Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

AS5048 (18%) (as5048-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: AS5048 (18%) (as5048-il)
Reynolds number: 500,000
Max Cl/Cd: 71.03 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-as5048-il-500000-n5.txt
Download as CSV file: xf-as5048-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AS5048 (18%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -0.7776   0.11328   0.11022  -0.0381   1.0000   0.0069
 -17.000  -0.8228   0.09972   0.09637  -0.0453   1.0000   0.0068
 -16.750  -0.8502   0.09074   0.08718  -0.0498   1.0000   0.0068
 -16.500  -0.8708   0.08349   0.07974  -0.0531   1.0000   0.0068
 -16.250  -0.8873   0.07736   0.07342  -0.0555   1.0000   0.0068
 -16.000  -0.9000   0.07217   0.06807  -0.0572   1.0000   0.0069
 -15.750  -0.9098   0.06764   0.06338  -0.0585   1.0000   0.0069
 -15.500  -0.9180   0.06356   0.05915  -0.0593   1.0000   0.0070
 -15.250  -0.9234   0.06004   0.05550  -0.0597   1.0000   0.0071
 -15.000  -0.9257   0.05654   0.05183  -0.0605   0.9996   0.0072
 -14.750  -0.9203   0.05306   0.04819  -0.0624   0.9957   0.0073
 -14.500  -0.9159   0.05009   0.04506  -0.0632   0.9389   0.0074
 -14.250  -0.8671   0.04542   0.04001  -0.0755   0.9066   0.0077
 -14.000  -0.8386   0.04275   0.03673  -0.0807   0.8109   0.0079
 -13.500  -0.8256   0.03951   0.03307  -0.0792   0.7771   0.0080
 -13.250  -0.8177   0.03798   0.03138  -0.0784   0.7687   0.0081
 -13.000  -0.8093   0.03646   0.02976  -0.0776   0.7626   0.0082
 -12.750  -0.7993   0.03511   0.02833  -0.0770   0.7571   0.0084
 -12.250  -0.7760   0.03273   0.02579  -0.0758   0.7488   0.0086
 -12.000  -0.7634   0.03160   0.02460  -0.0752   0.7451   0.0088
 -11.750  -0.7501   0.03054   0.02346  -0.0746   0.7416   0.0089
 -11.500  -0.7367   0.02950   0.02234  -0.0739   0.7383   0.0091
 -11.000  -0.7087   0.02751   0.02020  -0.0725   0.7329   0.0095
 -10.750  -0.6943   0.02652   0.01916  -0.0718   0.7306   0.0098
 -10.500  -0.6798   0.02557   0.01813  -0.0711   0.7283   0.0100
 -10.250  -0.6647   0.02466   0.01714  -0.0704   0.7261   0.0103
 -10.000  -0.6489   0.02381   0.01622  -0.0697   0.7240   0.0105
  -9.750  -0.6357   0.02277   0.01516  -0.0689   0.7220   0.0108
  -9.500  -0.6202   0.02192   0.01426  -0.0682   0.7201   0.0110
  -9.250  -0.6035   0.02116   0.01346  -0.0677   0.7183   0.0114
  -9.000  -0.5862   0.02044   0.01270  -0.0671   0.7166   0.0118
  -8.750  -0.5686   0.01973   0.01196  -0.0665   0.7148   0.0124
  -8.500  -0.5508   0.01907   0.01124  -0.0659   0.7129   0.0129
  -8.250  -0.5342   0.01836   0.01049  -0.0650   0.7111   0.0134
  -8.000  -0.5188   0.01765   0.00976  -0.0639   0.7095   0.0139
  -7.750  -0.5027   0.01711   0.00920  -0.0626   0.7078   0.0145
  -7.500  -0.4876   0.01667   0.00872  -0.0609   0.7063   0.0150
  -7.250  -0.4693   0.01625   0.00825  -0.0598   0.7048   0.0157
  -7.000  -0.4494   0.01585   0.00780  -0.0589   0.7033   0.0164
  -6.750  -0.4295   0.01543   0.00735  -0.0580   0.7018   0.0174
  -6.500  -0.4076   0.01510   0.00699  -0.0573   0.7002   0.0187
  -6.250  -0.3852   0.01477   0.00664  -0.0567   0.6988   0.0200
  -6.000  -0.3629   0.01441   0.00629  -0.0561   0.6975   0.0217
  -5.750  -0.3393   0.01412   0.00598  -0.0557   0.6961   0.0239
  -5.500  -0.3160   0.01380   0.00567  -0.0552   0.6948   0.0285
  -5.250  -0.2936   0.01340   0.00534  -0.0546   0.6933   0.0427
  -5.000  -0.2786   0.01244   0.00477  -0.0532   0.6917   0.1271
  -4.750  -0.2647   0.01130   0.00418  -0.0516   0.6901   0.2483
  -4.500  -0.2498   0.01008   0.00356  -0.0503   0.6885   0.3877
  -4.250  -0.2300   0.00923   0.00321  -0.0495   0.6872   0.5047
  -4.000  -0.2033   0.00910   0.00328  -0.0494   0.6859   0.5653
  -3.750  -0.1742   0.00915   0.00331  -0.0498   0.6844   0.5879
  -3.500  -0.1447   0.00923   0.00336  -0.0502   0.6829   0.6007
  -3.250  -0.1155   0.00929   0.00342  -0.0505   0.6816   0.6105
  -3.000  -0.0861   0.00936   0.00343  -0.0509   0.6801   0.6198
  -2.750  -0.0569   0.00941   0.00350  -0.0512   0.6783   0.6248
  -2.500  -0.0274   0.00944   0.00350  -0.0516   0.6765   0.6286
  -2.250   0.0021   0.00946   0.00348  -0.0520   0.6746   0.6321
  -2.000   0.0316   0.00948   0.00343  -0.0525   0.6727   0.6352
  -1.750   0.0611   0.00948   0.00341  -0.0529   0.6708   0.6376
  -1.500   0.0905   0.00950   0.00341  -0.0533   0.6690   0.6399
  -1.250   0.1200   0.00954   0.00343  -0.0537   0.6671   0.6425
  -1.000   0.1494   0.00957   0.00344  -0.0542   0.6649   0.6448
  -0.750   0.1783   0.00955   0.00343  -0.0545   0.6618   0.6469
  -0.500   0.2071   0.00952   0.00338  -0.0548   0.6580   0.6487
  -0.250   0.2361   0.00950   0.00333  -0.0551   0.6544   0.6504
   0.000   0.2654   0.00949   0.00328  -0.0555   0.6515   0.6521
   0.250   0.2947   0.00950   0.00326  -0.0559   0.6488   0.6536
   0.500   0.3234   0.00947   0.00327  -0.0562   0.6455   0.6548
   0.750   0.3521   0.00944   0.00328  -0.0565   0.6417   0.6561
   1.000   0.3809   0.00943   0.00327  -0.0568   0.6378   0.6576
   1.250   0.4096   0.00942   0.00326  -0.0570   0.6341   0.6590
   1.500   0.4381   0.00941   0.00326  -0.0573   0.6290   0.6603
   1.750   0.4660   0.00936   0.00323  -0.0573   0.6204   0.6617
   2.000   0.4938   0.00933   0.00320  -0.0574   0.6115   0.6632
   2.250   0.5218   0.00933   0.00319  -0.0575   0.6029   0.6649
   2.500   0.5500   0.00934   0.00320  -0.0577   0.5946   0.6664
   2.750   0.5776   0.00935   0.00320  -0.0577   0.5852   0.6678
   3.000   0.6051   0.00938   0.00321  -0.0578   0.5721   0.6690
   3.250   0.6314   0.00945   0.00322  -0.0576   0.5549   0.6702
   3.500   0.6567   0.00954   0.00326  -0.0571   0.5351   0.6715
   3.750   0.6812   0.00969   0.00335  -0.0566   0.5120   0.6729
   4.000   0.7042   0.00993   0.00349  -0.0558   0.4853   0.6743
   4.250   0.7264   0.01024   0.00368  -0.0548   0.4557   0.6756
   4.500   0.7487   0.01054   0.00389  -0.0540   0.4279   0.6769
   4.750   0.7709   0.01087   0.00412  -0.0531   0.4030   0.6783
   5.000   0.7927   0.01120   0.00437  -0.0521   0.3771   0.6797
   5.250   0.8137   0.01157   0.00463  -0.0511   0.3518   0.6811
   5.500   0.8344   0.01196   0.00491  -0.0500   0.3260   0.6827
   5.750   0.8549   0.01235   0.00520  -0.0489   0.3026   0.6844
   6.000   0.8759   0.01270   0.00548  -0.0479   0.2824   0.6859
   6.250   0.8962   0.01308   0.00578  -0.0467   0.2624   0.6871
   6.500   0.9160   0.01343   0.00609  -0.0455   0.2448   0.6884
   6.750   0.9356   0.01379   0.00641  -0.0443   0.2292   0.6898
   7.000   0.9543   0.01417   0.00675  -0.0429   0.2138   0.6912
   7.250   0.9708   0.01455   0.00709  -0.0410   0.1998   0.6926
   7.500   0.9866   0.01494   0.00745  -0.0391   0.1882   0.6941
   7.750   1.0034   0.01535   0.00784  -0.0374   0.1779   0.6956
   8.000   1.0221   0.01574   0.00824  -0.0361   0.1694   0.6973
   8.250   1.0393   0.01622   0.00870  -0.0347   0.1609   0.6991
   8.500   1.0580   0.01664   0.00914  -0.0335   0.1535   0.7010
   8.750   1.0744   0.01718   0.00965  -0.0320   0.1459   0.7027
   9.250   1.1074   0.01824   0.01074  -0.0292   0.1317   0.7057
   9.500   1.1246   0.01875   0.01131  -0.0281   0.1255   0.7073
   9.750   1.1391   0.01944   0.01199  -0.0266   0.1185   0.7090
  10.000   1.1549   0.02008   0.01268  -0.0255   0.1119   0.7108
  10.250   1.1681   0.02092   0.01351  -0.0241   0.1046   0.7127
  10.500   1.1829   0.02171   0.01434  -0.0231   0.0981   0.7146
  10.750   1.1955   0.02270   0.01533  -0.0220   0.0917   0.7166
  11.000   1.2094   0.02366   0.01631  -0.0212   0.0857   0.7185
  11.250   1.2214   0.02480   0.01745  -0.0202   0.0802   0.7204
  11.500   1.2350   0.02584   0.01854  -0.0195   0.0755   0.7225
  11.750   1.2462   0.02707   0.01980  -0.0187   0.0707   0.7247
  12.000   1.2591   0.02819   0.02098  -0.0180   0.0669   0.7272
  12.250   1.2704   0.02944   0.02227  -0.0173   0.0628   0.7298
  12.500   1.2808   0.03077   0.02364  -0.0165   0.0593   0.7323
  12.750   1.2921   0.03203   0.02495  -0.0158   0.0561   0.7348
  13.000   1.3012   0.03347   0.02641  -0.0150   0.0529   0.7373
  13.250   1.3107   0.03488   0.02789  -0.0143   0.0504   0.7399
  13.500   1.3203   0.03630   0.02938  -0.0136   0.0480   0.7429
  13.750   1.3283   0.03784   0.03098  -0.0129   0.0457   0.7462
  14.000   1.3347   0.03954   0.03274  -0.0121   0.0437   0.7497
  14.250   1.3433   0.04108   0.03436  -0.0115   0.0420   0.7534
  14.500   1.3504   0.04278   0.03615  -0.0109   0.0402   0.7574
  14.750   1.3561   0.04462   0.03807  -0.0103   0.0386   0.7624
  15.000   1.3601   0.04667   0.04019  -0.0098   0.0371   0.7681
  15.250   1.3669   0.04853   0.04217  -0.0094   0.0360   0.7752
  15.500   1.3729   0.05051   0.04428  -0.0092   0.0347   0.7850
  15.750   1.3772   0.05271   0.04661  -0.0089   0.0336   0.7986
  16.000   1.3801   0.05500   0.04907  -0.0087   0.0325   0.8238
  16.500   1.3610   0.05884   0.05331  -0.0027   0.0310   1.0000
  16.750   1.3644   0.06138   0.05595  -0.0029   0.0302   1.0000
  17.000   1.3666   0.06410   0.05875  -0.0031   0.0292   1.0000
  17.250   1.3667   0.06710   0.06183  -0.0035   0.0283   1.0000
  17.500   1.3653   0.07035   0.06515  -0.0040   0.0275   1.0000
  17.750   1.3621   0.07390   0.06878  -0.0047   0.0268   1.0000
  18.000   1.3576   0.07770   0.07267  -0.0055   0.0262   1.0000
  18.250   1.3555   0.08125   0.07633  -0.0063   0.0256   1.0000
  18.500   1.3517   0.08506   0.08025  -0.0074   0.0251   1.0000
  18.750   1.3465   0.08910   0.08440  -0.0085   0.0245   1.0000
  19.000   1.3401   0.09340   0.08880  -0.0099   0.0240   1.0000
  19.250   1.3325   0.09794   0.09344  -0.0115   0.0235   1.0000
<< Back to AS5048 (18%) (as5048-il)

Polar data table (+)

Polar graphs


<< Back to AS5048 (18%) (as5048-il)