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RAF 30 AIRFOIL (raf30-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RAF 30 AIRFOIL (raf30-il)
Reynolds number: 50,000
Max Cl/Cd: 28.69 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-raf30-il-50000-n5.txt
Download as CSV file: xf-raf30-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 30 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7104   0.09903   0.09116  -0.0247   1.0000   0.0704
 -12.500  -0.7516   0.08711   0.07918  -0.0323   1.0000   0.0694
 -12.250  -0.7924   0.07759   0.06953  -0.0381   1.0000   0.0684
 -12.000  -0.8255   0.07074   0.06248  -0.0412   1.0000   0.0679
 -11.750  -0.8503   0.06569   0.05722  -0.0422   1.0000   0.0679
 -11.500  -0.8696   0.06162   0.05293  -0.0417   1.0000   0.0682
 -11.250  -0.8847   0.05819   0.04926  -0.0403   1.0000   0.0689
 -11.000  -0.8955   0.05516   0.04597  -0.0380   1.0000   0.0696
 -10.750  -0.9021   0.05233   0.04285  -0.0355   1.0000   0.0705
 -10.500  -0.9036   0.04958   0.03974  -0.0332   1.0000   0.0719
 -10.250  -0.8996   0.04713   0.03699  -0.0312   1.0000   0.0739
 -10.000  -0.8862   0.04536   0.03524  -0.0300   1.0000   0.0765
  -9.750  -0.8742   0.04351   0.03324  -0.0286   1.0000   0.0794
  -9.500  -0.8594   0.04151   0.03097  -0.0272   1.0000   0.0821
  -9.250  -0.8415   0.03957   0.02870  -0.0260   1.0000   0.0851
  -9.000  -0.8237   0.03798   0.02713  -0.0249   1.0000   0.0889
  -8.750  -0.8078   0.03660   0.02567  -0.0235   1.0000   0.0941
  -8.500  -0.7890   0.03515   0.02403  -0.0223   1.0000   0.1000
  -8.250  -0.7729   0.03377   0.02270  -0.0208   1.0000   0.1059
  -8.000  -0.7562   0.03243   0.02124  -0.0191   1.0000   0.1141
  -7.750  -0.7440   0.03113   0.01999  -0.0171   1.0000   0.1249
  -7.500  -0.7327   0.02985   0.01878  -0.0149   1.0000   0.1391
  -7.250  -0.7224   0.02857   0.01762  -0.0125   1.0000   0.1581
  -7.000  -0.7129   0.02737   0.01657  -0.0100   1.0000   0.1799
  -6.750  -0.7028   0.02631   0.01567  -0.0075   1.0000   0.2076
  -6.500  -0.6926   0.02538   0.01491  -0.0050   1.0000   0.2414
  -6.250  -0.6834   0.02453   0.01430  -0.0022   1.0000   0.2845
  -6.000  -0.6744   0.02378   0.01381   0.0007   1.0000   0.3308
  -5.500  -0.6508   0.02269   0.01306   0.0064   1.0000   0.4111
  -5.250  -0.6363   0.02230   0.01275   0.0090   1.0000   0.4443
  -5.000  -0.6210   0.02199   0.01249   0.0114   1.0000   0.4751
  -4.750  -0.6056   0.02174   0.01227   0.0139   1.0000   0.5048
  -4.500  -0.5902   0.02154   0.01206   0.0163   1.0000   0.5335
  -4.250  -0.5753   0.02136   0.01188   0.0189   1.0000   0.5619
  -4.000  -0.5597   0.02127   0.01182   0.0214   1.0000   0.5891
  -3.750  -0.5444   0.02123   0.01180   0.0240   1.0000   0.6163
  -3.500  -0.5298   0.02119   0.01175   0.0267   1.0000   0.6432
  -3.250  -0.5138   0.02120   0.01177   0.0291   1.0000   0.6680
  -3.000  -0.4983   0.02119   0.01174   0.0315   1.0000   0.6911
  -2.750  -0.4815   0.02121   0.01173   0.0336   1.0000   0.7115
  -2.500  -0.4578   0.02125   0.01173   0.0342   0.9967   0.7325
  -2.250  -0.4188   0.02138   0.01177   0.0318   0.9863   0.7542
  -2.000  -0.3785   0.02154   0.01186   0.0295   0.9762   0.7734
  -1.750  -0.3382   0.02168   0.01194   0.0271   0.9661   0.7921
  -1.500  -0.2960   0.02183   0.01202   0.0243   0.9563   0.8100
  -1.250  -0.2519   0.02198   0.01212   0.0213   0.9467   0.8273
  -1.000  -0.2088   0.02211   0.01221   0.0184   0.9362   0.8438
  -0.750  -0.1583   0.02228   0.01233   0.0142   0.9277   0.8592
  -0.500  -0.1083   0.02242   0.01244   0.0100   0.9178   0.8736
  -0.250  -0.0556   0.02252   0.01253   0.0053   0.9082   0.8869
   0.000   0.0000   0.02253   0.01253   0.0000   0.8990   0.8990
   0.250   0.0557   0.02252   0.01253  -0.0053   0.8869   0.9083
   0.500   0.1083   0.02242   0.01244  -0.0100   0.8736   0.9178
   0.750   0.1583   0.02228   0.01233  -0.0141   0.8592   0.9276
   1.000   0.2087   0.02211   0.01220  -0.0184   0.8437   0.9362
   1.250   0.2519   0.02198   0.01211  -0.0213   0.8272   0.9467
   1.500   0.2960   0.02183   0.01201  -0.0243   0.8099   0.9563
   1.750   0.3382   0.02168   0.01194  -0.0271   0.7920   0.9660
   2.000   0.3785   0.02154   0.01186  -0.0295   0.7734   0.9762
   2.250   0.4188   0.02138   0.01177  -0.0318   0.7542   0.9863
   2.500   0.4578   0.02125   0.01172  -0.0342   0.7326   0.9967
   2.750   0.4815   0.02121   0.01173  -0.0336   0.7115   1.0000
   3.000   0.4983   0.02119   0.01173  -0.0315   0.6910   1.0000
   3.250   0.5139   0.02120   0.01177  -0.0291   0.6680   1.0000
   3.500   0.5298   0.02119   0.01175  -0.0267   0.6432   1.0000
   3.750   0.5444   0.02123   0.01180  -0.0240   0.6163   1.0000
   4.000   0.5598   0.02127   0.01182  -0.0214   0.5891   1.0000
   4.250   0.5753   0.02136   0.01188  -0.0189   0.5618   1.0000
   4.500   0.5902   0.02153   0.01206  -0.0163   0.5334   1.0000
   4.750   0.6056   0.02174   0.01227  -0.0139   0.5047   1.0000
   5.000   0.6211   0.02199   0.01249  -0.0114   0.4751   1.0000
   5.250   0.6363   0.02230   0.01275  -0.0090   0.4442   1.0000
   5.500   0.6509   0.02269   0.01306  -0.0064   0.4111   1.0000
   5.750   0.6639   0.02317   0.01339  -0.0037   0.3743   1.0000
   6.000   0.6743   0.02378   0.01380  -0.0007   0.3304   1.0000
   6.250   0.6834   0.02453   0.01430   0.0022   0.2843   1.0000
   6.500   0.6926   0.02537   0.01491   0.0050   0.2413   1.0000
   6.750   0.7028   0.02631   0.01567   0.0075   0.2073   1.0000
   7.000   0.7129   0.02737   0.01659   0.0100   0.1798   1.0000
   7.250   0.7223   0.02858   0.01762   0.0125   0.1580   1.0000
   7.500   0.7328   0.02984   0.01878   0.0149   0.1393   1.0000
   7.750   0.7440   0.03113   0.02000   0.0171   0.1246   1.0000
   8.000   0.7563   0.03243   0.02124   0.0191   0.1141   1.0000
   8.250   0.7730   0.03377   0.02269   0.0207   0.1059   1.0000
   8.500   0.7892   0.03514   0.02402   0.0222   0.1001   1.0000
   8.750   0.8080   0.03660   0.02568   0.0235   0.0942   1.0000
   9.000   0.8240   0.03799   0.02714   0.0249   0.0890   1.0000
   9.250   0.8416   0.03956   0.02869   0.0260   0.0852   1.0000
   9.500   0.8595   0.04151   0.03096   0.0272   0.0822   1.0000
   9.750   0.8744   0.04352   0.03325   0.0285   0.0794   1.0000
  10.000   0.8864   0.04538   0.03526   0.0300   0.0765   1.0000
  10.250   0.8998   0.04715   0.03702   0.0312   0.0739   1.0000
  10.500   0.9035   0.04960   0.03976   0.0332   0.0719   1.0000
  10.750   0.9024   0.05232   0.04284   0.0354   0.0706   1.0000
  11.000   0.8961   0.05515   0.04596   0.0380   0.0697   1.0000
  11.250   0.8849   0.05819   0.04926   0.0402   0.0689   1.0000
  11.500   0.8700   0.06162   0.05293   0.0417   0.0682   1.0000
  11.750   0.8506   0.06569   0.05722   0.0421   0.0678   1.0000
  12.000   0.8259   0.07074   0.06248   0.0411   0.0678   1.0000
  12.250   0.7927   0.07765   0.06958   0.0380   0.0684   1.0000
  12.500   0.7523   0.08713   0.07920   0.0322   0.0694   1.0000
  12.750   0.7112   0.09905   0.09117   0.0246   0.0704   1.0000
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