.01369   0.00698  -0.0866   0.1719   1.0000
   8.000   1.3169   0.01417   0.00741  -0.0860   0.1589   1.0000
   8.250   1.3388   0.01469   0.00788  -0.0854   0.1440   1.0000
   8.500   1.3605   0.01521   0.00838  -0.0846   0.1314   1.0000
   8.750   1.3813   0.01578   0.00891  -0.0838   0.1181   1.0000
   9.000   1.4011   0.01641   0.00948  -0.0829   0.1035   1.0000
   9.250   1.4202   0.01706   0.01008  -0.0818   0.0904   1.0000
   9.500   1.4388   0.01771   0.01071  -0.0807   0.0803   1.0000
   9.750   1.4561   0.01841   0.01139  -0.0795   0.0703   1.0000
  10.000   1.4718   0.01919   0.01212  -0.0780   0.0596   1.0000
  10.250   1.4864   0.01995   0.01288  -0.0764   0.0509   1.0000
  10.500   1.4978   0.02073   0.01366  -0.0742   0.0431   1.0000
  10.750   1.5047   0.02174   0.01463  -0.0715   0.0336   1.0000
  11.000   1.5094   0.02295   0.01580  -0.0689   0.0244   1.0000
  11.250   1.5114   0.02444   0.01726  -0.0662   0.0146   1.0000
  11.500   1.5120   0.02615   0.01896  -0.0638   0.0080   1.0000
  11.750   1.5169   0.02766   0.02055  -0.0619   0.0063   1.0000
  12.000   1.5217   0.02928   0.02225  -0.0603   0.0053   1.0000
  12.250   1.5277   0.03088   0.02394  -0.0589   0.0049   1.0000
  12.500   1.5337   0.03257   0.02574  -0.0578   0.0045   1.0000
  12.750   1.5385   0.03443   0.02771  -0.0567   0.0043   1.0000
  13.000   1.5427   0.03644   0.02984  -0.0558   0.0041   1.0000
  13.250   1.5454   0.03867   0.03218  -0.0550   0.0039   1.0000
  13.500   1.5463   0.04118   0.03480  -0.0544   0.0037   1.0000
  13.750   1.5457   0.04396   0.03771  -0.0540   0.0035   1.0000
  14.000   1.5437   0.04699   0.04088  -0.0537   0.0034   1.0000
  14.250   1.5405   0.05031   0.04433  -0.0537   0.0032   1.0000
  14.500   1.5387   0.05354   0.04768  -0.0538   0.0031   1.0000
  14.750   1.5357   0.05707   0.05135  -0.0542   0.0031   1.0000
  15.000   1.5321   0.06085   0.05526  -0.0549   0.0030   1.0000
  15.250   1.5262   0.06508   0.05963  -0.0558   0.0029   1.0000
  15.500   1.5214   0.06933   0.06400  -0.0569   0.0028   1.0000
  15.750   1.5149   0.07401   0.06882  -0.0583   0.0027   1.0000
  16.000   1.5050   0.07942   0.07437  -0.0601   0.0027   1.0000
  16.250   1.4969   0.08468   0.07977  -0.0621   0.0026   1.0000
  16.500   1.4860   0.09065   0.08588  -0.0645   0.0026   1.0000
  16.750   1.4740   0.09695   0.09233  -0.0672   0.0025   1.0000
  17.000   1.4624   0.10339   0.09891  -0.0700   0.0025   1.0000
  17.250   1.4495   0.11022   0.10589  -0.0732   0.0025   1.0000
  17.500   1.4364   0.11723   0.11304  -0.0767   0.0025   1.0000
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