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

NACA 67 (naca671215-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 67 (naca671215-il)
Reynolds number: 100,000
Max Cl/Cd: 25.76 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca671215-il-100000-n5.txt
Download as CSV file: xf-naca671215-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.5385   0.09351   0.08814  -0.0794   0.9826   0.0355
 -12.500  -0.5749   0.08239   0.07688  -0.0867   0.9794   0.0345
 -12.250  -0.6085   0.07448   0.06876  -0.0908   0.9765   0.0342
 -12.000  -0.6358   0.06866   0.06271  -0.0923   0.9740   0.0341
 -11.750  -0.6623   0.06492   0.05876  -0.0901   0.9698   0.0341
 -11.500  -0.6834   0.06142   0.05503  -0.0880   0.9665   0.0341
 -11.250  -0.6998   0.05830   0.05163  -0.0856   0.9637   0.0345
 -10.750  -0.7371   0.05413   0.04695  -0.0759   0.9553   0.0351
 -10.500  -0.7491   0.05196   0.04447  -0.0714   0.9520   0.0355
 -10.250  -0.7571   0.04974   0.04190  -0.0672   0.9493   0.0359
 -10.000  -0.7734   0.04840   0.04032  -0.0604   0.9452   0.0361
  -9.750  -0.7785   0.04639   0.03795  -0.0557   0.9420   0.0365
  -9.500  -0.7740   0.04424   0.03538  -0.0527   0.9395   0.0370
  -9.250  -0.7618   0.04220   0.03302  -0.0509   0.9379   0.0376
  -9.000  -0.7445   0.04064   0.03132  -0.0500   0.9367   0.0384
  -8.750  -0.7348   0.03955   0.03010  -0.0474   0.9350   0.0392
  -8.500  -0.7312   0.03868   0.02908  -0.0434   0.9325   0.0402
  -8.250  -0.7198   0.03767   0.02791  -0.0409   0.9303   0.0415
  -8.000  -0.7036   0.03666   0.02665  -0.0392   0.9282   0.0437
  -7.750  -0.6823   0.03550   0.02527  -0.0384   0.9269   0.0457
  -7.500  -0.6603   0.03451   0.02426  -0.0380   0.9258   0.0475
  -7.250  -0.6393   0.03375   0.02343  -0.0372   0.9246   0.0502
  -7.000  -0.6159   0.03301   0.02252  -0.0368   0.9236   0.0534
  -6.750  -0.5902   0.03210   0.02160  -0.0369   0.9227   0.0563
  -6.500  -0.5660   0.03147   0.02096  -0.0369   0.9216   0.0602
  -6.250  -0.5592   0.03103   0.02046  -0.0332   0.9188   0.0628
  -6.000  -0.5507   0.03061   0.01996  -0.0298   0.9166   0.0654
  -5.750  -0.5406   0.03003   0.01944  -0.0270   0.9143   0.0689
  -5.500  -0.5257   0.02958   0.01894  -0.0250   0.9119   0.0733
  -5.250  -0.5092   0.02912   0.01842  -0.0232   0.9100   0.0777
  -5.000  -0.4930   0.02864   0.01797  -0.0215   0.9084   0.0839
  -4.750  -0.4730   0.02823   0.01753  -0.0204   0.9070   0.0928
  -4.500  -0.4532   0.02782   0.01716  -0.0193   0.9053   0.1055
  -4.250  -0.4538   0.02750   0.01690  -0.0142   0.9016   0.1177
  -4.000  -0.4434   0.02701   0.01662  -0.0113   0.8987   0.1512
  -3.750  -0.4311   0.02621   0.01638  -0.0089   0.8961   0.2429
  -3.500  -0.3453   0.02729   0.01998  -0.0160   0.8998   0.7145
  -3.250  -0.3624   0.02703   0.01966  -0.0078   0.8950   0.7482
  -3.000  -0.3680   0.02682   0.01933  -0.0016   0.8915   0.7801
  -2.750  -0.3406   0.02782   0.02020  -0.0005   0.8900   0.8068
  -2.500  -0.3395   0.02867   0.02101   0.0058   0.8856   0.8309
  -2.250  -0.1885   0.03258   0.02467  -0.0140   0.8919   0.8681
  -1.750  -0.1373   0.03289   0.02479  -0.0139   0.8878   0.8818
  -1.500  -0.1187   0.03294   0.02477  -0.0126   0.8840   0.8871
  -1.250  -0.1139   0.03292   0.02469  -0.0086   0.8800   0.8949
  -1.000  -0.0785   0.03293   0.02462  -0.0107   0.8781   0.8970
  -0.750  -0.0452   0.03295   0.02457  -0.0124   0.8763   0.8995
  -0.500  -0.0140   0.03297   0.02453  -0.0137   0.8747   0.9023
  -0.250  -0.0308   0.03290   0.02445  -0.0055   0.8671   0.9102
   0.000  -0.0007   0.03290   0.02441  -0.0067   0.8642   0.9120
   0.250   0.0313   0.03290   0.02438  -0.0081   0.8617   0.9138
   0.500   0.0634   0.03290   0.02436  -0.0096   0.8597   0.9156
   0.750   0.0726   0.03291   0.02436  -0.0066   0.8537   0.9195
   1.000   0.0802   0.03282   0.02427  -0.0032   0.8482   0.9237
   1.250   0.1071   0.03278   0.02422  -0.0035   0.8452   0.9258
   1.500   0.1433   0.03276   0.02422  -0.0057   0.8432   0.9268
   1.750   0.1510   0.03279   0.02428  -0.0026   0.8348   0.9295
   2.000   0.1794   0.03274   0.02426  -0.0032   0.8309   0.9313
   2.250   0.2117   0.03266   0.02422  -0.0045   0.8282   0.9327
   2.500   0.2088   0.03260   0.02418   0.0009   0.8187   0.9368
   2.750   0.2317   0.03241   0.02403   0.0016   0.8141   0.9391
   3.000   0.2691   0.03224   0.02393  -0.0004   0.8113   0.9396
   3.250   0.2791   0.03223   0.02398   0.0022   0.8009   0.9416
   3.500   0.3156   0.03199   0.02383   0.0004   0.7971   0.9425
   3.750   0.3294   0.03187   0.02379   0.0026   0.7867   0.9450
   4.000   0.3669   0.03134   0.02337   0.0010   0.7816   0.9458
   4.250   0.3754   0.03102   0.02312   0.0045   0.7695   0.9484
   4.500   0.3842   0.03058   0.02275   0.0082   0.7585   0.9515
   4.750   0.4164   0.02983   0.02211   0.0078   0.7473   0.9526
   5.750   0.4958   0.02678   0.01948   0.0156   0.6537   0.9598
   6.000   0.5544   0.02425   0.01679   0.0133   0.5779   0.9592
   6.250   0.6021   0.02337   0.01481   0.0119   0.3969   0.9584
   6.500   0.6050   0.02417   0.01507   0.0158   0.3036   0.9615
   6.750   0.6118   0.02503   0.01545   0.0187   0.2202   0.9642
   7.000   0.6268   0.02596   0.01595   0.0199   0.1520   0.9657
   7.250   0.6427   0.02674   0.01651   0.0211   0.1178   0.9673
   7.500   0.6578   0.02746   0.01714   0.0225   0.0989   0.9693
   7.750   0.6714   0.02817   0.01778   0.0242   0.0874   0.9715
   8.000   0.6844   0.02877   0.01845   0.0261   0.0805   0.9741
   8.250   0.7020   0.02963   0.01928   0.0269   0.0741   0.9758
   8.500   0.7221   0.03038   0.02014   0.0272   0.0683   0.9776
   8.750   0.7397   0.03131   0.02106   0.0279   0.0642   0.9796
   9.000   0.7589   0.03214   0.02198   0.0286   0.0601   0.9817
   9.250   0.7768   0.03296   0.02286   0.0294   0.0563   0.9839
   9.500   0.7968   0.03401   0.02386   0.0297   0.0529   0.9855
   9.750   0.8199   0.03489   0.02494   0.0296   0.0490   0.9871
  10.000   0.8410   0.03589   0.02597   0.0297   0.0460   0.9890
  10.250   0.8632   0.03709   0.02722   0.0296   0.0432   0.9908
  10.500   0.8878   0.03837   0.02872   0.0295   0.0411   0.9927
  10.750   0.9098   0.03971   0.03021   0.0296   0.0390   0.9949
  11.000   0.9294   0.04100   0.03153   0.0296   0.0373   0.9976
  11.250   0.9511   0.04278   0.03350   0.0294   0.0358   1.0000
  11.500   0.9504   0.04395   0.03494   0.0333   0.0345   1.0000
  11.750   0.9503   0.04521   0.03641   0.0370   0.0337   1.0000
  12.000   0.9472   0.04650   0.03788   0.0410   0.0330   1.0000
  12.250   0.9437   0.04787   0.03944   0.0449   0.0326   1.0000
  12.500   0.9387   0.04938   0.04113   0.0486   0.0321   1.0000
  12.750   0.9353   0.05114   0.04306   0.0517   0.0317   1.0000
  13.000   0.9320   0.05318   0.04530   0.0543   0.0313   1.0000
  13.250   0.9285   0.05533   0.04761   0.0565   0.0309   1.0000
  13.500   0.9232   0.05781   0.05029   0.0585   0.0306   1.0000
  13.750   0.9166   0.06050   0.05315   0.0602   0.0303   1.0000
  14.000   0.9064   0.06361   0.05647   0.0618   0.0302   1.0000
  14.250   0.8932   0.06705   0.06013   0.0630   0.0301   1.0000
  14.500   0.8756   0.07111   0.06438   0.0638   0.0299   1.0000
  14.750   0.8575   0.07541   0.06890   0.0639   0.0300   1.0000
  15.000   0.8331   0.08077   0.07450   0.0630   0.0300   1.0000
  15.250   0.7959   0.08851   0.08258   0.0602   0.0303   1.0000
<< Back to NACA 67 (naca671215-il)

Polar data table (+)

Polar graphs


<< Back to NACA 67 (naca671215-il)