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NACA 64(2)-415 (naca642415-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 64(2)-415 (naca642415-il)
Reynolds number: 100,000
Max Cl/Cd: 51.25 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca642415-il-100000-n5.txt
Download as CSV file: xf-naca642415-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64(2)-415                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4993   0.09576   0.09027  -0.0545   1.0000   0.0389
 -12.250  -0.5417   0.08169   0.07617  -0.0636   1.0000   0.0382
 -12.000  -0.5809   0.07206   0.06641  -0.0701   1.0000   0.0376
 -11.750  -0.6131   0.06534   0.05954  -0.0739   1.0000   0.0373
 -11.500  -0.6398   0.06034   0.05438  -0.0756   1.0000   0.0371
 -11.250  -0.6637   0.05640   0.05028  -0.0757   1.0000   0.0371
 -11.000  -0.6855   0.05344   0.04717  -0.0741   1.0000   0.0371
 -10.750  -0.7085   0.05134   0.04497  -0.0706   1.0000   0.0371
 -10.500  -0.7288   0.04951   0.04303  -0.0664   1.0000   0.0372
 -10.250  -0.7479   0.04793   0.04132  -0.0618   1.0000   0.0374
 -10.000  -0.7431   0.04485   0.03787  -0.0621   0.9926   0.0379
  -9.750  -0.7248   0.04152   0.03404  -0.0644   0.9829   0.0391
  -9.500  -0.7038   0.03856   0.03049  -0.0662   0.9739   0.0404
  -9.250  -0.6769   0.03656   0.02841  -0.0678   0.9665   0.0416
  -9.000  -0.6460   0.03462   0.02627  -0.0700   0.9609   0.0427
  -8.750  -0.6178   0.03285   0.02429  -0.0712   0.9533   0.0439
  -8.500  -0.5864   0.03118   0.02238  -0.0728   0.9472   0.0458
  -8.250  -0.5573   0.02979   0.02067  -0.0737   0.9397   0.0478
  -8.000  -0.5271   0.02839   0.01932  -0.0749   0.9329   0.0497
  -7.750  -0.4963   0.02721   0.01809  -0.0760   0.9266   0.0517
  -7.500  -0.4693   0.02620   0.01697  -0.0763   0.9180   0.0540
  -7.250  -0.4381   0.02518   0.01583  -0.0773   0.9121   0.0573
  -7.000  -0.4162   0.02433   0.01503  -0.0769   0.9020   0.0601
  -6.750  -0.3881   0.02347   0.01410  -0.0774   0.8956   0.0636
  -6.500  -0.3673   0.02279   0.01336  -0.0765   0.8853   0.0677
  -6.250  -0.3419   0.02201   0.01258  -0.0767   0.8785   0.0733
  -6.000  -0.3214   0.02140   0.01191  -0.0758   0.8686   0.0793
  -5.750  -0.2966   0.02067   0.01115  -0.0758   0.8619   0.0894
  -5.500  -0.2769   0.02002   0.01055  -0.0749   0.8521   0.1034
  -5.250  -0.2532   0.01917   0.00983  -0.0748   0.8456   0.1324
  -5.000  -0.2351   0.01819   0.00919  -0.0742   0.8362   0.1978
  -4.750  -0.2167   0.01676   0.00860  -0.0738   0.8293   0.3550
  -4.500  -0.1952   0.01654   0.00879  -0.0727   0.8211   0.4745
  -4.250  -0.1687   0.01657   0.00878  -0.0722   0.8143   0.5233
  -4.000  -0.1424   0.01669   0.00886  -0.0716   0.8076   0.5570
  -3.750  -0.1175   0.01692   0.00908  -0.0705   0.8002   0.5826
  -3.500  -0.0905   0.01717   0.00924  -0.0697   0.7948   0.6090
  -3.250  -0.0673   0.01756   0.00965  -0.0681   0.7871   0.6298
  -3.000  -0.0412   0.01771   0.00972  -0.0672   0.7808   0.6446
  -2.750  -0.0138   0.01770   0.00960  -0.0669   0.7750   0.6520
  -2.500   0.0128   0.01762   0.00940  -0.0670   0.7677   0.6594
  -2.250   0.0404   0.01759   0.00930  -0.0667   0.7625   0.6643
  -2.000   0.0674   0.01757   0.00918  -0.0667   0.7565   0.6708
  -1.750   0.0946   0.01751   0.00903  -0.0668   0.7501   0.6770
  -1.500   0.1226   0.01747   0.00892  -0.0666   0.7451   0.6815
  -1.250   0.1491   0.01746   0.00886  -0.0666   0.7387   0.6870
  -1.000   0.1771   0.01740   0.00872  -0.0670   0.7327   0.6932
  -0.750   0.2051   0.01737   0.00864  -0.0668   0.7282   0.6972
  -0.500   0.2312   0.01743   0.00868  -0.0666   0.7224   0.7025
  -0.250   0.2589   0.01744   0.00865  -0.0669   0.7168   0.7091
   0.000   0.2867   0.01744   0.00862  -0.0669   0.7125   0.7137
   0.250   0.3134   0.01749   0.00867  -0.0667   0.7074   0.7188
   0.500   0.3401   0.01756   0.00873  -0.0668   0.7014   0.7253
   0.750   0.3675   0.01759   0.00876  -0.0667   0.6969   0.7308
   1.000   0.3954   0.01763   0.00879  -0.0667   0.6932   0.7367
   1.250   0.4210   0.01780   0.00900  -0.0668   0.6873   0.7443
   1.500   0.4465   0.01791   0.00916  -0.0663   0.6826   0.7494
   1.750   0.4745   0.01796   0.00922  -0.0663   0.6788   0.7560
   2.000   0.5006   0.01811   0.00941  -0.0663   0.6739   0.7630
   2.250   0.5245   0.01830   0.00970  -0.0657   0.6687   0.7696
   2.500   0.5523   0.01842   0.00984  -0.0659   0.6646   0.7780
   2.750   0.5793   0.01848   0.00995  -0.0655   0.6612   0.7845
   3.000   0.6025   0.01876   0.01034  -0.0651   0.6553   0.7930
   3.250   0.6269   0.01892   0.01059  -0.0645   0.6501   0.8002
   3.500   0.6548   0.01897   0.01069  -0.0644   0.6458   0.8088
   3.750   0.6780   0.01918   0.01102  -0.0637   0.6403   0.8172
   4.000   0.7017   0.01941   0.01136  -0.0631   0.6345   0.8271
   4.250   0.7272   0.01948   0.01151  -0.0625   0.6301   0.8357
   4.500   0.7517   0.01966   0.01181  -0.0620   0.6249   0.8460
   4.750   0.7722   0.01988   0.01218  -0.0608   0.6180   0.8565
   5.000   0.7995   0.01974   0.01211  -0.0602   0.6121   0.8668
   5.250   0.8179   0.01987   0.01241  -0.0585   0.6019   0.8794
   5.750   0.8661   0.01936   0.01202  -0.0560   0.5793   0.9067
   6.000   0.8858   0.01921   0.01198  -0.0542   0.5644   0.9240
   6.250   0.9092   0.01903   0.01193  -0.0532   0.5481   0.9444
   6.750   0.9604   0.01891   0.01193  -0.0529   0.4995   1.0000
   7.000   0.9793   0.01911   0.01213  -0.0517   0.4672   1.0000
   7.250   0.9954   0.01947   0.01244  -0.0502   0.4216   1.0000
   7.500   1.0045   0.02016   0.01267  -0.0475   0.3488   1.0000
   7.750   1.0032   0.02146   0.01351  -0.0439   0.2828   1.0000
   8.000   0.9997   0.02307   0.01475  -0.0404   0.2288   1.0000
   8.250   0.9979   0.02480   0.01619  -0.0375   0.1840   1.0000
   8.500   0.9984   0.02655   0.01770  -0.0352   0.1474   1.0000
   8.750   1.0009   0.02829   0.01927  -0.0334   0.1203   1.0000
   9.000   1.0048   0.03002   0.02087  -0.0317   0.1012   1.0000
   9.250   1.0101   0.03174   0.02251  -0.0303   0.0876   1.0000
   9.500   1.0168   0.03341   0.02418  -0.0291   0.0777   1.0000
   9.750   1.0232   0.03516   0.02591  -0.0280   0.0705   1.0000
  10.000   1.0302   0.03690   0.02765  -0.0270   0.0648   1.0000
  10.250   1.0379   0.03864   0.02942  -0.0260   0.0602   1.0000
  10.500   1.0460   0.04037   0.03120  -0.0252   0.0563   1.0000
  10.750   1.0527   0.04226   0.03309  -0.0244   0.0533   1.0000
  11.000   1.0628   0.04393   0.03486  -0.0237   0.0500   1.0000
  11.250   1.0719   0.04569   0.03666  -0.0230   0.0476   1.0000
  11.500   1.0798   0.04761   0.03855  -0.0224   0.0455   1.0000
  11.750   1.0921   0.04924   0.04033  -0.0218   0.0432   1.0000
  12.000   1.1030   0.05099   0.04216  -0.0212   0.0411   1.0000
  12.250   1.1139   0.05278   0.04399  -0.0208   0.0396   1.0000
  12.500   1.1265   0.05455   0.04572  -0.0202   0.0384   1.0000
  12.750   1.1403   0.05634   0.04770  -0.0197   0.0370   1.0000
  13.000   1.1519   0.05833   0.04986  -0.0193   0.0356   1.0000
  13.250   1.1618   0.06044   0.05211  -0.0190   0.0344   1.0000
  13.500   1.1709   0.06262   0.05438  -0.0188   0.0334   1.0000
  13.750   1.1804   0.06479   0.05659  -0.0187   0.0324   1.0000
  14.000   1.1901   0.06727   0.05918  -0.0184   0.0318   1.0000
  14.250   1.1940   0.07035   0.06256  -0.0184   0.0312   1.0000
  14.500   1.1951   0.07379   0.06627  -0.0185   0.0307   1.0000
  14.750   1.1932   0.07757   0.07033  -0.0189   0.0303   1.0000
  15.000   1.1882   0.08178   0.07480  -0.0196   0.0300   1.0000
  15.250   1.1804   0.08641   0.07969  -0.0208   0.0297   1.0000
  15.500   1.1696   0.09158   0.08513  -0.0224   0.0295   1.0000
  15.750   1.1558   0.09735   0.09117  -0.0246   0.0294   1.0000
  16.000   1.1388   0.10388   0.09797  -0.0275   0.0293   1.0000
  16.250   1.1184   0.11140   0.10574  -0.0314   0.0293   1.0000
  16.500   1.0927   0.12041   0.11503  -0.0366   0.0294   1.0000
  16.750   1.0590   0.13210   0.12700  -0.0441   0.0296   1.0000
  17.000   1.0030   0.15177   0.14695  -0.0573   0.0304   1.0000
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