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NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NPL AIRFOIL FROM ARC CP 1372 (nplx-il)
Reynolds number: 200,000
Max Cl/Cd: 41.04 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nplx-il-200000.txt
Download as CSV file: xf-nplx-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NPL AIRFOIL FROM ARC CP 1372                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5872   0.10286   0.09886  -0.0355   1.0000   0.0549
 -10.250  -0.6080   0.09608   0.09207  -0.0411   1.0000   0.0550
 -10.000  -0.6287   0.09088   0.08682  -0.0447   1.0000   0.0551
  -9.750  -0.5955   0.08761   0.08370  -0.0394   1.0000   0.0564
  -9.500  -0.5871   0.08549   0.08161  -0.0380   1.0000   0.0574
  -9.250  -0.6004   0.07979   0.07591  -0.0415   1.0000   0.0577
  -9.000  -0.6148   0.07498   0.07109  -0.0438   1.0000   0.0583
  -8.750  -0.6418   0.07030   0.06637  -0.0456   1.0000   0.0582
  -8.500  -0.6634   0.06725   0.06328  -0.0444   1.0000   0.0585
  -8.250  -0.6748   0.06413   0.06010  -0.0433   1.0000   0.0592
  -8.000  -0.6832   0.06110   0.05698  -0.0419   1.0000   0.0601
  -7.750  -0.6893   0.05810   0.05385  -0.0403   1.0000   0.0615
  -7.500  -0.7389   0.04313   0.03738  -0.0348   1.0000   0.0379
  -7.250  -0.7250   0.04034   0.03459  -0.0335   1.0000   0.0360
  -7.000  -0.7179   0.03671   0.03069  -0.0315   1.0000   0.0347
  -6.750  -0.7099   0.03225   0.02572  -0.0291   1.0000   0.0330
  -6.500  -0.6969   0.02878   0.02174  -0.0270   1.0000   0.0324
  -6.250  -0.6800   0.02675   0.01946  -0.0254   1.0000   0.0327
  -6.000  -0.6618   0.02534   0.01790  -0.0240   1.0000   0.0336
  -5.750  -0.6429   0.02412   0.01648  -0.0225   1.0000   0.0355
  -5.500  -0.6233   0.02302   0.01510  -0.0210   1.0000   0.0370
  -5.250  -0.6041   0.02116   0.01320  -0.0197   1.0000   0.0388
  -5.000  -0.5845   0.02022   0.01227  -0.0184   1.0000   0.0412
  -4.750  -0.5641   0.01947   0.01137  -0.0170   1.0000   0.0453
  -4.500  -0.5451   0.01827   0.01027  -0.0158   1.0000   0.0497
  -4.250  -0.5244   0.01787   0.00977  -0.0147   1.0000   0.0549
  -4.000  -0.5049   0.01715   0.00916  -0.0137   1.0000   0.0616
  -3.750  -0.4845   0.01664   0.00862  -0.0127   1.0000   0.0680
  -3.500  -0.4638   0.01628   0.00830  -0.0119   1.0000   0.0756
  -3.250  -0.4431   0.01565   0.00770  -0.0110   1.0000   0.0829
  -3.000  -0.4217   0.01520   0.00726  -0.0102   1.0000   0.0912
  -2.750  -0.4001   0.01458   0.00671  -0.0097   1.0000   0.1040
  -2.500  -0.3738   0.01390   0.00617  -0.0101   0.9991   0.1315
  -2.250  -0.3453   0.01183   0.00588  -0.0121   0.9966   0.5316
  -2.000  -0.3111   0.01222   0.00632  -0.0132   0.9928   0.5889
  -1.750  -0.2776   0.01256   0.00666  -0.0142   0.9882   0.6166
  -1.500  -0.2404   0.01294   0.00703  -0.0160   0.9841   0.6374
  -1.250  -0.2086   0.01314   0.00722  -0.0167   0.9787   0.6527
  -1.000  -0.1745   0.01343   0.00755  -0.0178   0.9745   0.6689
  -0.750  -0.1412   0.01372   0.00785  -0.0188   0.9706   0.6840
  -0.500  -0.1119   0.01382   0.00802  -0.0190   0.9651   0.6926
  -0.250  -0.0737   0.01393   0.00811  -0.0211   0.9609   0.7020
   0.000  -0.0391   0.01394   0.00816  -0.0223   0.9539   0.7096
   0.250   0.0064   0.01381   0.00800  -0.0258   0.9472   0.7164
   0.500   0.0444   0.01362   0.00785  -0.0276   0.9391   0.7199
   0.750   0.0874   0.01340   0.00767  -0.0304   0.9331   0.7240
   1.000   0.1287   0.01323   0.00752  -0.0330   0.9278   0.7293
   1.250   0.1738   0.01283   0.00717  -0.0359   0.9186   0.7338
   1.500   0.2243   0.01229   0.00672  -0.0396   0.9091   0.7380
   1.750   0.2750   0.01175   0.00625  -0.0433   0.9002   0.7430
   2.000   0.3142   0.01124   0.00577  -0.0445   0.8812   0.7485
   2.250   0.3490   0.01073   0.00529  -0.0443   0.8486   0.7533
   2.500   0.3803   0.01050   0.00501  -0.0440   0.8101   0.7597
   2.750   0.4075   0.01042   0.00485  -0.0430   0.7639   0.7659
   3.000   0.4305   0.01049   0.00471  -0.0411   0.6774   0.7720
   3.250   0.4377   0.01165   0.00467  -0.0365   0.4351   0.7795
   3.500   0.4414   0.01354   0.00521  -0.0325   0.1607   0.7859
   3.750   0.4604   0.01452   0.00582  -0.0310   0.1087   0.7945
   4.000   0.4811   0.01512   0.00640  -0.0295   0.0942   0.8022
   4.250   0.5036   0.01565   0.00692  -0.0284   0.0862   0.8120
   4.500   0.5243   0.01639   0.00768  -0.0270   0.0813   0.8215
   4.750   0.5475   0.01686   0.00822  -0.0259   0.0773   0.8318
   5.000   0.5707   0.01739   0.00874  -0.0249   0.0733   0.8436
   5.250   0.5930   0.01851   0.00983  -0.0239   0.0698   0.8562
   5.500   0.6165   0.01916   0.01058  -0.0228   0.0683   0.8706
   5.750   0.6395   0.01980   0.01135  -0.0215   0.0668   0.8877
   6.000   0.6621   0.02052   0.01221  -0.0201   0.0655   0.9089
   6.250   0.6889   0.02138   0.01323  -0.0196   0.0640   0.9387
   6.500   0.7286   0.02245   0.01441  -0.0222   0.0617   1.0000
   6.750   0.7580   0.02363   0.01557  -0.0231   0.0599   1.0000
   7.000   0.7864   0.02540   0.01741  -0.0236   0.0589   1.0000
   7.250   0.8128   0.02763   0.01979  -0.0237   0.0584   1.0000
   7.500   0.8369   0.03001   0.02238  -0.0234   0.0582   1.0000
   7.750   0.8595   0.03214   0.02475  -0.0227   0.0583   1.0000
   8.000   0.8793   0.03485   0.02773  -0.0217   0.0581   1.0000
   8.250   0.8963   0.03799   0.03115  -0.0205   0.0580   1.0000
   8.500   0.9154   0.03953   0.03297  -0.0191   0.0586   1.0000
   8.750   0.8435   0.04939   0.04486  -0.0103   0.0970   1.0000
   9.000   0.8160   0.05067   0.04688  -0.0050   0.0911   1.0000
   9.250   0.8073   0.05485   0.05121  -0.0034   0.0891   1.0000
   9.500   0.7969   0.05870   0.05515  -0.0017   0.0876   1.0000
   9.750   0.7824   0.06243   0.05895   0.0001   0.0867   1.0000
  10.000   0.8965   0.07509   0.07096  -0.0065   0.0824   1.0000
  10.250   0.8533   0.07734   0.07354  -0.0028   0.0816   1.0000
  10.500   0.8107   0.08186   0.07823  -0.0025   0.0810   1.0000
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