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NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NPL AIRFOIL FROM ARC CP 1372 (nplx-il)
Reynolds number: 500,000
Max Cl/Cd: 49.11 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nplx-il-500000.txt
Download as CSV file: xf-nplx-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4773   0.08788   0.08549  -0.0332   1.0000   0.0278
 -10.000  -0.4899   0.08091   0.07853  -0.0360   1.0000   0.0279
  -9.750  -0.8382   0.04431   0.04065  -0.0471   1.0000   0.0168
  -9.500  -0.8369   0.04224   0.03845  -0.0449   1.0000   0.0163
  -9.250  -0.8449   0.03904   0.03508  -0.0423   1.0000   0.0160
  -9.000  -0.8526   0.03528   0.03103  -0.0393   1.0000   0.0157
  -8.750  -0.8552   0.03159   0.02699  -0.0364   1.0000   0.0153
  -8.500  -0.8538   0.02780   0.02276  -0.0336   1.0000   0.0150
  -8.250  -0.8449   0.02504   0.01965  -0.0314   1.0000   0.0148
  -8.000  -0.8316   0.02312   0.01747  -0.0295   1.0000   0.0148
  -7.750  -0.8162   0.02161   0.01578  -0.0278   1.0000   0.0149
  -7.500  -0.7997   0.02038   0.01439  -0.0261   1.0000   0.0150
  -7.250  -0.7825   0.01932   0.01322  -0.0246   1.0000   0.0152
  -7.000  -0.7647   0.01840   0.01220  -0.0231   1.0000   0.0156
  -6.750  -0.7466   0.01758   0.01129  -0.0216   1.0000   0.0159
  -6.500  -0.7281   0.01687   0.01049  -0.0202   1.0000   0.0162
  -6.250  -0.7025   0.01601   0.00955  -0.0203   0.9991   0.0166
  -6.000  -0.6704   0.01509   0.00862  -0.0219   0.9970   0.0174
  -5.750  -0.6363   0.01457   0.00809  -0.0237   0.9949   0.0185
  -5.500  -0.6027   0.01404   0.00751  -0.0253   0.9927   0.0198
  -5.250  -0.5704   0.01335   0.00682  -0.0267   0.9897   0.0218
  -5.000  -0.5359   0.01291   0.00637  -0.0284   0.9872   0.0254
  -4.750  -0.5008   0.01249   0.00598  -0.0303   0.9852   0.0318
  -4.500  -0.4655   0.01224   0.00575  -0.0322   0.9833   0.0364
  -4.250  -0.4352   0.01184   0.00538  -0.0330   0.9791   0.0413
  -4.000  -0.4009   0.01160   0.00512  -0.0346   0.9763   0.0461
  -3.750  -0.3656   0.01120   0.00476  -0.0364   0.9741   0.0524
  -3.500  -0.3291   0.01085   0.00444  -0.0385   0.9726   0.0601
  -3.250  -0.3000   0.01052   0.00416  -0.0389   0.9674   0.0705
  -3.000  -0.2667   0.01017   0.00389  -0.0403   0.9642   0.0904
  -2.750  -0.2319   0.00965   0.00359  -0.0421   0.9620   0.1374
  -2.500  -0.2016   0.00777   0.00302  -0.0443   0.9601   0.4731
  -2.250  -0.1698   0.00762   0.00299  -0.0451   0.9563   0.5259
  -2.000  -0.1376   0.00755   0.00295  -0.0459   0.9521   0.5489
  -1.750  -0.1013   0.00747   0.00289  -0.0476   0.9496   0.5646
  -1.500  -0.0618   0.00736   0.00279  -0.0498   0.9471   0.5777
  -1.250  -0.0253   0.00727   0.00268  -0.0514   0.9426   0.5893
  -1.000   0.0070   0.00721   0.00263  -0.0520   0.9356   0.6017
  -0.750   0.0434   0.00712   0.00257  -0.0536   0.9311   0.6118
  -0.500   0.0736   0.00708   0.00251  -0.0539   0.9230   0.6174
  -0.250   0.1086   0.00696   0.00239  -0.0551   0.9152   0.6227
   0.000   0.1380   0.00690   0.00233  -0.0550   0.9022   0.6284
   0.250   0.1672   0.00690   0.00229  -0.0550   0.8888   0.6349
   0.500   0.1956   0.00684   0.00225  -0.0548   0.8742   0.6401
   0.750   0.2238   0.00682   0.00220  -0.0545   0.8577   0.6439
   1.000   0.2514   0.00684   0.00213  -0.0541   0.8354   0.6482
   1.250   0.2777   0.00688   0.00209  -0.0534   0.8098   0.6524
   1.500   0.3037   0.00692   0.00209  -0.0527   0.7840   0.6564
   1.750   0.3286   0.00700   0.00208  -0.0517   0.7478   0.6608
   2.000   0.3521   0.00717   0.00207  -0.0505   0.6943   0.6656
   2.250   0.3674   0.00779   0.00211  -0.0477   0.5524   0.6701
   2.500   0.3826   0.00870   0.00237  -0.0453   0.3932   0.6747
   2.750   0.4026   0.00942   0.00260  -0.0440   0.2767   0.6801
   3.000   0.4210   0.01039   0.00291  -0.0425   0.1252   0.6856
   3.250   0.4448   0.01082   0.00320  -0.0417   0.0876   0.6912
   3.500   0.4694   0.01123   0.00352  -0.0410   0.0692   0.6977
   3.750   0.4951   0.01147   0.00376  -0.0405   0.0617   0.7037
   4.000   0.5201   0.01180   0.00410  -0.0398   0.0562   0.7102
   4.250   0.5459   0.01205   0.00437  -0.0394   0.0532   0.7173
   4.500   0.5710   0.01233   0.00468  -0.0387   0.0506   0.7241
   5.000   0.6187   0.01323   0.00567  -0.0370   0.0469   0.7394
   5.250   0.6436   0.01358   0.00607  -0.0364   0.0457   0.7483
   5.500   0.6681   0.01390   0.00646  -0.0357   0.0443   0.7570
   5.750   0.6927   0.01425   0.00685  -0.0350   0.0429   0.7666
   6.000   0.7168   0.01466   0.00731  -0.0342   0.0418   0.7769
   6.250   0.7399   0.01520   0.00791  -0.0333   0.0408   0.7876
   6.500   0.7617   0.01625   0.00902  -0.0322   0.0396   0.7994
   6.750   0.7851   0.01711   0.00999  -0.0314   0.0390   0.8127
   7.000   0.8091   0.01763   0.01063  -0.0306   0.0385   0.8280
   7.250   0.8324   0.01824   0.01138  -0.0296   0.0380   0.8464
   7.500   0.8548   0.01886   0.01216  -0.0284   0.0374   0.8710
   7.750   0.8745   0.01936   0.01285  -0.0267   0.0366   0.9088
   8.000   0.9046   0.02006   0.01371  -0.0272   0.0358   1.0000
   8.250   0.9294   0.02098   0.01468  -0.0268   0.0352   1.0000
   8.500   0.9534   0.02194   0.01572  -0.0263   0.0346   1.0000
   8.750   0.9767   0.02293   0.01679  -0.0257   0.0340   1.0000
   9.000   0.9994   0.02403   0.01796  -0.0251   0.0335   1.0000
   9.250   1.0210   0.02545   0.01947  -0.0244   0.0331   1.0000
   9.500   1.0402   0.02763   0.02182  -0.0234   0.0326   1.0000
   9.750   1.0504   0.03145   0.02603  -0.0215   0.0319   1.0000
  10.000   1.0685   0.03200   0.02677  -0.0200   0.0314   1.0000
  10.250   1.0834   0.03349   0.02850  -0.0183   0.0307   1.0000
  10.500   1.0938   0.03572   0.03102  -0.0163   0.0301   1.0000
  10.750   1.0996   0.03840   0.03401  -0.0138   0.0295   1.0000
  11.000   1.0985   0.04179   0.03772  -0.0109   0.0292   1.0000
  11.250   1.0881   0.04587   0.04215  -0.0073   0.0289   1.0000
  11.500   1.0662   0.05026   0.04686  -0.0029   0.0288   1.0000
  11.750   1.0292   0.05518   0.05207   0.0022   0.0289   1.0000
  12.000   0.9800   0.06187   0.05905   0.0046   0.0294   1.0000
  12.250   0.9347   0.06942   0.06682   0.0028   0.0300   1.0000
  12.500   0.8847   0.08046   0.07803  -0.0046   0.0306   1.0000
  12.750   0.8454   0.09365   0.09127  -0.0146   0.0317   1.0000
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