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NPL 9510 AIRFOIL (npl9510-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NPL 9510 AIRFOIL (npl9510-il)
Reynolds number: 50,000
Max Cl/Cd: 17 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-npl9510-il-50000-n5.txt
Download as CSV file: xf-npl9510-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NPL 9510 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7586   0.10159   0.09304  -0.0315   1.0000   0.0720
 -12.500  -0.8055   0.08829   0.07961  -0.0397   1.0000   0.0711
 -12.250  -0.8441   0.07848   0.06961  -0.0456   1.0000   0.0704
 -12.000  -0.8706   0.07156   0.06249  -0.0493   1.0000   0.0704
 -11.750  -0.8893   0.06621   0.05692  -0.0514   1.0000   0.0710
 -11.500  -0.9031   0.06177   0.05224  -0.0526   1.0000   0.0718
 -11.250  -0.9135   0.05796   0.04818  -0.0530   1.0000   0.0728
 -11.000  -0.9210   0.05460   0.04450  -0.0527   1.0000   0.0740
 -10.750  -0.9148   0.05208   0.04186  -0.0521   1.0000   0.0757
 -10.500  -0.9050   0.05022   0.03998  -0.0514   1.0000   0.0783
 -10.250  -0.8972   0.04811   0.03773  -0.0508   1.0000   0.0815
 -10.000  -0.8890   0.04582   0.03511  -0.0500   1.0000   0.0852
  -9.750  -0.8746   0.04434   0.03368  -0.0487   1.0000   0.0890
  -9.500  -0.8623   0.04273   0.03197  -0.0476   1.0000   0.0941
  -9.250  -0.8488   0.04116   0.03029  -0.0463   1.0000   0.0999
  -9.000  -0.8359   0.03975   0.02888  -0.0451   1.0000   0.1064
  -8.750  -0.8230   0.03829   0.02738  -0.0438   1.0000   0.1143
  -8.500  -0.8100   0.03684   0.02582  -0.0426   1.0000   0.1242
  -8.250  -0.7976   0.03540   0.02448  -0.0416   1.0000   0.1349
  -8.000  -0.7846   0.03391   0.02304  -0.0407   1.0000   0.1483
  -7.750  -0.7709   0.03240   0.02158  -0.0401   1.0000   0.1650
  -7.500  -0.7557   0.03089   0.02010  -0.0397   1.0000   0.1852
  -7.250  -0.7398   0.02936   0.01879  -0.0396   1.0000   0.2083
  -7.000  -0.7219   0.02791   0.01756  -0.0398   1.0000   0.2385
  -6.750  -0.7023   0.02669   0.01665  -0.0399   1.0000   0.2780
  -6.500  -0.6818   0.02607   0.01637  -0.0393   1.0000   0.3239
  -6.250  -0.6606   0.02609   0.01660  -0.0378   1.0000   0.3674
  -6.000  -0.6382   0.02629   0.01680  -0.0364   1.0000   0.4042
  -5.750  -0.6157   0.02661   0.01705  -0.0349   1.0000   0.4324
  -5.500  -0.5918   0.02667   0.01693  -0.0343   1.0000   0.4578
  -5.250  -0.5698   0.02704   0.01720  -0.0325   1.0000   0.4761
  -5.000  -0.5476   0.02731   0.01736  -0.0310   1.0000   0.4930
  -4.750  -0.5252   0.02751   0.01743  -0.0296   1.0000   0.5090
  -4.500  -0.5024   0.02760   0.01741  -0.0285   1.0000   0.5243
  -4.250  -0.4814   0.02783   0.01759  -0.0266   1.0000   0.5366
  -4.000  -0.4609   0.02804   0.01774  -0.0245   1.0000   0.5480
  -3.750  -0.4388   0.02809   0.01772  -0.0232   1.0000   0.5615
  -3.500  -0.4159   0.02807   0.01762  -0.0223   1.0000   0.5757
  -3.250  -0.3968   0.02826   0.01781  -0.0198   1.0000   0.5856
  -3.000  -0.3737   0.02808   0.01756  -0.0191   1.0000   0.5962
  -2.750  -0.3500   0.02783   0.01726  -0.0186   1.0000   0.6051
  -2.500  -0.3252   0.02751   0.01689  -0.0185   1.0000   0.6130
  -2.250  -0.3017   0.02727   0.01662  -0.0179   1.0000   0.6199
  -2.000  -0.2737   0.02686   0.01615  -0.0189   1.0000   0.6283
  -1.750  -0.2512   0.02668   0.01598  -0.0179   1.0000   0.6338
  -1.500  -0.2236   0.02637   0.01563  -0.0187   1.0000   0.6415
  -1.250  -0.1983   0.02613   0.01541  -0.0187   1.0000   0.6474
  -1.000  -0.1743   0.02595   0.01526  -0.0183   1.0000   0.6532
  -0.750  -0.1445   0.02568   0.01498  -0.0197   1.0000   0.6609
  -0.500  -0.1210   0.02555   0.01493  -0.0191   1.0000   0.6656
  -0.250  -0.0956   0.02543   0.01487  -0.0190   1.0000   0.6716
   0.000  -0.0651   0.02527   0.01475  -0.0206   1.0000   0.6788
   0.250  -0.0417   0.02521   0.01481  -0.0200   1.0000   0.6834
   0.500  -0.0157   0.02515   0.01487  -0.0201   1.0000   0.6893
   0.750   0.0144   0.02511   0.01492  -0.0215   1.0000   0.6962
   1.000   0.0382   0.02511   0.01509  -0.0211   1.0000   0.7009
   1.250   0.0645   0.02514   0.01528  -0.0214   1.0000   0.7069
   1.500   0.0935   0.02521   0.01552  -0.0225   1.0000   0.7135
   1.750   0.1175   0.02530   0.01584  -0.0222   1.0000   0.7185
   2.000   0.1441   0.02544   0.01622  -0.0226   1.0000   0.7248
   2.250   0.3113   0.02543   0.01337  -0.0399   0.1727   0.7308
   2.500   0.3340   0.02633   0.01402  -0.0391   0.1363   0.7359
   2.750   0.3610   0.02709   0.01472  -0.0391   0.1194   0.7422
   3.000   0.3885   0.02783   0.01544  -0.0391   0.1080   0.7481
   3.250   0.4166   0.02856   0.01625  -0.0389   0.1004   0.7539
   3.500   0.4509   0.02949   0.01722  -0.0400   0.0940   0.7607
   3.750   0.4819   0.03030   0.01815  -0.0401   0.0878   0.7665
   4.000   0.5142   0.03151   0.01932  -0.0407   0.0841   0.7732
   4.250   0.5466   0.03278   0.02082  -0.0412   0.0809   0.7799
   4.500   0.5749   0.03399   0.02226  -0.0409   0.0770   0.7865
   5.000   0.6303   0.03708   0.02566  -0.0408   0.0725   0.8008
   5.250   0.6571   0.03908   0.02797  -0.0407   0.0708   0.8087
   5.500   0.6803   0.04102   0.03047  -0.0396   0.0685   0.8159
   5.750   0.7032   0.04323   0.03311  -0.0389   0.0665   0.8243
   6.000   0.7230   0.04567   0.03599  -0.0377   0.0658   0.8323
   6.500   0.7575   0.05113   0.04231  -0.0353   0.0645   0.8504
   6.750   0.7725   0.05374   0.04526  -0.0342   0.0633   0.8606
   7.000   0.7876   0.05615   0.04784  -0.0332   0.0619   0.8725
   7.250   0.7994   0.05904   0.05093  -0.0320   0.0610   0.8858
   7.500   0.8058   0.06254   0.05489  -0.0303   0.0609   0.9013
   7.750   0.8126   0.06614   0.05883  -0.0291   0.0610   0.9249
   8.250   0.7970   0.07785   0.07164  -0.0292   0.0641   1.0000
   8.500   0.7874   0.08371   0.07772  -0.0306   0.0656   1.0000
   8.750   0.7759   0.08914   0.08326  -0.0323   0.0669   1.0000
   9.000   0.7660   0.09476   0.08893  -0.0349   0.0681   1.0000
   9.250   0.7596   0.10056   0.09474  -0.0384   0.0692   1.0000
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