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S4320 (s4320-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S4320 (s4320-il)
Reynolds number: 200,000
Max Cl/Cd: 82.01 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4320-il-200000-n5.txt
Download as CSV file: xf-s4320-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2886   0.10435   0.10088  -0.0297   1.0000   0.0226
  -9.000  -0.2875   0.10129   0.09788  -0.0324   1.0000   0.0239
  -8.750  -0.2853   0.09830   0.09494  -0.0346   1.0000   0.0242
  -8.500  -0.1984   0.08082   0.07775  -0.0460   0.9567   0.0247
  -8.250  -0.1848   0.07634   0.07325  -0.0470   0.9429   0.0253
  -7.750  -0.1657   0.06887   0.06573  -0.0502   0.9112   0.0262
  -7.500  -0.1615   0.06526   0.06209  -0.0515   0.8951   0.0264
  -7.250  -0.1604   0.06150   0.05832  -0.0530   0.8798   0.0263
  -7.000  -0.2119   0.06826   0.06497  -0.0614   0.9102   0.0179
  -6.750  -0.1996   0.06466   0.06132  -0.0649   0.8931   0.0175
  -6.500  -0.1881   0.06018   0.05677  -0.0697   0.8765   0.0172
  -6.250  -0.1748   0.05529   0.05179  -0.0749   0.8621   0.0169
  -6.000  -0.1586   0.04973   0.04608  -0.0805   0.8494   0.0167
  -5.750  -0.1387   0.04225   0.03830  -0.0870   0.8384   0.0173
  -5.500  -0.1159   0.03317   0.02851  -0.0926   0.8282   0.0182
  -5.250  -0.0931   0.02863   0.02339  -0.0945   0.8193   0.0182
  -5.000  -0.0692   0.02480   0.01897  -0.0956   0.8110   0.0185
  -4.750  -0.0438   0.02228   0.01603  -0.0961   0.8024   0.0190
  -4.500  -0.0177   0.02071   0.01413  -0.0962   0.7948   0.0198
  -4.250   0.0091   0.01975   0.01297  -0.0963   0.7862   0.0214
  -4.000   0.0364   0.01843   0.01127  -0.0962   0.7790   0.0226
  -3.750   0.0641   0.01716   0.00968  -0.0960   0.7708   0.0232
  -3.500   0.0916   0.01617   0.00844  -0.0958   0.7639   0.0238
  -3.250   0.1192   0.01539   0.00746  -0.0955   0.7559   0.0244
  -3.000   0.1463   0.01452   0.00651  -0.0954   0.7491   0.0260
  -2.750   0.1738   0.01403   0.00598  -0.0953   0.7412   0.0280
  -2.500   0.2014   0.01354   0.00538  -0.0951   0.7345   0.0292
  -2.250   0.2292   0.01312   0.00487  -0.0950   0.7268   0.0305
  -2.000   0.2571   0.01281   0.00442  -0.0948   0.7202   0.0321
  -1.750   0.2851   0.01247   0.00404  -0.0948   0.7124   0.0353
  -1.500   0.3131   0.01224   0.00375  -0.0946   0.7058   0.0434
  -1.250   0.3411   0.01189   0.00350  -0.0946   0.6979   0.0749
  -1.000   0.3687   0.01154   0.00335  -0.0947   0.6913   0.1516
  -0.750   0.3962   0.01117   0.00330  -0.0948   0.6833   0.2562
  -0.500   0.4228   0.01071   0.00328  -0.0948   0.6764   0.4096
  -0.250   0.4450   0.00994   0.00339  -0.0935   0.6684   0.6780
   0.000   0.4727   0.00932   0.00324  -0.0925   0.6612   1.0000
   0.250   0.5007   0.00941   0.00318  -0.0924   0.6526   1.0000
   0.500   0.5286   0.00950   0.00313  -0.0923   0.6445   1.0000
   0.750   0.5565   0.00960   0.00310  -0.0921   0.6360   1.0000
   1.000   0.5843   0.00969   0.00310  -0.0921   0.6271   1.0000
   1.250   0.6119   0.00981   0.00308  -0.0919   0.6187   1.0000
   1.500   0.6396   0.00991   0.00312  -0.0918   0.6091   1.0000
   1.750   0.6672   0.01002   0.00315  -0.0917   0.6000   1.0000
   2.000   0.6946   0.01015   0.00318  -0.0915   0.5908   1.0000
   2.250   0.7221   0.01027   0.00326  -0.0914   0.5805   1.0000
   2.500   0.7494   0.01040   0.00333  -0.0912   0.5705   1.0000
   2.750   0.7766   0.01054   0.00341  -0.0910   0.5600   1.0000
   3.000   0.8037   0.01069   0.00350  -0.0908   0.5483   1.0000
   3.250   0.8306   0.01084   0.00361  -0.0906   0.5361   1.0000
   3.500   0.8574   0.01100   0.00373  -0.0904   0.5234   1.0000
   3.750   0.8841   0.01118   0.00389  -0.0902   0.5101   1.0000
   4.000   0.9105   0.01138   0.00404  -0.0899   0.4960   1.0000
   4.250   0.9367   0.01159   0.00420  -0.0896   0.4813   1.0000
   4.500   0.9627   0.01182   0.00441  -0.0893   0.4655   1.0000
   4.750   0.9884   0.01208   0.00461  -0.0889   0.4494   1.0000
   5.000   1.0137   0.01236   0.00484  -0.0885   0.4323   1.0000
   5.250   1.0388   0.01267   0.00510  -0.0881   0.4149   1.0000
   5.500   1.0637   0.01299   0.00540  -0.0877   0.3962   1.0000
   5.750   1.0881   0.01335   0.00571  -0.0873   0.3777   1.0000
   6.250   1.1359   0.01416   0.00643  -0.0862   0.3405   1.0000
   6.500   1.1592   0.01460   0.00685  -0.0856   0.3217   1.0000
   6.750   1.1821   0.01508   0.00728  -0.0850   0.3041   1.0000
   7.250   1.2268   0.01609   0.00823  -0.0837   0.2707   1.0000
   7.500   1.2487   0.01662   0.00877  -0.0829   0.2546   1.0000
   7.750   1.2701   0.01717   0.00931  -0.0822   0.2394   1.0000
   8.000   1.2910   0.01774   0.00989  -0.0813   0.2251   1.0000
   8.250   1.3114   0.01833   0.01049  -0.0805   0.2117   1.0000
   8.500   1.3311   0.01896   0.01113  -0.0795   0.1984   1.0000
   8.750   1.3500   0.01962   0.01182  -0.0784   0.1858   1.0000
   9.000   1.3678   0.02033   0.01254  -0.0772   0.1742   1.0000
   9.250   1.3854   0.02102   0.01327  -0.0760   0.1626   1.0000
   9.500   1.4019   0.02176   0.01405  -0.0747   0.1518   1.0000
   9.750   1.4168   0.02255   0.01489  -0.0732   0.1416   1.0000
  10.000   1.4285   0.02341   0.01578  -0.0712   0.1310   1.0000
  10.250   1.4378   0.02437   0.01674  -0.0690   0.1194   1.0000
  10.500   1.4463   0.02543   0.01779  -0.0669   0.1080   1.0000
  10.750   1.4555   0.02651   0.01890  -0.0651   0.0976   1.0000
  11.000   1.4638   0.02770   0.02014  -0.0633   0.0888   1.0000
  11.250   1.4706   0.02906   0.02153  -0.0616   0.0802   1.0000
  11.500   1.4757   0.03063   0.02310  -0.0600   0.0709   1.0000
  11.750   1.4814   0.03224   0.02474  -0.0586   0.0614   1.0000
  12.000   1.4855   0.03407   0.02661  -0.0573   0.0520   1.0000
  12.250   1.4891   0.03602   0.02860  -0.0562   0.0446   1.0000
  12.500   1.4910   0.03822   0.03085  -0.0552   0.0371   1.0000
  12.750   1.4907   0.04075   0.03340  -0.0542   0.0292   1.0000
  13.000   1.4883   0.04361   0.03629  -0.0535   0.0223   1.0000
  13.250   1.4839   0.04680   0.03954  -0.0530   0.0172   1.0000
  13.500   1.4787   0.05023   0.04305  -0.0527   0.0139   1.0000
  13.750   1.4742   0.05371   0.04666  -0.0527   0.0122   1.0000
  14.000   1.4692   0.05739   0.05048  -0.0529   0.0111   1.0000
  14.250   1.4617   0.06155   0.05477  -0.0534   0.0102   1.0000
  14.500   1.4549   0.06581   0.05918  -0.0542   0.0096   1.0000
  14.750   1.4485   0.07020   0.06374  -0.0553   0.0091   1.0000
  15.000   1.4407   0.07499   0.06870  -0.0566   0.0086   1.0000
  15.250   1.4321   0.08008   0.07395  -0.0583   0.0082   1.0000
  15.500   1.4222   0.08560   0.07965  -0.0603   0.0079   1.0000
  15.750   1.4112   0.09151   0.08574  -0.0627   0.0077   1.0000
  16.000   1.3976   0.09809   0.09248  -0.0655   0.0074   1.0000
  16.250   1.3848   0.10478   0.09934  -0.0686   0.0073   1.0000
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