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RAF-48 AIRFOIL (raf48-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: RAF-48 AIRFOIL (raf48-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.79 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf48-il-1000000.txt
Download as CSV file: xf-raf48-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF-48 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.250  -1.0020   0.08607   0.08308  -0.0509   1.0000   0.0176
 -18.000  -1.0334   0.07764   0.07452  -0.0557   1.0000   0.0177
 -17.750  -1.0621   0.06971   0.06646  -0.0604   1.0000   0.0177
 -17.500  -1.0960   0.06103   0.05763  -0.0656   1.0000   0.0176
 -17.250  -1.1190   0.05383   0.05028  -0.0703   1.0000   0.0177
 -17.000  -1.1282   0.04877   0.04508  -0.0736   1.0000   0.0179
 -16.750  -1.1453   0.04296   0.03912  -0.0773   1.0000   0.0179
 -16.500  -1.1590   0.03819   0.03422  -0.0800   1.0000   0.0181
 -16.250  -1.1695   0.03438   0.03030  -0.0814   1.0000   0.0183
 -16.000  -1.1717   0.03182   0.02766  -0.0817   1.0000   0.0187
 -15.750  -1.1710   0.02978   0.02555  -0.0813   1.0000   0.0189
 -15.500  -1.1646   0.02835   0.02406  -0.0806   1.0000   0.0192
 -15.250  -1.1587   0.02703   0.02267  -0.0796   1.0000   0.0196
 -15.000  -1.1496   0.02603   0.02161  -0.0784   1.0000   0.0199
 -14.750  -1.1430   0.02496   0.02047  -0.0767   1.0000   0.0203
 -14.500  -1.1324   0.02420   0.01964  -0.0751   1.0000   0.0207
 -14.250  -1.1215   0.02351   0.01888  -0.0732   1.0000   0.0210
 -14.000  -1.1173   0.02260   0.01789  -0.0704   1.0000   0.0213
 -13.750  -1.1176   0.02165   0.01689  -0.0666   1.0000   0.0217
 -13.500  -1.1141   0.02103   0.01624  -0.0628   1.0000   0.0222
 -13.250  -1.1087   0.02056   0.01575  -0.0592   1.0000   0.0226
 -13.000  -1.0988   0.02009   0.01525  -0.0563   1.0000   0.0231
 -12.500  -1.0528   0.01902   0.01409  -0.0556   0.9968   0.0242
 -12.250  -1.0219   0.01862   0.01362  -0.0566   0.9875   0.0247
 -12.000  -0.9953   0.01759   0.01254  -0.0573   0.9753   0.0256
 -11.750  -0.9584   0.01696   0.01190  -0.0598   0.9655   0.0265
 -11.500  -0.9140   0.01642   0.01132  -0.0637   0.9568   0.0275
 -11.250  -0.8672   0.01587   0.01070  -0.0681   0.9451   0.0285
 -11.000  -0.8239   0.01536   0.01008  -0.0717   0.9282   0.0292
 -10.750  -0.7989   0.01471   0.00932  -0.0717   0.9061   0.0304
 -10.500  -0.7771   0.01445   0.00898  -0.0707   0.8886   0.0313
 -10.250  -0.7565   0.01418   0.00863  -0.0693   0.8731   0.0321
 -10.000  -0.7356   0.01393   0.00830  -0.0680   0.8588   0.0328
  -9.750  -0.7138   0.01372   0.00800  -0.0668   0.8459   0.0335
  -9.500  -0.6948   0.01330   0.00750  -0.0652   0.8334   0.0344
  -9.250  -0.6747   0.01294   0.00709  -0.0637   0.8211   0.0356
  -9.000  -0.6522   0.01270   0.00680  -0.0627   0.8097   0.0367
  -8.750  -0.6296   0.01247   0.00649  -0.0616   0.7991   0.0377
  -8.500  -0.6061   0.01229   0.00624  -0.0607   0.7889   0.0386
  -8.250  -0.5841   0.01196   0.00585  -0.0596   0.7792   0.0399
  -8.000  -0.5620   0.01168   0.00552  -0.0584   0.7692   0.0415
  -7.750  -0.5381   0.01145   0.00525  -0.0576   0.7610   0.0429
  -7.500  -0.5139   0.01128   0.00502  -0.0568   0.7524   0.0444
  -7.250  -0.4901   0.01102   0.00472  -0.0559   0.7449   0.0462
  -7.000  -0.4665   0.01077   0.00444  -0.0551   0.7376   0.0487
  -6.750  -0.4418   0.01060   0.00422  -0.0543   0.7314   0.0509
  -6.500  -0.4172   0.01035   0.00397  -0.0536   0.7261   0.0542
  -6.250  -0.3926   0.01013   0.00375  -0.0529   0.7206   0.0581
  -6.000  -0.3682   0.00994   0.00353  -0.0521   0.7150   0.0632
  -5.750  -0.3429   0.00972   0.00334  -0.0516   0.7104   0.0697
  -5.500  -0.3181   0.00949   0.00315  -0.0509   0.7054   0.0798
  -5.250  -0.2933   0.00930   0.00299  -0.0502   0.7005   0.0921
  -5.000  -0.2677   0.00915   0.00286  -0.0497   0.6961   0.1030
  -4.750  -0.2419   0.00898   0.00274  -0.0492   0.6914   0.1134
  -4.500  -0.2161   0.00884   0.00261  -0.0487   0.6863   0.1228
  -4.250  -0.1902   0.00875   0.00250  -0.0482   0.6812   0.1311
  -4.000  -0.1641   0.00861   0.00240  -0.0477   0.6770   0.1416
  -3.750  -0.1379   0.00847   0.00230  -0.0473   0.6723   0.1520
  -3.500  -0.1117   0.00837   0.00220  -0.0469   0.6675   0.1621
  -3.250  -0.0859   0.00827   0.00211  -0.0463   0.6626   0.1755
  -3.000  -0.0598   0.00811   0.00203  -0.0459   0.6578   0.1920
  -2.750  -0.0342   0.00796   0.00194  -0.0454   0.6524   0.2131
  -2.500  -0.0090   0.00783   0.00187  -0.0447   0.6470   0.2375
  -2.250   0.0169   0.00768   0.00181  -0.0443   0.6421   0.2638
  -2.000   0.0426   0.00754   0.00175  -0.0438   0.6366   0.2910
  -1.750   0.0673   0.00738   0.00168  -0.0430   0.6310   0.3268
  -1.500   0.0915   0.00716   0.00163  -0.0423   0.6255   0.3740
  -1.250   0.1153   0.00693   0.00158  -0.0414   0.6189   0.4316
  -1.000   0.1387   0.00676   0.00154  -0.0404   0.6123   0.4850
  -0.750   0.1630   0.00657   0.00150  -0.0396   0.6057   0.5326
  -0.500   0.1859   0.00639   0.00148  -0.0385   0.5986   0.5875
  -0.250   0.2085   0.00623   0.00148  -0.0373   0.5916   0.6448
   0.000   0.2314   0.00611   0.00149  -0.0361   0.5831   0.6933
   0.250   0.2548   0.00604   0.00150  -0.0350   0.5747   0.7315
   0.500   0.2786   0.00600   0.00152  -0.0339   0.5648   0.7623
   0.750   0.3031   0.00598   0.00155  -0.0330   0.5553   0.7901
   1.000   0.3270   0.00599   0.00159  -0.0320   0.5444   0.8151
   1.250   0.3518   0.00601   0.00163  -0.0312   0.5325   0.8372
   1.500   0.3769   0.00604   0.00167  -0.0305   0.5207   0.8564
   1.750   0.4024   0.00609   0.00171  -0.0299   0.5086   0.8749
   2.000   0.4302   0.00615   0.00177  -0.0298   0.4952   0.8948
   2.250   0.4714   0.00624   0.00187  -0.0327   0.4807   0.9171
   2.500   0.5200   0.00639   0.00200  -0.0373   0.4676   0.9298
   2.750   0.5697   0.00655   0.00211  -0.0421   0.4566   0.9378
   3.250   0.6469   0.00691   0.00241  -0.0467   0.4392   0.9568
   3.750   0.7116   0.00729   0.00272  -0.0486   0.4240   0.9724
   4.000   0.7467   0.00747   0.00286  -0.0502   0.4169   0.9772
   4.250   0.7771   0.00764   0.00301  -0.0508   0.4111   0.9828
   4.500   0.8146   0.00776   0.00312  -0.0529   0.4043   0.9848
   4.750   0.8512   0.00793   0.00325  -0.0549   0.3980   0.9876
   5.000   0.8876   0.00806   0.00339  -0.0568   0.3925   0.9908
   5.250   0.9231   0.00820   0.00353  -0.0585   0.3863   0.9936
   5.500   0.9601   0.00835   0.00364  -0.0607   0.3790   0.9956
   5.750   0.9964   0.00843   0.00373  -0.0627   0.3710   0.9975
   6.000   1.0318   0.00858   0.00384  -0.0645   0.3605   0.9994
   6.250   1.0581   0.00871   0.00395  -0.0644   0.3505   1.0000
   6.500   1.0778   0.00885   0.00407  -0.0629   0.3409   1.0000
   6.750   1.0970   0.00904   0.00421  -0.0613   0.3284   1.0000
   7.000   1.1160   0.00927   0.00438  -0.0596   0.3139   1.0000
   7.250   1.1343   0.00954   0.00459  -0.0579   0.2967   1.0000
   7.500   1.1512   0.00988   0.00483  -0.0559   0.2768   1.0000
   7.750   1.1662   0.01029   0.00514  -0.0536   0.2555   1.0000
   8.000   1.1808   0.01072   0.00547  -0.0513   0.2368   1.0000
   8.250   1.1951   0.01114   0.00581  -0.0489   0.2192   1.0000
   8.500   1.2095   0.01155   0.00615  -0.0465   0.2051   1.0000
   8.750   1.2231   0.01198   0.00651  -0.0440   0.1917   1.0000
   9.000   1.2364   0.01238   0.00687  -0.0414   0.1797   1.0000
   9.250   1.2499   0.01275   0.00721  -0.0389   0.1701   1.0000
   9.500   1.2570   0.01315   0.00757  -0.0352   0.1602   1.0000
   9.750   1.2644   0.01353   0.00793  -0.0315   0.1517   1.0000
  10.000   1.2739   0.01393   0.00832  -0.0284   0.1437   1.0000
  10.250   1.2817   0.01446   0.00880  -0.0252   0.1342   1.0000
  10.500   1.2919   0.01498   0.00930  -0.0225   0.1256   1.0000
  10.750   1.3009   0.01560   0.00989  -0.0199   0.1160   1.0000
  11.000   1.3088   0.01636   0.01060  -0.0173   0.1055   1.0000
  11.250   1.3152   0.01726   0.01145  -0.0147   0.0928   1.0000
  11.500   1.3161   0.01855   0.01263  -0.0118   0.0752   1.0000
  11.750   1.3150   0.02010   0.01406  -0.0090   0.0586   1.0000
  12.000   1.3179   0.02152   0.01545  -0.0068   0.0500   1.0000
  12.250   1.3255   0.02273   0.01667  -0.0052   0.0457   1.0000
  12.500   1.3320   0.02407   0.01802  -0.0038   0.0423   1.0000
  12.750   1.3409   0.02530   0.01929  -0.0026   0.0400   1.0000
  13.000   1.3471   0.02678   0.02078  -0.0013   0.0379   1.0000
  13.250   1.3541   0.02824   0.02228  -0.0003   0.0361   1.0000
  13.500   1.3623   0.02964   0.02373   0.0007   0.0348   1.0000
  13.750   1.3691   0.03120   0.02532   0.0016   0.0336   1.0000
  14.000   1.3729   0.03304   0.02720   0.0025   0.0321   1.0000
  14.250   1.3770   0.03488   0.02910   0.0033   0.0310   1.0000
  14.500   1.3840   0.03653   0.03082   0.0039   0.0303   1.0000
  14.750   1.3902   0.03830   0.03263   0.0045   0.0291   1.0000
  15.000   1.3924   0.04048   0.03486   0.0050   0.0284   1.0000
  15.250   1.3936   0.04284   0.03727   0.0055   0.0275   1.0000
  15.500   1.3932   0.04544   0.03993   0.0058   0.0266   1.0000
  15.750   1.3988   0.04746   0.04202   0.0060   0.0259   1.0000
  16.000   1.4019   0.04978   0.04441   0.0061   0.0253   1.0000
  16.250   1.4035   0.05233   0.04702   0.0061   0.0245   1.0000
  16.500   1.4036   0.05512   0.04985   0.0060   0.0238   1.0000
  16.750   1.3996   0.05842   0.05321   0.0058   0.0231   1.0000
  17.000   1.3938   0.06203   0.05689   0.0054   0.0225   1.0000
  17.250   1.3950   0.06486   0.05981   0.0051   0.0221   1.0000
  17.500   1.3958   0.06777   0.06279   0.0046   0.0217   1.0000
  17.750   1.3957   0.07082   0.06591   0.0041   0.0210   1.0000
  18.000   1.3924   0.07430   0.06946   0.0034   0.0206   1.0000
  18.250   1.3867   0.07818   0.07340   0.0026   0.0201   1.0000
  18.500   1.3799   0.08225   0.07754   0.0016   0.0197   1.0000
  18.750   1.3693   0.08689   0.08226   0.0004   0.0193   1.0000
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