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NACA 642-015 AIRFOIL (n64015-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 642-015 AIRFOIL (n64015-il)
Reynolds number: 200,000
Max Cl/Cd: 44.98 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64015-il-200000-n5.txt
Download as CSV file: xf-n64015-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 642-015 AIRFOIL                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.8703   0.11308   0.10900  -0.0046   1.0000   0.0211
 -16.000  -0.9150   0.09889   0.09453  -0.0137   1.0000   0.0209
 -15.750  -0.9447   0.08935   0.08474  -0.0195   1.0000   0.0208
 -15.500  -0.9678   0.08178   0.07695  -0.0237   1.0000   0.0209
 -15.250  -0.9862   0.07551   0.07045  -0.0267   1.0000   0.0209
 -15.000  -1.0015   0.07008   0.06479  -0.0290   1.0000   0.0209
 -14.750  -1.0136   0.06540   0.05988  -0.0306   1.0000   0.0211
 -14.500  -1.0235   0.06117   0.05542  -0.0318   1.0000   0.0212
 -14.250  -1.0301   0.05752   0.05154  -0.0325   1.0000   0.0215
 -14.000  -1.0348   0.05412   0.04791  -0.0329   1.0000   0.0217
 -13.750  -1.0366   0.05119   0.04475  -0.0330   1.0000   0.0220
 -13.500  -1.0371   0.04852   0.04184  -0.0329   1.0000   0.0224
 -13.250  -1.0326   0.04614   0.03930  -0.0326   1.0000   0.0227
 -13.000  -1.0245   0.04421   0.03731  -0.0323   1.0000   0.0230
 -12.750  -1.0160   0.04244   0.03549  -0.0319   1.0000   0.0234
 -12.500  -1.0065   0.04075   0.03371  -0.0315   1.0000   0.0238
 -12.250  -0.9959   0.03913   0.03199  -0.0309   1.0000   0.0242
 -12.000  -0.9845   0.03757   0.03033  -0.0304   1.0000   0.0246
 -11.750  -0.9724   0.03611   0.02877  -0.0297   1.0000   0.0252
 -11.500  -0.9590   0.03471   0.02726  -0.0291   1.0000   0.0257
 -11.250  -0.9452   0.03338   0.02582  -0.0284   1.0000   0.0264
 -11.000  -0.9308   0.03213   0.02446  -0.0276   1.0000   0.0270
 -10.750  -0.9165   0.03091   0.02315  -0.0269   1.0000   0.0277
 -10.500  -0.9038   0.02963   0.02187  -0.0260   1.0000   0.0283
 -10.250  -0.8909   0.02851   0.02074  -0.0253   1.0000   0.0293
 -10.000  -0.8771   0.02747   0.01968  -0.0245   1.0000   0.0304
  -9.750  -0.8632   0.02645   0.01861  -0.0236   1.0000   0.0315
  -9.500  -0.8491   0.02547   0.01757  -0.0226   1.0000   0.0325
  -9.250  -0.8354   0.02450   0.01653  -0.0216   1.0000   0.0337
  -9.000  -0.8250   0.02341   0.01546  -0.0203   1.0000   0.0348
  -8.750  -0.8127   0.02253   0.01459  -0.0190   1.0000   0.0362
  -8.500  -0.7893   0.02169   0.01368  -0.0197   0.9586   0.0383
  -8.250  -0.7654   0.02097   0.01283  -0.0201   0.9340   0.0406
  -8.000  -0.7522   0.02020   0.01204  -0.0185   0.9128   0.0430
  -7.750  -0.7369   0.01963   0.01140  -0.0169   0.8960   0.0458
  -7.250  -0.7058   0.01849   0.01013  -0.0135   0.8693   0.0534
  -7.000  -0.6880   0.01799   0.00956  -0.0121   0.8574   0.0589
  -6.750  -0.6704   0.01741   0.00897  -0.0107   0.8468   0.0671
  -6.250  -0.6344   0.01621   0.00784  -0.0081   0.8270   0.1002
  -6.000  -0.6166   0.01553   0.00729  -0.0069   0.8182   0.1327
  -5.750  -0.5996   0.01470   0.00670  -0.0056   0.8090   0.1847
  -5.500  -0.5841   0.01374   0.00607  -0.0042   0.8006   0.2588
  -5.250  -0.5691   0.01273   0.00551  -0.0027   0.7920   0.3552
  -5.000  -0.5496   0.01222   0.00534  -0.0015   0.7846   0.4426
  -4.750  -0.5246   0.01206   0.00521  -0.0010   0.7768   0.4797
  -4.500  -0.4993   0.01196   0.00509  -0.0004   0.7700   0.5072
  -4.250  -0.4733   0.01190   0.00504  -0.0001   0.7620   0.5311
  -4.000  -0.4473   0.01189   0.00499   0.0004   0.7554   0.5510
  -3.750  -0.4205   0.01189   0.00497   0.0007   0.7478   0.5686
  -3.500  -0.3940   0.01193   0.00498   0.0011   0.7412   0.5861
  -3.250  -0.3667   0.01193   0.00494   0.0013   0.7349   0.5969
  -3.000  -0.3388   0.01188   0.00480   0.0012   0.7281   0.6033
  -2.750  -0.3110   0.01181   0.00464   0.0012   0.7224   0.6084
  -2.500  -0.2828   0.01176   0.00457   0.0012   0.7158   0.6133
  -2.250  -0.2548   0.01172   0.00445   0.0011   0.7093   0.6193
  -2.000  -0.2267   0.01167   0.00432   0.0011   0.7037   0.6243
  -1.750  -0.1983   0.01162   0.00426   0.0009   0.6971   0.6279
  -1.500  -0.1702   0.01158   0.00417   0.0008   0.6916   0.6324
  -1.250  -0.1419   0.01156   0.00408   0.0007   0.6865   0.6376
  -0.750  -0.0851   0.01149   0.00400   0.0004   0.6755   0.6457
  -0.500  -0.0568   0.01149   0.00395   0.0003   0.6710   0.6505
   0.000   0.0000   0.01146   0.00394   0.0000   0.6599   0.6599
   0.500   0.0568   0.01149   0.00395  -0.0003   0.6505   0.6710
   0.750   0.0851   0.01149   0.00400  -0.0004   0.6457   0.6755
   1.000   0.1134   0.01152   0.00404  -0.0005   0.6417   0.6806
   1.250   0.1418   0.01156   0.00408  -0.0007   0.6376   0.6865
   1.500   0.1701   0.01158   0.00417  -0.0008   0.6324   0.6916
   1.750   0.1983   0.01162   0.00426  -0.0009   0.6279   0.6971
   2.000   0.2267   0.01167   0.00432  -0.0011   0.6243   0.7038
   2.250   0.2548   0.01172   0.00445  -0.0011   0.6193   0.7093
   2.500   0.2828   0.01176   0.00457  -0.0012   0.6133   0.7157
   2.750   0.3110   0.01181   0.00464  -0.0012   0.6084   0.7224
   3.000   0.3388   0.01188   0.00480  -0.0012   0.6034   0.7281
   3.250   0.3667   0.01193   0.00494  -0.0013   0.5969   0.7349
   3.500   0.3940   0.01193   0.00498  -0.0011   0.5861   0.7412
   3.750   0.4205   0.01189   0.00497  -0.0007   0.5686   0.7478
   4.000   0.4473   0.01189   0.00499  -0.0004   0.5510   0.7554
   4.250   0.4733   0.01190   0.00504   0.0001   0.5311   0.7620
   4.500   0.4994   0.01196   0.00509   0.0004   0.5071   0.7700
   4.750   0.5246   0.01206   0.00520   0.0010   0.4795   0.7768
   5.000   0.5496   0.01222   0.00534   0.0015   0.4424   0.7846
   5.250   0.5691   0.01273   0.00551   0.0027   0.3551   0.7920
   5.500   0.5841   0.01374   0.00607   0.0042   0.2589   0.8006
   5.750   0.5996   0.01471   0.00670   0.0056   0.1842   0.8090
   6.000   0.6167   0.01553   0.00728   0.0069   0.1328   0.8182
   6.250   0.6345   0.01621   0.00785   0.0081   0.1000   0.8270
   6.750   0.6706   0.01741   0.00897   0.0107   0.0670   0.8467
   7.000   0.6882   0.01799   0.00956   0.0120   0.0588   0.8574
   7.250   0.7060   0.01850   0.01013   0.0134   0.0533   0.8694
   7.500   0.7208   0.01912   0.01077   0.0152   0.0488   0.8820
   7.750   0.7372   0.01963   0.01139   0.0168   0.0458   0.8960
   8.000   0.7525   0.02021   0.01205   0.0184   0.0430   0.9127
   8.250   0.7659   0.02097   0.01283   0.0200   0.0406   0.9339
   8.500   0.7898   0.02168   0.01368   0.0196   0.0381   0.9584
   8.750   0.8133   0.02253   0.01458   0.0189   0.0361   1.0000
   9.000   0.8256   0.02341   0.01546   0.0201   0.0348   1.0000
   9.250   0.8355   0.02455   0.01658   0.0215   0.0336   1.0000
   9.500   0.8497   0.02548   0.01757   0.0225   0.0326   1.0000
   9.750   0.8638   0.02646   0.01862   0.0235   0.0314   1.0000
  10.000   0.8779   0.02748   0.01969   0.0243   0.0303   1.0000
  10.250   0.8917   0.02850   0.02073   0.0251   0.0292   1.0000
  10.500   0.9047   0.02962   0.02186   0.0259   0.0283   1.0000
  10.750   0.9172   0.03094   0.02316   0.0267   0.0276   1.0000
  11.000   0.9318   0.03213   0.02447   0.0275   0.0270   1.0000
  11.250   0.9461   0.03338   0.02583   0.0282   0.0263   1.0000
  11.500   0.9602   0.03472   0.02727   0.0289   0.0257   1.0000
  11.750   0.9734   0.03611   0.02877   0.0296   0.0251   1.0000
  12.000   0.9862   0.03758   0.03034   0.0302   0.0247   1.0000
  12.250   0.9971   0.03913   0.03199   0.0308   0.0241   1.0000
  12.500   1.0079   0.04076   0.03372   0.0313   0.0238   1.0000
  12.750   1.0173   0.04244   0.03549   0.0317   0.0234   1.0000
  13.000   1.0259   0.04422   0.03732   0.0321   0.0230   1.0000
  13.250   1.0340   0.04618   0.03936   0.0324   0.0227   1.0000
  13.500   1.0384   0.04847   0.04179   0.0327   0.0223   1.0000
  13.750   1.0383   0.05116   0.04472   0.0328   0.0220   1.0000
  14.000   1.0357   0.05421   0.04800   0.0327   0.0217   1.0000
  14.250   1.0314   0.05753   0.05157   0.0323   0.0214   1.0000
  14.500   1.0248   0.06122   0.05548   0.0315   0.0212   1.0000
  14.750   1.0152   0.06541   0.05989   0.0304   0.0211   1.0000
  15.000   1.0033   0.07006   0.06477   0.0288   0.0210   1.0000
  15.250   0.9881   0.07549   0.07042   0.0265   0.0208   1.0000
  15.500   0.9692   0.08184   0.07701   0.0234   0.0208   1.0000
  15.750   0.9455   0.08954   0.08495   0.0191   0.0207   1.0000
  16.000   0.9159   0.09910   0.09475   0.0133   0.0208   1.0000
  16.250   0.8698   0.11371   0.10965   0.0039   0.0211   1.0000
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