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NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NPL AIRFOIL FROM ARC CP 1372 (nplx-il)
Reynolds number: 200,000
Max Cl/Cd: 38.16 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nplx-il-200000-n5.txt
Download as CSV file: xf-nplx-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.6272   0.09226   0.08814  -0.0309   1.0000   0.0156
 -10.750  -0.6713   0.07516   0.07101  -0.0418   1.0000   0.0151
 -10.500  -0.7200   0.06303   0.05867  -0.0488   1.0000   0.0148
 -10.250  -0.7572   0.05556   0.05096  -0.0514   1.0000   0.0146
 -10.000  -0.7888   0.05017   0.04533  -0.0512   1.0000   0.0145
  -9.750  -0.8172   0.04626   0.04118  -0.0483   1.0000   0.0144
  -9.500  -0.8339   0.04239   0.03699  -0.0454   1.0000   0.0145
  -9.250  -0.8423   0.03876   0.03300  -0.0428   1.0000   0.0146
  -9.000  -0.8425   0.03575   0.02964  -0.0404   1.0000   0.0148
  -8.750  -0.8376   0.03309   0.02665  -0.0383   1.0000   0.0149
  -8.500  -0.8286   0.03079   0.02405  -0.0364   1.0000   0.0152
  -8.250  -0.8167   0.02881   0.02178  -0.0346   1.0000   0.0155
  -8.000  -0.8028   0.02706   0.01977  -0.0329   1.0000   0.0159
  -7.750  -0.7875   0.02554   0.01801  -0.0312   1.0000   0.0162
  -7.500  -0.7714   0.02425   0.01659  -0.0297   1.0000   0.0166
  -7.250  -0.7546   0.02334   0.01563  -0.0283   1.0000   0.0170
  -7.000  -0.7367   0.02268   0.01494  -0.0270   1.0000   0.0178
  -6.750  -0.7187   0.02192   0.01410  -0.0256   1.0000   0.0187
  -6.500  -0.7006   0.02106   0.01311  -0.0242   1.0000   0.0198
  -6.250  -0.6828   0.02022   0.01221  -0.0228   1.0000   0.0208
  -6.000  -0.6644   0.01958   0.01157  -0.0215   1.0000   0.0218
  -5.750  -0.6441   0.01888   0.01082  -0.0205   0.9997   0.0235
  -5.500  -0.6129   0.01805   0.00992  -0.0218   0.9968   0.0257
  -5.250  -0.5805   0.01747   0.00932  -0.0233   0.9940   0.0285
  -5.000  -0.5500   0.01683   0.00864  -0.0244   0.9905   0.0318
  -4.750  -0.5181   0.01641   0.00820  -0.0257   0.9871   0.0363
  -4.500  -0.4856   0.01593   0.00773  -0.0272   0.9843   0.0409
  -4.250  -0.4557   0.01552   0.00729  -0.0280   0.9802   0.0463
  -4.000  -0.4244   0.01510   0.00690  -0.0292   0.9762   0.0532
  -3.750  -0.3914   0.01462   0.00644  -0.0307   0.9732   0.0598
  -3.500  -0.3618   0.01423   0.00605  -0.0314   0.9687   0.0677
  -3.250  -0.3313   0.01385   0.00567  -0.0322   0.9644   0.0787
  -3.000  -0.2987   0.01340   0.00529  -0.0336   0.9612   0.0963
  -2.750  -0.2666   0.01291   0.00495  -0.0350   0.9579   0.1281
  -2.500  -0.2394   0.01221   0.00455  -0.0355   0.9522   0.2056
  -2.250  -0.2128   0.01085   0.00439  -0.0365   0.9485   0.5034
  -2.000  -0.1787   0.01081   0.00439  -0.0377   0.9459   0.5411
  -1.750  -0.1493   0.01079   0.00440  -0.0379   0.9409   0.5623
  -1.500  -0.1185   0.01081   0.00443  -0.0383   0.9364   0.5836
  -1.250  -0.0851   0.01083   0.00445  -0.0393   0.9333   0.6027
  -1.000  -0.0501   0.01081   0.00446  -0.0407   0.9309   0.6136
  -0.750  -0.0205   0.01079   0.00444  -0.0409   0.9249   0.6223
  -0.500   0.0130   0.01074   0.00440  -0.0419   0.9197   0.6305
  -0.250   0.0514   0.01062   0.00427  -0.0438   0.9152   0.6376
   0.000   0.0818   0.01051   0.00419  -0.0441   0.9053   0.6416
   0.250   0.1190   0.01037   0.00404  -0.0457   0.8979   0.6456
   0.500   0.1501   0.01029   0.00395  -0.0461   0.8876   0.6498
   0.750   0.1824   0.01018   0.00386  -0.0467   0.8754   0.6534
   1.000   0.2156   0.01005   0.00375  -0.0473   0.8581   0.6569
   1.250   0.2489   0.00994   0.00362  -0.0479   0.8379   0.6611
   1.500   0.2791   0.00991   0.00356  -0.0480   0.8172   0.6660
   1.750   0.3083   0.00990   0.00351  -0.0478   0.7894   0.6704
   2.000   0.3345   0.00996   0.00344  -0.0468   0.7386   0.6750
   2.250   0.3546   0.01034   0.00327  -0.0445   0.5977   0.6802
   2.500   0.3657   0.01140   0.00342  -0.0411   0.4143   0.6851
   2.750   0.3838   0.01215   0.00369  -0.0394   0.3029   0.6898
   3.000   0.4036   0.01290   0.00395  -0.0381   0.1895   0.6953
   3.250   0.4249   0.01361   0.00429  -0.0371   0.1143   0.7013
   3.500   0.4488   0.01400   0.00460  -0.0363   0.0918   0.7070
   3.750   0.4734   0.01435   0.00492  -0.0357   0.0783   0.7140
   4.000   0.4976   0.01471   0.00525  -0.0350   0.0686   0.7204
   4.250   0.5224   0.01502   0.00561  -0.0343   0.0625   0.7275
   4.500   0.5462   0.01545   0.00603  -0.0336   0.0580   0.7346
   4.750   0.5703   0.01580   0.00646  -0.0328   0.0551   0.7419
   5.000   0.5944   0.01618   0.00689  -0.0320   0.0524   0.7499
   5.250   0.6180   0.01657   0.00733  -0.0312   0.0500   0.7585
   5.500   0.6403   0.01715   0.00790  -0.0302   0.0477   0.7677
   5.750   0.6639   0.01757   0.00842  -0.0294   0.0462   0.7781
   6.000   0.6868   0.01808   0.00903  -0.0283   0.0449   0.7887
   6.250   0.7096   0.01862   0.00966  -0.0274   0.0436   0.8004
   6.500   0.7322   0.01919   0.01030  -0.0264   0.0425   0.8133
   6.750   0.7549   0.01978   0.01097  -0.0254   0.0416   0.8279
   7.000   0.7769   0.02039   0.01165  -0.0243   0.0406   0.8453
   7.250   0.7982   0.02122   0.01254  -0.0231   0.0395   0.8678
   7.500   0.8202   0.02190   0.01338  -0.0219   0.0386   0.8981
   7.750   0.8500   0.02269   0.01439  -0.0224   0.0376   0.9681
   8.000   0.8746   0.02369   0.01550  -0.0221   0.0368   1.0000
   8.250   0.8987   0.02478   0.01670  -0.0216   0.0360   1.0000
   8.500   0.9220   0.02592   0.01798  -0.0211   0.0353   1.0000
   8.750   0.9446   0.02713   0.01933  -0.0204   0.0347   1.0000
   9.000   0.9663   0.02831   0.02063  -0.0197   0.0341   1.0000
   9.250   0.9872   0.02943   0.02185  -0.0189   0.0334   1.0000
   9.500   1.0075   0.03057   0.02306  -0.0182   0.0327   1.0000
   9.750   1.0254   0.03248   0.02507  -0.0173   0.0320   1.0000
  10.000   1.0407   0.03419   0.02713  -0.0157   0.0315   1.0000
  10.250   1.0529   0.03640   0.02970  -0.0140   0.0311   1.0000
  10.500   1.0611   0.03900   0.03268  -0.0119   0.0306   1.0000
  10.750   1.0645   0.04197   0.03603  -0.0094   0.0301   1.0000
  11.000   1.0626   0.04522   0.03966  -0.0067   0.0297   1.0000
  11.250   1.0552   0.04858   0.04337  -0.0037   0.0293   1.0000
  11.500   1.0412   0.05167   0.04672  -0.0001   0.0290   1.0000
  11.750   1.0232   0.05502   0.05031   0.0030   0.0287   1.0000
  12.000   1.0001   0.05907   0.05460   0.0049   0.0285   1.0000
  12.250   0.9685   0.06467   0.06043   0.0048   0.0285   1.0000
  12.500   0.9105   0.07587   0.07194  -0.0010   0.0288   1.0000
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