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NACA 63-215 AIRFOIL (n63215-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-215 AIRFOIL (n63215-il)
Reynolds number: 100,000
Max Cl/Cd: 46.49 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n63215-il-100000-n5.txt
Download as CSV file: xf-n63215-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-215 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.6567   0.11452   0.10904  -0.0223   1.0000   0.0365
 -14.250  -0.6990   0.09962   0.09405  -0.0315   1.0000   0.0359
 -14.000  -0.7424   0.08722   0.08146  -0.0399   1.0000   0.0354
 -13.750  -0.7744   0.07859   0.07264  -0.0455   1.0000   0.0351
 -13.500  -0.8013   0.07167   0.06549  -0.0495   1.0000   0.0351
 -13.250  -0.8231   0.06605   0.05964  -0.0523   1.0000   0.0352
 -13.000  -0.8409   0.06130   0.05465  -0.0541   1.0000   0.0354
 -12.750  -0.8566   0.05712   0.05021  -0.0552   1.0000   0.0357
 -12.500  -0.8694   0.05347   0.04627  -0.0555   1.0000   0.0361
 -12.250  -0.8812   0.05027   0.04274  -0.0552   1.0000   0.0367
 -12.000  -0.8806   0.04772   0.04003  -0.0547   1.0000   0.0372
 -11.750  -0.8738   0.04582   0.03809  -0.0542   1.0000   0.0380
 -11.500  -0.8682   0.04389   0.03606  -0.0534   1.0000   0.0388
 -11.250  -0.8616   0.04201   0.03404  -0.0524   1.0000   0.0396
 -11.000  -0.8533   0.04016   0.03203  -0.0513   1.0000   0.0405
 -10.750  -0.8429   0.03839   0.03007  -0.0501   1.0000   0.0415
 -10.500  -0.8316   0.03676   0.02824  -0.0489   1.0000   0.0428
 -10.250  -0.8184   0.03526   0.02652  -0.0477   1.0000   0.0442
 -10.000  -0.8026   0.03395   0.02528  -0.0470   1.0000   0.0459
  -9.750  -0.7878   0.03279   0.02410  -0.0459   1.0000   0.0476
  -9.500  -0.7722   0.03162   0.02286  -0.0448   1.0000   0.0494
  -9.250  -0.7575   0.03057   0.02169  -0.0434   1.0000   0.0515
  -9.000  -0.7457   0.02955   0.02067  -0.0417   1.0000   0.0535
  -8.750  -0.7400   0.02877   0.01995  -0.0390   1.0000   0.0553
  -8.500  -0.7261   0.02792   0.01909  -0.0379   0.9936   0.0577
  -8.250  -0.6934   0.02684   0.01787  -0.0399   0.9823   0.0618
  -8.000  -0.6633   0.02562   0.01670  -0.0419   0.9712   0.0662
  -7.750  -0.6325   0.02462   0.01561  -0.0436   0.9604   0.0715
  -7.500  -0.6052   0.02356   0.01457  -0.0449   0.9487   0.0780
  -7.250  -0.5782   0.02264   0.01360  -0.0458   0.9375   0.0866
  -7.000  -0.5523   0.02172   0.01268  -0.0466   0.9270   0.0987
  -6.750  -0.5302   0.02078   0.01184  -0.0466   0.9156   0.1176
  -6.500  -0.5104   0.01986   0.01106  -0.0462   0.9040   0.1499
  -6.250  -0.4914   0.01885   0.01030  -0.0456   0.8936   0.2020
  -6.000  -0.4742   0.01783   0.00967  -0.0448   0.8833   0.2772
  -5.750  -0.4560   0.01714   0.00938  -0.0437   0.8731   0.3582
  -5.500  -0.4329   0.01686   0.00926  -0.0429   0.8651   0.4211
  -5.250  -0.4099   0.01678   0.00923  -0.0420   0.8554   0.4633
  -5.000  -0.3842   0.01679   0.00922  -0.0413   0.8483   0.4974
  -4.750  -0.3597   0.01686   0.00923  -0.0405   0.8389   0.5245
  -4.500  -0.3335   0.01696   0.00928  -0.0398   0.8322   0.5456
  -4.250  -0.3081   0.01705   0.00931  -0.0391   0.8234   0.5626
  -4.000  -0.2817   0.01710   0.00926  -0.0385   0.8165   0.5772
  -3.750  -0.2559   0.01716   0.00924  -0.0379   0.8085   0.5912
  -3.500  -0.2296   0.01718   0.00917  -0.0374   0.8013   0.6038
  -3.250  -0.2030   0.01722   0.00915  -0.0368   0.7944   0.6120
  -3.000  -0.1765   0.01714   0.00894  -0.0367   0.7867   0.6218
  -2.750  -0.1494   0.01714   0.00888  -0.0361   0.7810   0.6282
  -2.500  -0.1230   0.01709   0.00875  -0.0361   0.7727   0.6371
  -2.250  -0.0960   0.01706   0.00867  -0.0356   0.7665   0.6433
  -2.000  -0.0693   0.01704   0.00859  -0.0355   0.7594   0.6509
  -1.750  -0.0424   0.01700   0.00849  -0.0353   0.7524   0.6579
  -1.500  -0.0151   0.01697   0.00840  -0.0349   0.7470   0.6643
  -1.250   0.0117   0.01694   0.00832  -0.0350   0.7392   0.6724
  -1.000   0.0387   0.01693   0.00830  -0.0346   0.7332   0.6777
  -0.750   0.0657   0.01693   0.00826  -0.0345   0.7267   0.6850
  -0.500   0.0926   0.01693   0.00824  -0.0344   0.7199   0.6915
  -0.250   0.1200   0.01691   0.00819  -0.0340   0.7148   0.6977
   0.000   0.1469   0.01694   0.00820  -0.0342   0.7073   0.7058
   0.250   0.1735   0.01696   0.00825  -0.0337   0.7012   0.7113
   0.500   0.2009   0.01697   0.00824  -0.0336   0.6959   0.7185
   0.750   0.2273   0.01704   0.00833  -0.0334   0.6885   0.7254
   1.000   0.2543   0.01705   0.00836  -0.0331   0.6831   0.7319
   1.250   0.2815   0.01711   0.00843  -0.0332   0.6768   0.7400
   1.500   0.3072   0.01719   0.00857  -0.0327   0.6702   0.7461
   1.750   0.3351   0.01719   0.00856  -0.0326   0.6652   0.7540
   2.000   0.3604   0.01732   0.00878  -0.0322   0.6579   0.7608
   2.250   0.3870   0.01738   0.00887  -0.0319   0.6518   0.7685
   2.500   0.4140   0.01742   0.00895  -0.0316   0.6462   0.7760
   2.750   0.4388   0.01756   0.00918  -0.0311   0.6386   0.7836
   3.000   0.4661   0.01758   0.00923  -0.0309   0.6330   0.7917
   3.250   0.4906   0.01772   0.00948  -0.0303   0.6254   0.7994
   3.500   0.5170   0.01778   0.00960  -0.0300   0.6187   0.8081
   3.750   0.5424   0.01786   0.00976  -0.0293   0.6121   0.8160
   4.000   0.5675   0.01797   0.00998  -0.0289   0.6040   0.8251
   4.250   0.5934   0.01799   0.01005  -0.0282   0.5972   0.8336
   4.500   0.6172   0.01808   0.01026  -0.0275   0.5874   0.8429
   4.750   0.6416   0.01808   0.01036  -0.0266   0.5771   0.8529
   5.000   0.6667   0.01798   0.01030  -0.0257   0.5665   0.8621
   5.250   0.6893   0.01802   0.01047  -0.0246   0.5535   0.8732
   5.500   0.7118   0.01801   0.01058  -0.0234   0.5402   0.8846
   5.750   0.7343   0.01797   0.01063  -0.0222   0.5248   0.8964
   6.000   0.7568   0.01791   0.01065  -0.0210   0.5068   0.9096
   6.250   0.7800   0.01785   0.01062  -0.0199   0.4848   0.9244
   6.500   0.8037   0.01788   0.01070  -0.0193   0.4549   0.9413
   6.750   0.8309   0.01806   0.01086  -0.0196   0.4147   0.9613
   7.000   0.8587   0.01847   0.01110  -0.0204   0.3603   1.0000
   7.250   0.8722   0.01924   0.01155  -0.0189   0.3039   1.0000
   7.500   0.8824   0.02034   0.01229  -0.0173   0.2477   1.0000
   7.750   0.8911   0.02161   0.01323  -0.0156   0.1982   1.0000
   8.000   0.8995   0.02289   0.01427  -0.0139   0.1602   1.0000
   8.250   0.9067   0.02412   0.01533  -0.0120   0.1322   1.0000
   8.500   0.9131   0.02540   0.01648  -0.0101   0.1120   1.0000
   8.750   0.9205   0.02673   0.01772  -0.0085   0.0974   1.0000
   9.250   0.9363   0.02950   0.02045  -0.0058   0.0795   1.0000
   9.500   0.9435   0.03103   0.02195  -0.0046   0.0740   1.0000
   9.750   0.9531   0.03244   0.02342  -0.0036   0.0687   1.0000
  10.000   0.9599   0.03411   0.02505  -0.0027   0.0649   1.0000
  10.250   0.9705   0.03556   0.02658  -0.0018   0.0612   1.0000
  10.500   0.9806   0.03708   0.02814  -0.0011   0.0578   1.0000
  10.750   0.9890   0.03877   0.02982  -0.0004   0.0552   1.0000
  11.000   1.0007   0.04029   0.03144   0.0003   0.0524   1.0000
  11.250   1.0122   0.04186   0.03308   0.0009   0.0499   1.0000
  11.500   1.0223   0.04353   0.03477   0.0013   0.0477   1.0000
  11.750   1.0333   0.04526   0.03649   0.0019   0.0458   1.0000
  12.000   1.0458   0.04694   0.03834   0.0024   0.0438   1.0000
  12.250   1.0566   0.04874   0.04027   0.0028   0.0419   1.0000
  12.500   1.0664   0.05061   0.04219   0.0031   0.0404   1.0000
  12.750   1.0773   0.05248   0.04405   0.0033   0.0391   1.0000
  13.000   1.0890   0.05456   0.04626   0.0037   0.0381   1.0000
  13.250   1.0976   0.05695   0.04888   0.0040   0.0371   1.0000
  13.500   1.1041   0.05956   0.05170   0.0042   0.0362   1.0000
  13.750   1.1079   0.06238   0.05473   0.0041   0.0353   1.0000
  14.000   1.1098   0.06533   0.05786   0.0038   0.0345   1.0000
  14.250   1.1106   0.06840   0.06107   0.0034   0.0338   1.0000
  14.500   1.1111   0.07151   0.06429   0.0028   0.0331   1.0000
  14.750   1.1126   0.07461   0.06747   0.0021   0.0325   1.0000
  15.000   1.1079   0.07864   0.07166   0.0010   0.0320   1.0000
  15.250   1.0943   0.08389   0.07720  -0.0010   0.0317   1.0000
  15.500   1.0776   0.08990   0.08351  -0.0036   0.0315   1.0000
  15.750   1.0602   0.09640   0.09027  -0.0068   0.0314   1.0000
  16.000   1.0382   0.10409   0.09823  -0.0111   0.0313   1.0000
  16.250   1.0133   0.11293   0.10732  -0.0165   0.0313   1.0000
  16.500   0.9840   0.12350   0.11813  -0.0233   0.0315   1.0000
  16.750   0.9463   0.13732   0.13216  -0.0324   0.0318   1.0000
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