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NACA 67 (naca671215-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 67 (naca671215-il)
Reynolds number: 200,000
Max Cl/Cd: 42.41 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca671215-il-200000.txt
Download as CSV file: xf-naca671215-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 67                                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.3633   0.11614   0.11269  -0.0634   0.9795   0.0715
 -12.250  -0.3643   0.11338   0.10993  -0.0634   0.9785   0.0740
 -12.000  -0.5183   0.10430   0.10075  -0.0692   0.9853   0.0694
 -11.750  -0.5044   0.10268   0.09910  -0.0687   0.9844   0.0709
 -11.500  -0.5085   0.09735   0.09378  -0.0720   0.9833   0.0720
 -11.250  -0.5313   0.09105   0.08750  -0.0749   0.9809   0.0730
 -11.000  -0.5682   0.08412   0.08053  -0.0777   0.9785   0.0730
 -10.750  -0.6005   0.07945   0.07579  -0.0774   0.9765   0.0733
 -10.500  -0.6301   0.07555   0.07178  -0.0760   0.9744   0.0735
 -10.250  -0.6554   0.07237   0.06847  -0.0737   0.9725   0.0742
 -10.000  -0.6871   0.07081   0.06683  -0.0676   0.9708   0.0745
  -9.750  -0.7244   0.07011   0.06608  -0.0588   0.9691   0.0744
  -9.500  -0.7527   0.06862   0.06450  -0.0517   0.9672   0.0748
  -9.250  -0.7788   0.06705   0.06280  -0.0447   0.9668   0.0761
  -9.000  -0.8983   0.05356   0.04766  -0.0215   0.9684   0.0474
  -8.250  -0.9815   0.05155   0.04560   0.0088   1.0000   0.0465
  -8.000  -0.9776   0.04760   0.04148   0.0116   1.0000   0.0456
  -7.750  -0.9739   0.04456   0.03809   0.0152   1.0000   0.0455
  -7.500  -0.9668   0.04161   0.03482   0.0183   1.0000   0.0452
  -7.250  -0.9567   0.03888   0.03174   0.0211   1.0000   0.0448
  -7.000  -0.9437   0.03647   0.02898   0.0236   1.0000   0.0446
  -6.750  -0.9285   0.03454   0.02671   0.0258   1.0000   0.0452
  -6.500  -0.9116   0.03299   0.02486   0.0277   1.0000   0.0459
  -6.250  -0.8946   0.03205   0.02363   0.0296   1.0000   0.0468
  -6.000  -0.8736   0.02987   0.02139   0.0303   1.0000   0.0488
  -5.750  -0.8543   0.02899   0.02046   0.0314   1.0000   0.0506
  -5.500  -0.8342   0.02812   0.01951   0.0325   1.0000   0.0524
  -5.250  -0.8101   0.02739   0.01865   0.0330   0.9993   0.0546
  -5.000  -0.7826   0.02667   0.01780   0.0327   0.9975   0.0575
  -4.750  -0.7543   0.02615   0.01736   0.0319   0.9953   0.0612
  -4.500  -0.7276   0.02593   0.01711   0.0317   0.9935   0.0652
  -4.250  -0.7039   0.02529   0.01644   0.0320   0.9902   0.0694
  -4.000  -0.6778   0.02504   0.01625   0.0317   0.9869   0.0746
  -3.750  -0.6481   0.02524   0.01639   0.0308   0.9843   0.0804
  -3.500  -0.6302   0.02458   0.01583   0.0321   0.9804   0.0870
  -3.250  -0.6053   0.02435   0.01558   0.0321   0.9758   0.0958
  -3.000  -0.5775   0.02438   0.01574   0.0315   0.9728   0.1140
  -2.750  -0.5641   0.02344   0.01523   0.0336   0.9681   0.1751
  -2.500  -0.5710   0.02074   0.01468   0.0391   0.9627   0.5669
  -2.000  -0.5436   0.02277   0.01763   0.0482   0.9512   0.8405
  -1.750  -0.5129   0.02449   0.01930   0.0490   0.9468   0.8603
  -1.500  -0.4965   0.02533   0.02009   0.0523   0.9403   0.8761
  -1.250  -0.4567   0.02697   0.02166   0.0515   0.9338   0.8925
  -1.000  -0.0842   0.03377   0.02810  -0.0106   0.9165   0.9241
  -0.500  -0.0454   0.03354   0.02781  -0.0088   0.9050   0.9359
  -0.250   0.0052   0.03363   0.02785  -0.0139   0.9025   0.9382
   0.000   0.0527   0.03384   0.02803  -0.0184   0.9000   0.9406
   0.250   0.0365   0.03359   0.02777  -0.0106   0.8901   0.9476
   0.500   0.0845   0.03354   0.02770  -0.0153   0.8874   0.9490
   0.750   0.1348   0.03361   0.02777  -0.0203   0.8854   0.9504
   1.000   0.1415   0.03337   0.02754  -0.0171   0.8758   0.9538
   1.250   0.1786   0.03332   0.02749  -0.0194   0.8721   0.9558
   1.500   0.2213   0.03333   0.02752  -0.0228   0.8699   0.9572
   1.750   0.2164   0.03315   0.02734  -0.0171   0.8586   0.9608
   2.000   0.2621   0.03295   0.02718  -0.0210   0.8556   0.9615
   2.250   0.3083   0.03283   0.02710  -0.0249   0.8531   0.9622
   2.500   0.3211   0.03256   0.02687  -0.0227   0.8424   0.9645
   2.750   0.3744   0.03206   0.02644  -0.0276   0.8394   0.9650
   3.000   0.3885   0.03170   0.02612  -0.0252   0.8281   0.9665
   3.250   0.4499   0.03072   0.02522  -0.0311   0.8246   0.9670
   3.500   0.4800   0.02981   0.02439  -0.0310   0.8133   0.9683
   3.750   0.6746   0.02395   0.01876  -0.0585   0.8090   0.9663
   4.000   0.6805   0.02337   0.01825  -0.0538   0.7966   0.9677
   4.250   0.7292   0.02150   0.01651  -0.0565   0.7850   0.9688
   4.500   0.7248   0.02104   0.01610  -0.0498   0.7708   0.9696
   4.750   0.7021   0.02127   0.01636  -0.0401   0.7546   0.9717
   5.000   0.6917   0.02111   0.01624  -0.0326   0.7344   0.9727
   5.250   0.7867   0.01855   0.01211  -0.0415   0.4430   0.9723
   5.500   0.7625   0.01929   0.01245  -0.0320   0.3697   0.9738
   5.750   0.7416   0.02026   0.01297  -0.0235   0.2868   0.9753
   6.000   0.7259   0.02133   0.01353  -0.0163   0.2007   0.9765
   6.250   0.7198   0.02250   0.01421  -0.0111   0.1299   0.9785
   6.500   0.7204   0.02323   0.01476  -0.0068   0.1070   0.9797
   6.750   0.7246   0.02379   0.01530  -0.0030   0.0955   0.9809
   7.000   0.7284   0.02443   0.01589   0.0008   0.0883   0.9824
   7.250   0.7388   0.02493   0.01641   0.0033   0.0816   0.9840
   7.500   0.7523   0.02565   0.01709   0.0051   0.0758   0.9849
   7.750   0.7692   0.02614   0.01762   0.0064   0.0705   0.9859
   8.000   0.7861   0.02710   0.01847   0.0076   0.0654   0.9867
   8.250   0.8051   0.02754   0.01903   0.0086   0.0618   0.9878
   8.500   0.8243   0.02816   0.01965   0.0094   0.0578   0.9888
   8.750   0.8548   0.02934   0.02079   0.0086   0.0538   0.9894
   9.000   0.8777   0.03002   0.02159   0.0089   0.0504   0.9908
   9.250   0.9003   0.03081   0.02237   0.0091   0.0473   0.9920
   9.500   0.9449   0.03270   0.02434   0.0061   0.0444   0.9918
   9.750   0.9725   0.03403   0.02590   0.0059   0.0428   0.9926
  10.000   0.9974   0.03545   0.02749   0.0059   0.0411   0.9934
  10.250   1.0226   0.03694   0.02911   0.0057   0.0398   0.9942
  10.500   1.0700   0.04078   0.03300   0.0009   0.0376   0.9937
  10.750   1.0713   0.04192   0.03448   0.0046   0.0371   0.9957
  11.000   1.0784   0.04400   0.03690   0.0072   0.0368   0.9974
  11.250   1.0847   0.04663   0.03985   0.0095   0.0368   0.9991
  11.500   1.0773   0.04863   0.04213   0.0142   0.0367   1.0000
  11.750   1.0601   0.05026   0.04398   0.0206   0.0367   1.0000
  12.000   1.0467   0.05220   0.04609   0.0261   0.0369   1.0000
  12.250   1.0231   0.05359   0.04766   0.0330   0.0369   1.0000
  12.500   1.0080   0.05574   0.04994   0.0383   0.0372   1.0000
  12.750   0.9845   0.05735   0.05169   0.0448   0.0373   1.0000
  13.000   0.9749   0.06019   0.05461   0.0489   0.0377   1.0000
  13.250   0.9527   0.06107   0.05563   0.0546   0.0378   1.0000
  13.500   0.8478   0.06798   0.06344   0.0642   0.0416   1.0000
  13.750   0.8174   0.07315   0.06881   0.0654   0.0428   1.0000
  14.000   0.7922   0.07843   0.07423   0.0653   0.0436   1.0000
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