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(2)-615 (naca632615-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 63(2)-615 (naca632615-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.64 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca632615-il-1000000-n5.txt
Download as CSV file: xf-naca632615-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63(2)-615                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.500  -0.8139   0.11244   0.10997  -0.0496   1.0000   0.0092
 -18.250  -0.8872   0.09498   0.09227  -0.0594   1.0000   0.0089
 -18.000  -0.9354   0.08258   0.07967  -0.0666   1.0000   0.0089
 -17.750  -0.9701   0.07292   0.06984  -0.0725   1.0000   0.0089
 -17.500  -0.9924   0.06568   0.06245  -0.0769   1.0000   0.0089
 -17.250  -1.0072   0.05995   0.05661  -0.0803   1.0000   0.0089
 -17.000  -1.0223   0.05445   0.05098  -0.0836   1.0000   0.0089
 -16.750  -1.0282   0.05053   0.04696  -0.0857   1.0000   0.0091
 -16.500  -1.0346   0.04674   0.04307  -0.0876   1.0000   0.0091
 -16.250  -1.0395   0.04331   0.03954  -0.0892   1.0000   0.0093
 -16.000  -1.0406   0.04046   0.03661  -0.0904   1.0000   0.0094
 -15.750  -1.0423   0.03765   0.03371  -0.0913   1.0000   0.0094
 -15.500  -1.0405   0.03535   0.03133  -0.0919   1.0000   0.0095
 -15.250  -1.0388   0.03316   0.02905  -0.0922   1.0000   0.0096
 -15.000  -1.0358   0.03122   0.02705  -0.0923   1.0000   0.0097
 -14.750  -1.0326   0.02945   0.02520  -0.0920   1.0000   0.0098
 -14.500  -1.0299   0.02783   0.02350  -0.0913   1.0000   0.0099
 -14.000  -1.0070   0.02478   0.02031  -0.0925   0.9917   0.0102
 -13.750  -0.9864   0.02322   0.01870  -0.0947   0.9819   0.0105
 -13.500  -0.9587   0.02192   0.01733  -0.0977   0.9720   0.0108
 -13.250  -0.9230   0.02073   0.01606  -0.1019   0.9628   0.0111
 -13.000  -0.8845   0.01964   0.01490  -0.1063   0.9510   0.0115
 -12.750  -0.8497   0.01869   0.01383  -0.1098   0.9329   0.0119
 -12.500  -0.8284   0.01799   0.01299  -0.1103   0.9108   0.0122
 -12.250  -0.8105   0.01745   0.01232  -0.1097   0.8941   0.0125
 -12.000  -0.7938   0.01685   0.01162  -0.1088   0.8797   0.0128
 -11.750  -0.7749   0.01633   0.01103  -0.1081   0.8675   0.0133
 -11.500  -0.7546   0.01587   0.01051  -0.1075   0.8569   0.0138
 -11.000  -0.7111   0.01503   0.00951  -0.1065   0.8375   0.0147
 -10.750  -0.6884   0.01465   0.00905  -0.1061   0.8288   0.0151
 -10.500  -0.6650   0.01424   0.00858  -0.1059   0.8205   0.0157
 -10.000  -0.6166   0.01352   0.00776  -0.1055   0.8053   0.0170
  -9.750  -0.5915   0.01322   0.00740  -0.1053   0.7978   0.0178
  -9.500  -0.5658   0.01293   0.00705  -0.1053   0.7914   0.0185
  -9.250  -0.5402   0.01259   0.00669  -0.1053   0.7844   0.0194
  -9.000  -0.5143   0.01232   0.00637  -0.1052   0.7775   0.0203
  -8.750  -0.4876   0.01206   0.00607  -0.1053   0.7711   0.0213
  -8.500  -0.4609   0.01182   0.00577  -0.1053   0.7643   0.0220
  -8.250  -0.4342   0.01155   0.00547  -0.1054   0.7581   0.0231
  -8.000  -0.4069   0.01131   0.00521  -0.1055   0.7515   0.0243
  -7.750  -0.3797   0.01112   0.00497  -0.1056   0.7451   0.0255
  -7.500  -0.3519   0.01093   0.00473  -0.1058   0.7392   0.0263
  -7.250  -0.3244   0.01067   0.00445  -0.1060   0.7325   0.0277
  -7.000  -0.2967   0.01048   0.00422  -0.1061   0.7266   0.0290
  -6.750  -0.2685   0.01029   0.00401  -0.1064   0.7206   0.0304
  -6.500  -0.2404   0.01014   0.00381  -0.1066   0.7141   0.0313
  -6.250  -0.2123   0.00993   0.00357  -0.1068   0.7083   0.0331
  -6.000  -0.1838   0.00975   0.00338  -0.1071   0.7024   0.0349
  -5.750  -0.1554   0.00961   0.00320  -0.1073   0.6961   0.0364
  -5.500  -0.1268   0.00945   0.00301  -0.1076   0.6904   0.0384
  -5.250  -0.0981   0.00928   0.00284  -0.1079   0.6844   0.0413
  -5.000  -0.0695   0.00916   0.00269  -0.1082   0.6787   0.0439
  -4.750  -0.0406   0.00900   0.00253  -0.1085   0.6732   0.0493
  -4.500  -0.0117   0.00885   0.00239  -0.1089   0.6670   0.0563
  -4.250   0.0171   0.00869   0.00225  -0.1092   0.6611   0.0676
  -4.000   0.0463   0.00850   0.00211  -0.1097   0.6562   0.0853
  -3.750   0.0755   0.00830   0.00198  -0.1101   0.6504   0.1092
  -3.500   0.1046   0.00810   0.00185  -0.1106   0.6443   0.1401
  -3.250   0.1342   0.00784   0.00172  -0.1112   0.6391   0.1801
  -3.000   0.1639   0.00754   0.00159  -0.1119   0.6334   0.2365
  -2.750   0.1934   0.00728   0.00148  -0.1126   0.6279   0.2919
  -2.500   0.2234   0.00703   0.00139  -0.1133   0.6228   0.3457
  -2.250   0.2532   0.00685   0.00134  -0.1139   0.6168   0.3959
  -2.000   0.2827   0.00674   0.00132  -0.1144   0.6113   0.4393
  -1.750   0.3124   0.00666   0.00132  -0.1148   0.6066   0.4715
  -1.500   0.3419   0.00663   0.00132  -0.1152   0.6011   0.4895
  -1.250   0.3710   0.00665   0.00133  -0.1155   0.5954   0.5032
  -1.000   0.4005   0.00664   0.00135  -0.1158   0.5905   0.5175
  -0.750   0.4298   0.00665   0.00136  -0.1161   0.5853   0.5269
  -0.500   0.4589   0.00669   0.00138  -0.1164   0.5799   0.5348
  -0.250   0.4880   0.00671   0.00140  -0.1167   0.5749   0.5419
   0.000   0.5173   0.00674   0.00143  -0.1170   0.5696   0.5493
   0.500   0.5752   0.00682   0.00150  -0.1174   0.5592   0.5621
   0.750   0.6044   0.00686   0.00154  -0.1177   0.5537   0.5684
   1.000   0.6331   0.00692   0.00159  -0.1179   0.5478   0.5737
   1.250   0.6619   0.00697   0.00164  -0.1182   0.5424   0.5799
   1.500   0.6909   0.00702   0.00170  -0.1184   0.5366   0.5860
   1.750   0.7194   0.00710   0.00176  -0.1186   0.5306   0.5912
   2.000   0.7482   0.00715   0.00183  -0.1188   0.5254   0.5970
   2.250   0.7769   0.00721   0.00191  -0.1190   0.5195   0.6035
   2.500   0.8051   0.00730   0.00199  -0.1191   0.5132   0.6092
   2.750   0.8337   0.00736   0.00207  -0.1193   0.5062   0.6152
   3.250   0.8896   0.00758   0.00227  -0.1195   0.4861   0.6271
   3.500   0.9173   0.00770   0.00238  -0.1196   0.4767   0.6338
   3.750   0.9449   0.00783   0.00250  -0.1196   0.4664   0.6404
   4.000   0.9719   0.00799   0.00264  -0.1195   0.4510   0.6461
   4.250   0.9978   0.00824   0.00281  -0.1193   0.4290   0.6527
   4.500   1.0236   0.00849   0.00299  -0.1191   0.4062   0.6595
   4.750   1.0482   0.00882   0.00322  -0.1187   0.3786   0.6661
   5.000   1.0706   0.00933   0.00355  -0.1179   0.3376   0.6730
   5.250   1.0910   0.00998   0.00396  -0.1168   0.2900   0.6791
   5.500   1.1119   0.01056   0.00436  -0.1159   0.2497   0.6862
   5.750   1.1317   0.01121   0.00482  -0.1148   0.2099   0.6934
   6.000   1.1521   0.01179   0.00525  -0.1137   0.1775   0.6998
   6.250   1.1718   0.01238   0.00571  -0.1126   0.1468   0.7070
   6.500   1.1915   0.01295   0.00615  -0.1114   0.1221   0.7140
   6.750   1.2108   0.01349   0.00661  -0.1102   0.1002   0.7215
   7.000   1.2293   0.01406   0.00708  -0.1088   0.0807   0.7287
   7.250   1.2476   0.01460   0.00756  -0.1074   0.0654   0.7359
   7.750   1.2813   0.01558   0.00849  -0.1041   0.0457   0.7514
   8.250   1.3107   0.01655   0.00946  -0.1000   0.0344   0.7680
   8.750   1.3411   0.01754   0.01052  -0.0964   0.0294   0.7862
   9.000   1.3551   0.01811   0.01112  -0.0945   0.0274   0.7963
   9.250   1.3703   0.01865   0.01172  -0.0929   0.0262   0.8066
   9.500   1.3844   0.01926   0.01238  -0.0912   0.0248   0.8178
   9.750   1.3975   0.01995   0.01312  -0.0894   0.0235   0.8303
  10.000   1.4106   0.02066   0.01389  -0.0877   0.0224   0.8441
  10.250   1.4238   0.02137   0.01468  -0.0861   0.0213   0.8597
  10.500   1.4353   0.02215   0.01555  -0.0844   0.0203   0.8806
  10.750   1.4436   0.02297   0.01648  -0.0821   0.0193   0.9172
  11.000   1.4524   0.02378   0.01740  -0.0800   0.0185   1.0000
  11.250   1.4653   0.02476   0.01841  -0.0788   0.0175   1.0000
  11.500   1.4771   0.02584   0.01952  -0.0776   0.0164   1.0000
  11.750   1.4875   0.02706   0.02076  -0.0764   0.0154   1.0000
  12.000   1.4989   0.02824   0.02199  -0.0753   0.0146   1.0000
  12.250   1.5093   0.02954   0.02331  -0.0743   0.0136   1.0000
  12.500   1.5186   0.03097   0.02477  -0.0732   0.0127   1.0000
  12.750   1.5281   0.03241   0.02626  -0.0722   0.0121   1.0000
  13.000   1.5370   0.03395   0.02784  -0.0713   0.0115   1.0000
  13.250   1.5452   0.03559   0.02952  -0.0705   0.0110   1.0000
  13.500   1.5525   0.03735   0.03132  -0.0697   0.0104   1.0000
  13.750   1.5595   0.03919   0.03321  -0.0689   0.0101   1.0000
  14.000   1.5666   0.04107   0.03515  -0.0683   0.0099   1.0000
  14.250   1.5734   0.04303   0.03718  -0.0677   0.0097   1.0000
  14.500   1.5798   0.04510   0.03930  -0.0672   0.0094   1.0000
  14.750   1.5856   0.04727   0.04153  -0.0668   0.0093   1.0000
  15.000   1.5905   0.04959   0.04392  -0.0665   0.0090   1.0000
  15.250   1.5952   0.05200   0.04640  -0.0663   0.0089   1.0000
  15.500   1.5997   0.05450   0.04896  -0.0662   0.0087   1.0000
  15.750   1.6031   0.05718   0.05171  -0.0661   0.0086   1.0000
  16.000   1.6057   0.06001   0.05461  -0.0662   0.0084   1.0000
  16.250   1.6078   0.06298   0.05765  -0.0664   0.0083   1.0000
  16.500   1.6091   0.06614   0.06088  -0.0667   0.0082   1.0000
  16.750   1.6092   0.06951   0.06433  -0.0671   0.0080   1.0000
  17.000   1.6109   0.07273   0.06764  -0.0676   0.0079   1.0000
  17.250   1.6119   0.07610   0.07110  -0.0683   0.0079   1.0000
  17.500   1.6127   0.07956   0.07464  -0.0690   0.0078   1.0000
  17.750   1.6122   0.08328   0.07846  -0.0699   0.0077   1.0000
  18.000   1.6109   0.08717   0.08244  -0.0709   0.0077   1.0000
  18.250   1.6091   0.09120   0.08656  -0.0721   0.0076   1.0000
  18.500   1.6071   0.09534   0.09079  -0.0734   0.0075   1.0000
  18.750   1.6043   0.09965   0.09520  -0.0748   0.0075   1.0000
  19.000   1.6004   0.10420   0.09984  -0.0764   0.0074   1.0000
  19.250   1.5962   0.10883   0.10458  -0.0782   0.0074   1.0000
<< Back to NACA 63(2)-615 (naca632615-il)

Polar data table (+)

Polar graphs


<< Back to NACA 63(2)-615 (naca632615-il)