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RAF 28 AIRFOIL (raf28-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RAF 28 AIRFOIL (raf28-il)
Reynolds number: 200,000
Max Cl/Cd: 69.45 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf28-il-200000.txt
Download as CSV file: xf-raf28-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 28 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4898   0.11569   0.11189  -0.0200   1.0000   0.0533
 -10.750  -0.5023   0.11101   0.10727  -0.0262   1.0000   0.0548
 -10.500  -0.5106   0.10618   0.10250  -0.0309   1.0000   0.0551
 -10.250  -0.4990   0.10193   0.09825  -0.0268   1.0000   0.0567
 -10.000  -0.4885   0.09967   0.09598  -0.0255   1.0000   0.0583
  -9.750  -0.4843   0.09667   0.09299  -0.0259   1.0000   0.0605
  -9.500  -0.4860   0.09280   0.08917  -0.0278   1.0000   0.0635
  -9.250  -0.4042   0.07904   0.07566  -0.0330   1.0000   0.0709
  -9.000  -0.4015   0.07596   0.07259  -0.0329   1.0000   0.0742
  -8.750  -0.4110   0.07126   0.06793  -0.0349   1.0000   0.0768
  -8.250  -0.5551   0.06659   0.06315  -0.0439   1.0000   0.0695
  -8.000  -0.5479   0.06460   0.06118  -0.0422   1.0000   0.0710
  -7.750  -0.5470   0.06183   0.05839  -0.0414   1.0000   0.0737
  -7.500  -0.5555   0.05750   0.05390  -0.0417   1.0000   0.0775
  -7.250  -0.5799   0.05213   0.04801  -0.0405   1.0000   0.0817
  -7.000  -0.5620   0.05000   0.04615  -0.0390   1.0000   0.0844
  -6.750  -0.5556   0.04786   0.04395  -0.0370   1.0000   0.0881
  -6.500  -0.5823   0.03422   0.02890  -0.0312   1.0000   0.0524
  -6.250  -0.5799   0.03024   0.02448  -0.0276   1.0000   0.0492
  -6.000  -0.5732   0.02672   0.02036  -0.0242   1.0000   0.0474
  -5.750  -0.5600   0.02526   0.01869  -0.0220   1.0000   0.0488
  -5.500  -0.5422   0.02384   0.01699  -0.0205   0.9995   0.0506
  -5.250  -0.5064   0.02180   0.01456  -0.0222   0.9956   0.0517
  -5.000  -0.4702   0.02055   0.01300  -0.0239   0.9913   0.0540
  -4.750  -0.4340   0.01917   0.01138  -0.0256   0.9869   0.0557
  -4.500  -0.3968   0.01766   0.00983  -0.0277   0.9835   0.0581
  -4.250  -0.3631   0.01690   0.00906  -0.0291   0.9773   0.0617
  -4.000  -0.3247   0.01617   0.00826  -0.0313   0.9726   0.0650
  -3.750  -0.2900   0.01542   0.00745  -0.0327   0.9666   0.0680
  -3.500  -0.2547   0.01462   0.00672  -0.0344   0.9605   0.0737
  -3.250  -0.2150   0.01397   0.00610  -0.0369   0.9562   0.0859
  -3.000  -0.1851   0.01301   0.00541  -0.0375   0.9478   0.1375
  -2.750  -0.1496   0.01175   0.00505  -0.0397   0.9434   0.3418
  -2.500  -0.1198   0.01118   0.00485  -0.0402   0.9348   0.4375
  -2.250  -0.0846   0.01044   0.00464  -0.0416   0.9299   0.5693
  -2.000  -0.0579   0.00990   0.00458  -0.0409   0.9210   0.6947
  -1.750  -0.0205   0.00947   0.00446  -0.0420   0.9157   0.7970
  -1.500   0.0454   0.00934   0.00451  -0.0486   0.9146   0.9026
  -1.250   0.1108   0.00948   0.00459  -0.0555   0.9110   0.9518
  -1.000   0.1749   0.00956   0.00457  -0.0624   0.9054   0.9741
  -0.750   0.2304   0.00946   0.00436  -0.0680   0.8977   0.9852
  -0.500   0.2836   0.00932   0.00413  -0.0732   0.8867   0.9950
  -0.250   0.3243   0.00920   0.00391  -0.0760   0.8730   1.0000
   0.000   0.3479   0.00918   0.00379  -0.0752   0.8572   1.0000
   0.250   0.3702   0.00921   0.00372  -0.0741   0.8419   1.0000
   0.500   0.3920   0.00926   0.00369  -0.0729   0.8270   1.0000
   0.750   0.4136   0.00933   0.00368  -0.0716   0.8124   1.0000
   1.000   0.4353   0.00940   0.00370  -0.0703   0.7982   1.0000
   1.250   0.4570   0.00949   0.00374  -0.0689   0.7841   1.0000
   1.500   0.4788   0.00956   0.00377  -0.0676   0.7698   1.0000
   1.750   0.5006   0.00962   0.00380  -0.0662   0.7552   1.0000
   2.000   0.5226   0.00967   0.00381  -0.0649   0.7399   1.0000
   2.250   0.5447   0.00970   0.00380  -0.0634   0.7236   1.0000
   2.500   0.5667   0.00974   0.00380  -0.0620   0.7064   1.0000
   2.750   0.5886   0.00980   0.00383  -0.0606   0.6884   1.0000
   3.000   0.6109   0.00989   0.00389  -0.0592   0.6704   1.0000
   3.250   0.6333   0.01000   0.00395  -0.0579   0.6526   1.0000
   3.500   0.6559   0.01016   0.00404  -0.0566   0.6349   1.0000
   3.750   0.6776   0.01031   0.00418  -0.0552   0.6141   1.0000
   4.000   0.6991   0.01049   0.00430  -0.0537   0.5918   1.0000
   4.250   0.7207   0.01066   0.00448  -0.0522   0.5701   1.0000
   4.500   0.7421   0.01084   0.00464  -0.0508   0.5475   1.0000
   4.750   0.7623   0.01103   0.00479  -0.0491   0.5181   1.0000
   5.000   0.7820   0.01126   0.00498  -0.0473   0.4834   1.0000
   5.250   0.8003   0.01158   0.00518  -0.0453   0.4408   1.0000
   5.500   0.8161   0.01207   0.00545  -0.0429   0.3793   1.0000
   5.750   0.8266   0.01298   0.00586  -0.0398   0.2779   1.0000
   6.000   0.8319   0.01454   0.00667  -0.0362   0.1546   1.0000
   6.250   0.8396   0.01609   0.00767  -0.0329   0.0754   1.0000
   6.500   0.8545   0.01703   0.00851  -0.0306   0.0587   1.0000
   6.750   0.8673   0.01813   0.00958  -0.0280   0.0516   1.0000
   7.000   0.8831   0.01899   0.01054  -0.0258   0.0481   1.0000
   7.250   0.8975   0.01998   0.01156  -0.0236   0.0442   1.0000
   7.500   0.9073   0.02171   0.01324  -0.0208   0.0409   1.0000
   7.750   0.9254   0.02273   0.01438  -0.0191   0.0395   1.0000
   8.000   0.9445   0.02399   0.01573  -0.0175   0.0380   1.0000
   8.250   0.9651   0.02543   0.01724  -0.0163   0.0363   1.0000
   8.500   0.9855   0.02685   0.01872  -0.0153   0.0344   1.0000
   8.750   1.0083   0.02923   0.02110  -0.0149   0.0323   1.0000
   9.000   1.0324   0.03270   0.02481  -0.0146   0.0317   1.0000
   9.250   1.0509   0.03625   0.02868  -0.0135   0.0315   1.0000
   9.500   1.0660   0.03898   0.03170  -0.0118   0.0315   1.0000
   9.750   1.0769   0.04211   0.03515  -0.0098   0.0315   1.0000
  10.000   1.0799   0.04317   0.03658  -0.0063   0.0308   1.0000
  10.250   1.0827   0.04623   0.03996  -0.0036   0.0308   1.0000
  10.500   1.0820   0.04944   0.04347  -0.0007   0.0308   1.0000
  10.750   1.0959   0.05183   0.04605   0.0009   0.0324   1.0000
  11.000   1.0443   0.05877   0.05385   0.0090   0.0393   1.0000
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