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NACA 63-415 AIRFOIL (n63415-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-415 AIRFOIL (n63415-il)
Reynolds number: 100,000
Max Cl/Cd: 53.05 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63415-il-100000.txt
Download as CSV file: xf-n63415-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-415 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3312   0.10643   0.10167  -0.0436   1.0000   0.1704
 -11.000  -0.2956   0.10409   0.09929  -0.0408   1.0000   0.1765
 -10.750  -0.5457   0.07393   0.06883  -0.0666   1.0000   0.0933
 -10.500  -0.5648   0.06828   0.06318  -0.0685   1.0000   0.0906
 -10.250  -0.6742   0.06179   0.05637  -0.0669   1.0000   0.0812
 -10.000  -0.6912   0.05912   0.05365  -0.0638   1.0000   0.0807
  -9.750  -0.7131   0.05710   0.05159  -0.0594   1.0000   0.0803
  -9.500  -0.7321   0.05506   0.04945  -0.0552   1.0000   0.0796
  -9.250  -0.7496   0.05286   0.04708  -0.0513   1.0000   0.0794
  -9.000  -0.7612   0.05035   0.04436  -0.0482   1.0000   0.0790
  -8.750  -0.7678   0.04772   0.04148  -0.0455   1.0000   0.0789
  -8.500  -0.7694   0.04498   0.03843  -0.0432   1.0000   0.0786
  -8.250  -0.7645   0.04213   0.03521  -0.0418   0.9995   0.0784
  -8.000  -0.7323   0.03855   0.03105  -0.0449   0.9935   0.0794
  -7.750  -0.6995   0.03625   0.02810  -0.0474   0.9866   0.0820
  -7.500  -0.6643   0.03326   0.02493  -0.0501   0.9817   0.0849
  -7.250  -0.6311   0.03156   0.02311  -0.0519   0.9749   0.0885
  -7.000  -0.5900   0.03014   0.02136  -0.0549   0.9697   0.0941
  -6.750  -0.5600   0.02843   0.01964  -0.0558   0.9626   0.0983
  -6.500  -0.5210   0.02731   0.01847  -0.0583   0.9569   0.1061
  -6.250  -0.4885   0.02607   0.01729  -0.0595   0.9504   0.1133
  -6.000  -0.4544   0.02516   0.01635  -0.0610   0.9435   0.1243
  -5.750  -0.4142   0.02389   0.01533  -0.0638   0.9392   0.1417
  -5.500  -0.3933   0.02292   0.01456  -0.0634   0.9296   0.1669
  -5.250  -0.3629   0.02010   0.01323  -0.0665   0.9243   0.3527
  -5.000  -0.3397   0.02022   0.01376  -0.0656   0.9153   0.4909
  -4.750  -0.3015   0.02080   0.01430  -0.0667   0.9093   0.5416
  -4.500  -0.2717   0.02141   0.01482  -0.0665   0.9019   0.5728
  -4.250  -0.2419   0.02218   0.01562  -0.0655   0.8947   0.5968
  -4.000  -0.2013   0.02291   0.01629  -0.0663   0.8907   0.6241
  -3.750  -0.1862   0.02361   0.01698  -0.0631   0.8804   0.6412
  -3.500  -0.1516   0.02423   0.01756  -0.0626   0.8756   0.6590
  -3.250  -0.1319   0.02463   0.01789  -0.0608   0.8668   0.6740
  -3.000  -0.1035   0.02507   0.01830  -0.0594   0.8606   0.6866
  -2.750  -0.0675   0.02532   0.01848  -0.0594   0.8569   0.6993
  -2.500  -0.0561   0.02551   0.01862  -0.0570   0.8460   0.7106
  -2.250  -0.0201   0.02542   0.01843  -0.0578   0.8416   0.7212
  -2.000  -0.0059   0.02564   0.01862  -0.0556   0.8322   0.7295
  -1.750   0.0269   0.02544   0.01831  -0.0569   0.8266   0.7409
  -1.500   0.0610   0.02536   0.01817  -0.0568   0.8231   0.7477
  -1.250   0.0723   0.02556   0.01834  -0.0552   0.8120   0.7582
  -1.000   0.1040   0.02546   0.01819  -0.0550   0.8079   0.7652
  -0.750   0.1190   0.02569   0.01838  -0.0539   0.7984   0.7753
  -0.500   0.1465   0.02562   0.01829  -0.0533   0.7929   0.7825
  -0.250   0.1836   0.02533   0.01792  -0.0548   0.7897   0.7919
   0.000   0.1886   0.02587   0.01850  -0.0516   0.7786   0.7998
   0.250   0.2233   0.02562   0.01820  -0.0527   0.7746   0.8090
   0.500   0.2334   0.02609   0.01870  -0.0503   0.7653   0.8176
   0.750   0.2613   0.02602   0.01861  -0.0503   0.7598   0.8266
   1.000   0.2954   0.02575   0.01831  -0.0507   0.7567   0.8354
   1.250   0.2990   0.02646   0.01907  -0.0479   0.7456   0.8454
   1.500   0.3326   0.02624   0.01884  -0.0487   0.7416   0.8556
   1.750   0.3393   0.02683   0.01948  -0.0458   0.7324   0.8657
   2.000   0.3643   0.02678   0.01944  -0.0452   0.7267   0.8761
   2.250   0.3999   0.02642   0.01908  -0.0458   0.7237   0.8868
   2.500   0.3981   0.02734   0.02008  -0.0423   0.7122   0.9003
   2.750   0.4310   0.02698   0.01974  -0.0424   0.7085   0.9115
   3.000   0.4371   0.02777   0.02059  -0.0401   0.6984   0.9274
   3.250   0.4716   0.02753   0.02041  -0.0409   0.6936   0.9405
   3.500   0.5210   0.02693   0.01984  -0.0436   0.6909   0.9514
   3.750   0.5458   0.02800   0.02103  -0.0455   0.6795   0.9681
   4.000   0.6066   0.02737   0.02046  -0.0505   0.6761   0.9763
   4.250   0.6526   0.02790   0.02112  -0.0552   0.6671   0.9888
   4.500   0.7102   0.02744   0.02074  -0.0602   0.6613   0.9994
   4.750   0.7165   0.02759   0.02091  -0.0573   0.6542   1.0000
   5.000   0.7311   0.02788   0.02126  -0.0562   0.6449   1.0000
   5.250   0.7689   0.02735   0.02078  -0.0573   0.6384   1.0000
   5.500   0.7990   0.02719   0.02068  -0.0578   0.6285   1.0000
   5.750   0.8299   0.02703   0.02060  -0.0583   0.6183   1.0000
   6.000   0.8765   0.02576   0.01937  -0.0597   0.6106   1.0000
   6.250   0.9052   0.02559   0.01928  -0.0598   0.5982   1.0000
   6.500   0.9421   0.02475   0.01850  -0.0603   0.5862   1.0000
   6.750   0.9804   0.02366   0.01743  -0.0607   0.5724   1.0000
   7.000   1.0121   0.02274   0.01655  -0.0602   0.5539   1.0000
   7.250   1.0424   0.02189   0.01570  -0.0597   0.5332   1.0000
   7.500   1.0726   0.02119   0.01496  -0.0591   0.5120   1.0000
   7.750   1.0910   0.02115   0.01506  -0.0575   0.4873   1.0000
   8.000   1.1103   0.02106   0.01499  -0.0559   0.4584   1.0000
   8.250   1.1247   0.02120   0.01511  -0.0536   0.4214   1.0000
   8.500   1.1315   0.02171   0.01543  -0.0504   0.3694   1.0000
   8.750   1.1257   0.02293   0.01622  -0.0459   0.3015   1.0000
   9.000   1.1108   0.02496   0.01774  -0.0409   0.2405   1.0000
   9.250   1.0961   0.02750   0.01981  -0.0369   0.1935   1.0000
   9.500   1.0867   0.03008   0.02204  -0.0339   0.1610   1.0000
   9.750   1.0839   0.03246   0.02412  -0.0317   0.1395   1.0000
  10.000   1.0893   0.03446   0.02598  -0.0300   0.1234   1.0000
  10.250   1.1000   0.03626   0.02760  -0.0287   0.1117   1.0000
  10.500   1.1139   0.03784   0.02913  -0.0276   0.1021   1.0000
  10.750   1.1339   0.03939   0.03070  -0.0268   0.0941   1.0000
  11.000   1.1619   0.04098   0.03207  -0.0266   0.0866   1.0000
  11.250   1.1791   0.04263   0.03392  -0.0259   0.0815   1.0000
  11.500   1.2185   0.04460   0.03566  -0.0267   0.0752   1.0000
  11.750   1.2341   0.04660   0.03799  -0.0258   0.0723   1.0000
  12.000   1.2532   0.04872   0.04030  -0.0253   0.0691   1.0000
  12.250   1.2792   0.05098   0.04251  -0.0256   0.0657   1.0000
  12.500   1.2948   0.05421   0.04599  -0.0251   0.0636   1.0000
  12.750   1.2954   0.05709   0.04922  -0.0235   0.0627   1.0000
  13.000   1.2932   0.06031   0.05280  -0.0221   0.0620   1.0000
  13.250   1.2871   0.06383   0.05665  -0.0207   0.0615   1.0000
  13.500   1.2769   0.06765   0.06079  -0.0197   0.0612   1.0000
  13.750   1.2634   0.07183   0.06527  -0.0190   0.0610   1.0000
  14.000   1.2459   0.07644   0.07018  -0.0188   0.0609   1.0000
  14.250   1.2250   0.08161   0.07564  -0.0193   0.0610   1.0000
  14.500   1.2011   0.08737   0.08167  -0.0205   0.0613   1.0000
  14.750   1.1739   0.09391   0.08847  -0.0226   0.0617   1.0000
  15.000   1.1449   0.10123   0.09603  -0.0256   0.0622   1.0000
  15.250   1.1156   0.10931   0.10430  -0.0296   0.0629   1.0000
  15.500   1.0873   0.11816   0.11331  -0.0345   0.0636   1.0000
  15.750   1.0655   0.12698   0.12224  -0.0392   0.0642   1.0000
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