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RAF 6 AIRFOIL (raf6-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RAF 6 AIRFOIL (raf6-il)
Reynolds number: 500,000
Max Cl/Cd: 90.47 at α=0.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf6-il-500000.txt
Download as CSV file: xf-raf6-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 6 AIRFOIL                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3863   0.09972   0.09755  -0.0246   1.0000   0.0167
  -8.500  -0.3968   0.09693   0.09480  -0.0248   1.0000   0.0169
  -8.250  -0.4101   0.09450   0.09242  -0.0240   1.0000   0.0169
  -8.000  -0.4095   0.09021   0.08816  -0.0289   0.9974   0.0170
  -7.750  -0.3847   0.08276   0.08067  -0.0413   0.9931   0.0170
  -7.500  -0.3732   0.07754   0.07545  -0.0447   0.9898   0.0173
  -7.250  -0.3544   0.07396   0.07185  -0.0478   0.9874   0.0176
  -7.000  -0.3311   0.06969   0.06754  -0.0534   0.9853   0.0180
  -6.750  -0.3111   0.06533   0.06312  -0.0583   0.9800   0.0185
  -6.500  -0.2849   0.06041   0.05812  -0.0644   0.9764   0.0193
  -6.250  -0.2415   0.05275   0.05009  -0.0741   0.9736   0.0213
  -6.000  -0.2245   0.04696   0.04407  -0.0761   0.9664   0.0215
  -5.750  -0.2014   0.04366   0.04074  -0.0785   0.9638   0.0220
  -5.500  -0.1726   0.04083   0.03783  -0.0812   0.9620   0.0225
  -5.250  -0.1402   0.03782   0.03467  -0.0841   0.9607   0.0233
  -5.000  -0.1185   0.03506   0.03172  -0.0839   0.9528   0.0246
  -4.750  -0.0822   0.03040   0.02638  -0.0849   0.9499   0.0270
  -4.500  -0.0511   0.02744   0.02339  -0.0874   0.9484   0.0279
  -4.250  -0.0233   0.02573   0.02160  -0.0881   0.9435   0.0291
  -4.000   0.0080   0.02392   0.01956  -0.0886   0.9386   0.0316
  -2.750   0.1668   0.01267   0.00675  -0.0896   0.9088   0.0282
  -2.500   0.1990   0.01202   0.00608  -0.0904   0.8987   0.0300
  -2.250   0.2334   0.01119   0.00516  -0.0914   0.8904   0.0313
  -2.000   0.2648   0.01064   0.00453  -0.0919   0.8802   0.0328
  -1.750   0.2950   0.00993   0.00377  -0.0923   0.8690   0.0355
  -1.500   0.3253   0.00959   0.00338  -0.0927   0.8566   0.0382
  -1.250   0.3546   0.00933   0.00305  -0.0928   0.8439   0.0410
  -1.000   0.3826   0.00901   0.00266  -0.0926   0.8319   0.0452
  -0.750   0.4100   0.00886   0.00245  -0.0924   0.8196   0.0503
  -0.500   0.4366   0.00871   0.00224  -0.0919   0.8067   0.0573
  -0.250   0.4629   0.00857   0.00208  -0.0914   0.7926   0.0729
   0.000   0.4686   0.00628   0.00223  -0.0871   0.7800   0.8801
   0.250   0.5545   0.00647   0.00235  -0.0989   0.7576   0.9986
   0.500   0.5819   0.00654   0.00231  -0.0988   0.7340   1.0000
   0.750   0.6025   0.00666   0.00225  -0.0971   0.6995   1.0000
   1.000   0.6192   0.00693   0.00222  -0.0946   0.6400   1.0000
   1.250   0.6318   0.00744   0.00229  -0.0913   0.5576   1.0000
   1.500   0.6458   0.00797   0.00243  -0.0885   0.4865   1.0000
   1.750   0.6635   0.00837   0.00257  -0.0864   0.4411   1.0000
   2.000   0.6830   0.00871   0.00270  -0.0847   0.4081   1.0000
   2.250   0.7033   0.00901   0.00283  -0.0832   0.3782   1.0000
   2.500   0.7244   0.00930   0.00296  -0.0819   0.3489   1.0000
   2.750   0.7459   0.00959   0.00310  -0.0806   0.3220   1.0000
   3.000   0.7678   0.00988   0.00325  -0.0795   0.3003   1.0000
   3.250   0.7905   0.01015   0.00341  -0.0785   0.2835   1.0000
   3.500   0.8133   0.01043   0.00359  -0.0775   0.2705   1.0000
   3.750   0.8368   0.01067   0.00376  -0.0767   0.2603   1.0000
   4.000   0.8605   0.01091   0.00396  -0.0759   0.2526   1.0000
   4.250   0.8841   0.01116   0.00415  -0.0752   0.2453   1.0000
   4.500   0.9079   0.01141   0.00438  -0.0744   0.2391   1.0000
   4.750   0.9321   0.01163   0.00458  -0.0738   0.2335   1.0000
   5.000   0.9550   0.01195   0.00484  -0.0729   0.2280   1.0000
   5.250   0.9796   0.01215   0.00507  -0.0723   0.2234   1.0000
   5.500   1.0038   0.01237   0.00530  -0.0717   0.2187   1.0000
   5.750   1.0267   0.01269   0.00558  -0.0709   0.2142   1.0000
   6.000   1.0504   0.01297   0.00586  -0.0702   0.2103   1.0000
   6.250   1.0748   0.01317   0.00611  -0.0696   0.2063   1.0000
   6.500   1.0982   0.01344   0.00638  -0.0689   0.2020   1.0000
   6.750   1.1199   0.01387   0.00677  -0.0679   0.1974   1.0000
   7.000   1.1444   0.01405   0.00703  -0.0674   0.1945   1.0000
   7.250   1.1681   0.01428   0.00731  -0.0668   0.1908   1.0000
   7.500   1.1909   0.01458   0.00762  -0.0660   0.1870   1.0000
   7.750   1.2122   0.01501   0.00803  -0.0650   0.1825   1.0000
   8.000   1.2367   0.01510   0.00821  -0.0645   0.1774   1.0000
   8.250   1.2590   0.01535   0.00845  -0.0636   0.1715   1.0000
   8.500   1.2808   0.01565   0.00879  -0.0627   0.1669   1.0000
   8.750   1.3032   0.01584   0.00905  -0.0619   0.1618   1.0000
   9.000   1.3229   0.01619   0.00937  -0.0606   0.1560   1.0000
   9.250   1.3449   0.01643   0.00969  -0.0597   0.1514   1.0000
   9.500   1.3655   0.01673   0.01001  -0.0586   0.1456   1.0000
   9.750   1.3855   0.01708   0.01040  -0.0575   0.1398   1.0000
  10.000   1.4061   0.01740   0.01076  -0.0564   0.1332   1.0000
  10.250   1.4254   0.01779   0.01117  -0.0552   0.1257   1.0000
  10.500   1.4438   0.01827   0.01163  -0.0539   0.1150   1.0000
  10.750   1.4605   0.01888   0.01219  -0.0524   0.0987   1.0000
  11.000   1.4662   0.02035   0.01334  -0.0494   0.0598   1.0000
  11.250   1.4619   0.02255   0.01530  -0.0450   0.0267   1.0000
  11.500   1.4692   0.02385   0.01667  -0.0422   0.0228   1.0000
  11.750   1.4789   0.02493   0.01787  -0.0399   0.0207   1.0000
  12.000   1.4874   0.02609   0.01914  -0.0375   0.0192   1.0000
  12.250   1.4911   0.02761   0.02077  -0.0347   0.0178   1.0000
  12.500   1.4913   0.02940   0.02271  -0.0318   0.0168   1.0000
  12.750   1.4977   0.03077   0.02420  -0.0297   0.0162   1.0000
  13.000   1.5013   0.03240   0.02596  -0.0275   0.0155   1.0000
  13.250   1.5029   0.03426   0.02794  -0.0255   0.0149   1.0000
  13.500   1.5020   0.03643   0.03023  -0.0236   0.0144   1.0000
  13.750   1.4982   0.03899   0.03292  -0.0219   0.0140   1.0000
  14.000   1.4895   0.04220   0.03625  -0.0204   0.0136   1.0000
  14.250   1.4750   0.04624   0.04045  -0.0194   0.0133   1.0000
  14.500   1.4570   0.05108   0.04545  -0.0190   0.0130   1.0000
  14.750   1.4505   0.05494   0.04946  -0.0193   0.0128   1.0000
  15.000   1.4421   0.05936   0.05403  -0.0202   0.0126   1.0000
  15.250   1.4312   0.06449   0.05931  -0.0217   0.0125   1.0000
  15.500   1.4178   0.07034   0.06532  -0.0239   0.0123   1.0000
  15.750   1.4024   0.07674   0.07188  -0.0265   0.0122   1.0000
  16.000   1.3855   0.08354   0.07884  -0.0292   0.0121   1.0000
  16.250   1.3680   0.09040   0.08583  -0.0320   0.0121   1.0000
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