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S4320 (s4320-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S4320 (s4320-il)
Reynolds number: 100,000
Max Cl/Cd: 59.1 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4320-il-100000.txt
Download as CSV file: xf-s4320-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2909   0.09632   0.09205  -0.0355   1.0000   0.0791
  -7.500  -0.3134   0.09639   0.09229  -0.0331   1.0000   0.0793
  -7.250  -0.3363   0.09638   0.09243  -0.0297   1.0000   0.0794
  -7.000  -0.3584   0.09626   0.09242  -0.0276   1.0000   0.0795
  -6.750  -0.3756   0.09560   0.09184  -0.0280   1.0000   0.0797
  -6.500  -0.3667   0.09050   0.08680  -0.0240   0.9982   0.0812
  -6.250  -0.3413   0.08663   0.08291  -0.0234   0.9940   0.0868
  -6.000  -0.3009   0.08004   0.07620  -0.0483   0.9801   0.0944
  -5.750  -0.2842   0.07682   0.07305  -0.0411   0.9760   0.0990
  -5.500  -0.2442   0.07063   0.06669  -0.0601   0.9647   0.1091
  -5.250  -0.2215   0.06728   0.06338  -0.0579   0.9595   0.1136
  -5.000  -0.1861   0.06207   0.05801  -0.0695   0.9499   0.1248
  -4.750  -0.1460   0.05750   0.05325  -0.0783   0.9435   0.1389
  -4.500  -0.1237   0.05478   0.05057  -0.0780   0.9353   0.1475
  -4.250  -0.0839   0.05064   0.04628  -0.0852   0.9295   0.1703
  -4.000  -0.0506   0.04796   0.04334  -0.0906   0.9204   0.1977
  -3.750  -0.0164   0.04450   0.03990  -0.0929   0.9154   0.2149
  -3.500   0.0595   0.03104   0.02428  -0.1065   0.9103   0.0822
  -3.250   0.0953   0.02853   0.02122  -0.1078   0.9027   0.0776
  -3.000   0.1391   0.02631   0.01843  -0.1103   0.8984   0.0787
  -2.750   0.1661   0.02482   0.01662  -0.1099   0.8887   0.0783
  -2.500   0.2064   0.02325   0.01470  -0.1114   0.8839   0.0796
  -2.250   0.2315   0.02210   0.01353  -0.1108   0.8743   0.0828
  -2.000   0.2683   0.02122   0.01255  -0.1116   0.8690   0.0935
  -1.750   0.2918   0.02052   0.01197  -0.1107   0.8589   0.1049
  -1.500   0.3232   0.01912   0.01099  -0.1108   0.8527   0.1776
  -1.250   0.3410   0.01740   0.01105  -0.1089   0.8436   0.6261
  -1.000   0.3771   0.01655   0.01062  -0.1085   0.8376   1.0000
  -0.750   0.4036   0.01676   0.01054  -0.1081   0.8280   1.0000
  -0.500   0.4304   0.01697   0.01049  -0.1077   0.8191   1.0000
  -0.250   0.4597   0.01703   0.01031  -0.1074   0.8115   1.0000
   0.000   0.4847   0.01731   0.01042  -0.1068   0.8014   1.0000
   0.250   0.5150   0.01728   0.01018  -0.1064   0.7950   1.0000
   0.500   0.5391   0.01759   0.01037  -0.1058   0.7840   1.0000
   0.750   0.5651   0.01779   0.01045  -0.1052   0.7746   1.0000
   1.000   0.5937   0.01779   0.01030  -0.1045   0.7668   1.0000
   1.250   0.6184   0.01806   0.01049  -0.1039   0.7559   1.0000
   1.500   0.6452   0.01818   0.01051  -0.1032   0.7469   1.0000
   1.750   0.6727   0.01821   0.01044  -0.1025   0.7379   1.0000
   2.000   0.6977   0.01845   0.01063  -0.1018   0.7269   1.0000
   2.250   0.7245   0.01854   0.01065  -0.1011   0.7175   1.0000
   2.500   0.7522   0.01853   0.01056  -0.1004   0.7082   1.0000
   2.750   0.7773   0.01875   0.01077  -0.0996   0.6966   1.0000
   3.000   0.8033   0.01888   0.01086  -0.0989   0.6858   1.0000
   3.250   0.8318   0.01878   0.01067  -0.0982   0.6769   1.0000
   3.500   0.8574   0.01891   0.01079  -0.0974   0.6648   1.0000
   3.750   0.8829   0.01905   0.01096  -0.0967   0.6523   1.0000
   4.000   0.9089   0.01913   0.01103  -0.0959   0.6399   1.0000
   4.250   0.9353   0.01917   0.01105  -0.0951   0.6274   1.0000
   4.500   0.9618   0.01918   0.01104  -0.0944   0.6148   1.0000
   4.750   0.9884   0.01919   0.01106  -0.0936   0.6016   1.0000
   5.000   1.0145   0.01922   0.01107  -0.0928   0.5876   1.0000
   5.250   1.0402   0.01928   0.01114  -0.0920   0.5725   1.0000
   5.500   1.0655   0.01937   0.01127  -0.0911   0.5565   1.0000
   5.750   1.0906   0.01947   0.01138  -0.0903   0.5398   1.0000
   6.000   1.1157   0.01958   0.01148  -0.0894   0.5225   1.0000
   6.250   1.1410   0.01969   0.01156  -0.0886   0.5049   1.0000
   6.500   1.1649   0.01992   0.01182  -0.0877   0.4857   1.0000
   6.750   1.1882   0.02021   0.01212  -0.0867   0.4653   1.0000
   7.000   1.2122   0.02051   0.01234  -0.0858   0.4458   1.0000
   7.250   1.2337   0.02097   0.01284  -0.0847   0.4239   1.0000
   7.500   1.2561   0.02145   0.01327  -0.0837   0.4034   1.0000
   7.750   1.2768   0.02205   0.01389  -0.0826   0.3819   1.0000
   8.000   1.2977   0.02269   0.01448  -0.0815   0.3613   1.0000
   8.250   1.3177   0.02344   0.01520  -0.0803   0.3413   1.0000
   8.500   1.3367   0.02423   0.01601  -0.0791   0.3212   1.0000
   8.750   1.3561   0.02509   0.01683  -0.0779   0.3028   1.0000
   9.000   1.3743   0.02605   0.01778  -0.0767   0.2848   1.0000
   9.250   1.3914   0.02705   0.01885  -0.0753   0.2673   1.0000
   9.500   1.4081   0.02810   0.01992  -0.0740   0.2508   1.0000
   9.750   1.4243   0.02920   0.02105  -0.0726   0.2353   1.0000
  10.000   1.4399   0.03037   0.02228  -0.0711   0.2207   1.0000
  10.250   1.4543   0.03159   0.02355  -0.0696   0.2069   1.0000
  10.500   1.4681   0.03289   0.02492  -0.0680   0.1941   1.0000
  10.750   1.4812   0.03425   0.02635  -0.0664   0.1821   1.0000
  11.000   1.4936   0.03564   0.02778  -0.0647   0.1708   1.0000
  11.250   1.5076   0.03709   0.02918  -0.0634   0.1599   1.0000
  11.500   1.5097   0.03842   0.03075  -0.0606   0.1504   1.0000
  11.750   1.5096   0.03986   0.03233  -0.0577   0.1414   1.0000
  12.000   1.5084   0.04118   0.03364  -0.0551   0.1323   1.0000
  12.250   1.4991   0.04281   0.03548  -0.0523   0.1243   1.0000
  12.500   1.4912   0.04480   0.03758  -0.0503   0.1162   1.0000
  12.750   1.4845   0.04688   0.03964  -0.0489   0.1081   1.0000
  13.000   1.4759   0.04966   0.04272  -0.0478   0.1007   1.0000
  13.250   1.4697   0.05254   0.04563  -0.0470   0.0932   1.0000
  13.500   1.4602   0.05594   0.04920  -0.0467   0.0855   1.0000
  13.750   1.4488   0.05995   0.05337  -0.0467   0.0772   1.0000
  14.000   1.4358   0.06432   0.05773  -0.0470   0.0693   1.0000
  14.250   1.4207   0.06924   0.06276  -0.0479   0.0617   1.0000
  14.500   1.4064   0.07456   0.06822  -0.0489   0.0548   1.0000
  14.750   1.3968   0.07918   0.07269  -0.0497   0.0492   1.0000
  15.000   1.3843   0.08487   0.07872  -0.0514   0.0455   1.0000
  15.250   1.3761   0.08984   0.08378  -0.0530   0.0422   1.0000
  15.500   1.3726   0.09409   0.08799  -0.0535   0.0392   1.0000
  15.750   1.3636   0.09975   0.09395  -0.0554   0.0377   1.0000
  16.000   1.3541   0.10561   0.10007  -0.0576   0.0365   1.0000
  16.250   1.3443   0.11166   0.10634  -0.0601   0.0355   1.0000
  16.500   1.3331   0.11814   0.11304  -0.0632   0.0348   1.0000
  16.750   1.3198   0.12524   0.12036  -0.0670   0.0344   1.0000
  17.000   1.3028   0.13351   0.12886  -0.0718   0.0344   1.0000
  17.250   1.2803   0.14361   0.13921  -0.0783   0.0350   1.0000
  17.500   1.2485   0.15689   0.15273  -0.0874   0.0366   1.0000
  17.750   1.2179   0.17088   0.16684  -0.0968   0.0383   1.0000
  18.000   1.1948   0.18364   0.17962  -0.1048   0.0395   1.0000
  18.250   1.1222   0.22499   0.22058  -0.1281   0.0560   1.0000
  18.500   1.1247   0.23152   0.22708  -0.1315   0.0570   1.0000
  18.750   1.1304   0.23707   0.23263  -0.1339   0.0582   1.0000
  19.000   1.1390   0.24204   0.23761  -0.1354   0.0591   1.0000
  19.250   0.8664   0.24163   0.23795  -0.1223   0.0917   1.0000
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