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

NACA 63(3)-618 (naca633618-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 63(3)-618 (naca633618-il)
Reynolds number: 200,000
Max Cl/Cd: 73.97 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca633618-il-200000.txt
Download as CSV file: xf-naca633618-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63(3)-618                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.4860   0.10327   0.09932  -0.0697   1.0000   0.0495
 -14.500  -0.5245   0.09132   0.08732  -0.0759   1.0000   0.0486
 -14.250  -0.6090   0.07409   0.06983  -0.0869   1.0000   0.0463
 -13.750  -0.7617   0.05403   0.04882  -0.0962   1.0000   0.0439
 -13.500  -0.7664   0.05174   0.04651  -0.0954   1.0000   0.0444
 -13.250  -0.7697   0.05003   0.04481  -0.0939   1.0000   0.0449
 -13.000  -0.7804   0.04897   0.04378  -0.0911   1.0000   0.0455
 -12.750  -0.8302   0.04783   0.04252  -0.0845   0.9990   0.0449
 -12.500  -0.8049   0.04559   0.04020  -0.0886   0.9933   0.0464
 -12.250  -0.7926   0.04260   0.03690  -0.0927   0.9840   0.0478
 -12.000  -0.7825   0.03955   0.03339  -0.0962   0.9728   0.0491
 -11.750  -0.7543   0.03660   0.03024  -0.0996   0.9687   0.0508
 -11.500  -0.7262   0.03507   0.02868  -0.1014   0.9615   0.0525
 -11.250  -0.6946   0.03328   0.02669  -0.1044   0.9567   0.0548
 -11.000  -0.6650   0.03132   0.02440  -0.1072   0.9517   0.0573
 -10.750  -0.6338   0.02993   0.02309  -0.1086   0.9451   0.0595
 -10.500  -0.6001   0.02864   0.02167  -0.1110   0.9399   0.0624
 -10.250  -0.5749   0.02765   0.02041  -0.1119   0.9316   0.0647
 -10.000  -0.5413   0.02613   0.01901  -0.1132   0.9259   0.0677
  -9.750  -0.5093   0.02516   0.01796  -0.1148   0.9203   0.0709
  -9.500  -0.4897   0.02452   0.01716  -0.1139   0.9095   0.0733
  -9.250  -0.4604   0.02334   0.01602  -0.1145   0.9035   0.0765
  -9.000  -0.4414   0.02276   0.01545  -0.1135   0.8936   0.0794
  -8.750  -0.4177   0.02211   0.01468  -0.1131   0.8861   0.0828
  -8.500  -0.3996   0.02137   0.01396  -0.1119   0.8771   0.0860
  -8.250  -0.3794   0.02072   0.01332  -0.1111   0.8694   0.0902
  -8.000  -0.3600   0.02023   0.01275  -0.1101   0.8615   0.0946
  -7.750  -0.3430   0.01946   0.01203  -0.1089   0.8532   0.0998
  -7.500  -0.3211   0.01892   0.01142  -0.1084   0.8471   0.1074
  -7.250  -0.3053   0.01822   0.01081  -0.1073   0.8383   0.1171
  -7.000  -0.2847   0.01745   0.01008  -0.1068   0.8320   0.1343
  -6.750  -0.2665   0.01657   0.00938  -0.1063   0.8247   0.1669
  -6.500  -0.2477   0.01543   0.00863  -0.1063   0.8174   0.2348
  -6.250  -0.2241   0.01446   0.00809  -0.1067   0.8121   0.3306
  -6.000  -0.1994   0.01422   0.00807  -0.1067   0.8051   0.3954
  -5.750  -0.1718   0.01417   0.00804  -0.1067   0.7987   0.4337
  -5.500  -0.1423   0.01420   0.00798  -0.1068   0.7938   0.4602
  -5.250  -0.1155   0.01433   0.00810  -0.1066   0.7872   0.4802
  -5.000  -0.0876   0.01444   0.00816  -0.1065   0.7810   0.4974
  -4.750  -0.0581   0.01456   0.00817  -0.1065   0.7762   0.5135
  -4.500  -0.0305   0.01477   0.00832  -0.1064   0.7701   0.5290
  -4.250  -0.0037   0.01500   0.00858  -0.1058   0.7638   0.5420
  -4.000   0.0248   0.01517   0.00871  -0.1055   0.7590   0.5534
  -3.750   0.0538   0.01531   0.00873  -0.1057   0.7540   0.5654
  -3.500   0.0793   0.01548   0.00897  -0.1049   0.7473   0.5726
  -3.250   0.1092   0.01551   0.00885  -0.1053   0.7422   0.5830
  -3.000   0.1372   0.01569   0.00903  -0.1047   0.7382   0.5903
  -2.750   0.1636   0.01583   0.00915  -0.1046   0.7317   0.6003
  -2.500   0.1909   0.01585   0.00917  -0.1042   0.7262   0.6059
  -2.250   0.2201   0.01588   0.00912  -0.1043   0.7219   0.6116
  -2.000   0.2489   0.01589   0.00905  -0.1048   0.7164   0.6193
  -1.750   0.2753   0.01592   0.00910  -0.1044   0.7107   0.6240
  -1.500   0.3037   0.01595   0.00911  -0.1044   0.7061   0.6292
  -1.250   0.3350   0.01595   0.00898  -0.1051   0.7024   0.6362
  -1.000   0.3607   0.01599   0.00906  -0.1049   0.6960   0.6416
  -0.750   0.3878   0.01603   0.00911  -0.1046   0.6908   0.6462
  -0.500   0.4179   0.01603   0.00904  -0.1050   0.6867   0.6522
  -0.250   0.4478   0.01607   0.00901  -0.1058   0.6824   0.6587
   0.000   0.4727   0.01617   0.00919  -0.1052   0.6766   0.6629
   0.250   0.5009   0.01619   0.00921  -0.1053   0.6719   0.6680
   0.500   0.5326   0.01619   0.00910  -0.1061   0.6680   0.6746
   0.750   0.5589   0.01630   0.00926  -0.1060   0.6630   0.6796
   1.000   0.5847   0.01642   0.00943  -0.1057   0.6578   0.6844
   1.250   0.6141   0.01645   0.00944  -0.1061   0.6534   0.6902
   1.500   0.6461   0.01646   0.00936  -0.1070   0.6498   0.6966
   1.750   0.6697   0.01665   0.00966  -0.1062   0.6444   0.7012
   2.000   0.6963   0.01677   0.00983  -0.1061   0.6393   0.7072
   2.250   0.7276   0.01680   0.00980  -0.1070   0.6351   0.7142
   2.500   0.7569   0.01686   0.00985  -0.1071   0.6316   0.7186
   2.750   0.7796   0.01708   0.01020  -0.1064   0.6258   0.7244
   3.000   0.8088   0.01718   0.01031  -0.1070   0.6207   0.7322
   3.250   0.8364   0.01721   0.01036  -0.1068   0.6167   0.7370
   3.500   0.8645   0.01736   0.01053  -0.1068   0.6125   0.7433
   3.750   0.8899   0.01757   0.01082  -0.1069   0.6066   0.7507
   4.000   0.9155   0.01764   0.01096  -0.1063   0.6019   0.7559
   4.250   0.9457   0.01769   0.01099  -0.1067   0.5980   0.7631
   4.500   0.9707   0.01792   0.01132  -0.1065   0.5927   0.7703
   4.750   0.9938   0.01808   0.01158  -0.1057   0.5871   0.7764
   5.000   1.0240   0.01812   0.01161  -0.1062   0.5825   0.7844
   5.250   1.0513   0.01822   0.01175  -0.1060   0.5779   0.7908
   5.500   1.0720   0.01841   0.01209  -0.1049   0.5711   0.7986
   5.750   1.1007   0.01837   0.01205  -0.1050   0.5654   0.8063
   6.000   1.1256   0.01842   0.01216  -0.1044   0.5592   0.8136
   6.250   1.1486   0.01849   0.01233  -0.1037   0.5516   0.8224
   6.500   1.1767   0.01838   0.01220  -0.1034   0.5459   0.8301
   6.750   1.1964   0.01855   0.01252  -0.1022   0.5379   0.8394
   7.000   1.2202   0.01845   0.01246  -0.1012   0.5308   0.8479
   7.250   1.2416   0.01852   0.01261  -0.1001   0.5232   0.8576
   7.500   1.2623   0.01850   0.01267  -0.0987   0.5150   0.8679
   7.750   1.2816   0.01849   0.01272  -0.0971   0.5069   0.8782
   8.000   1.2996   0.01836   0.01264  -0.0952   0.4962   0.8900
   8.250   1.3111   0.01833   0.01272  -0.0922   0.4844   0.9041
   8.500   1.3230   0.01822   0.01264  -0.0892   0.4730   0.9205
   8.750   1.3313   0.01813   0.01261  -0.0856   0.4619   0.9434
   9.000   1.3462   0.01820   0.01281  -0.0839   0.4493   1.0000
   9.250   1.3663   0.01854   0.01318  -0.0835   0.4352   1.0000
   9.500   1.3830   0.01900   0.01365  -0.0825   0.4201   1.0000
   9.750   1.3956   0.01959   0.01424  -0.0810   0.4036   1.0000
  10.000   1.4045   0.02034   0.01498  -0.0790   0.3851   1.0000
  10.250   1.4095   0.02132   0.01590  -0.0767   0.3645   1.0000
  10.500   1.4113   0.02256   0.01707  -0.0741   0.3420   1.0000
  10.750   1.4095   0.02412   0.01853  -0.0715   0.3176   1.0000
  11.000   1.4051   0.02602   0.02031  -0.0689   0.2938   1.0000
  11.250   1.3991   0.02819   0.02237  -0.0664   0.2692   1.0000
  11.500   1.3917   0.03065   0.02471  -0.0642   0.2459   1.0000
  11.750   1.3839   0.03332   0.02727  -0.0623   0.2227   1.0000
  12.000   1.3743   0.03629   0.03013  -0.0606   0.2022   1.0000
  12.250   1.3669   0.03928   0.03304  -0.0592   0.1816   1.0000
  12.500   1.3587   0.04249   0.03617  -0.0581   0.1626   1.0000
  12.750   1.3502   0.04591   0.03950  -0.0572   0.1455   1.0000
  13.000   1.3417   0.04950   0.04300  -0.0566   0.1299   1.0000
  13.250   1.3340   0.05316   0.04658  -0.0561   0.1162   1.0000
  13.500   1.3282   0.05675   0.05012  -0.0558   0.1044   1.0000
  13.750   1.3250   0.06016   0.05351  -0.0557   0.0947   1.0000
  14.000   1.3225   0.06356   0.05690  -0.0557   0.0873   1.0000
  14.250   1.3197   0.06705   0.06034  -0.0557   0.0816   1.0000
  14.500   1.3226   0.06994   0.06329  -0.0559   0.0763   1.0000
  14.750   1.3231   0.07313   0.06644  -0.0561   0.0722   1.0000
  15.000   1.3270   0.07593   0.06929  -0.0562   0.0684   1.0000
  15.250   1.3309   0.07882   0.07221  -0.0566   0.0650   1.0000
  15.500   1.3350   0.08150   0.07481  -0.0567   0.0621   1.0000
  15.750   1.3411   0.08418   0.07763  -0.0571   0.0595   1.0000
  16.000   1.3466   0.08690   0.08039  -0.0575   0.0570   1.0000
  16.250   1.3545   0.08905   0.08245  -0.0575   0.0546   1.0000
  16.500   1.3607   0.09175   0.08528  -0.0580   0.0527   1.0000
  16.750   1.3668   0.09444   0.08806  -0.0585   0.0506   1.0000
<< Back to NACA 63(3)-618 (naca633618-il)

Polar data table (+)

Polar graphs


<< Back to NACA 63(3)-618 (naca633618-il)