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NPL 9510 AIRFOIL (npl9510-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NPL 9510 AIRFOIL (npl9510-il)
Reynolds number: 100,000
Max Cl/Cd: 23.3 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-npl9510-il-100000-n5.txt
Download as CSV file: xf-npl9510-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.8382   0.10932   0.10313  -0.0263   1.0000   0.0403
 -14.500  -0.8914   0.09384   0.08740  -0.0362   1.0000   0.0398
 -14.250  -0.9246   0.08425   0.07757  -0.0422   1.0000   0.0396
 -14.000  -0.9494   0.07697   0.07005  -0.0464   1.0000   0.0396
 -13.750  -0.9684   0.07100   0.06385  -0.0495   1.0000   0.0397
 -13.500  -0.9828   0.06593   0.05854  -0.0518   1.0000   0.0399
 -13.250  -0.9934   0.06154   0.05391  -0.0535   1.0000   0.0402
 -13.000  -1.0006   0.05769   0.04981  -0.0546   1.0000   0.0406
 -12.750  -1.0048   0.05428   0.04614  -0.0553   1.0000   0.0410
 -12.500  -1.0038   0.05147   0.04316  -0.0555   1.0000   0.0415
 -12.250  -0.9968   0.04941   0.04107  -0.0551   1.0000   0.0422
 -12.000  -0.9909   0.04741   0.03903  -0.0549   1.0000   0.0431
 -11.750  -0.9858   0.04544   0.03697  -0.0545   1.0000   0.0441
 -11.500  -0.9810   0.04352   0.03491  -0.0539   1.0000   0.0453
 -11.250  -0.9759   0.04170   0.03295  -0.0529   1.0000   0.0465
 -11.000  -0.9702   0.04000   0.03107  -0.0516   1.0000   0.0477
 -10.750  -0.9617   0.03846   0.02951  -0.0504   1.0000   0.0489
 -10.500  -0.9526   0.03699   0.02804  -0.0494   1.0000   0.0501
 -10.250  -0.9428   0.03556   0.02656  -0.0485   1.0000   0.0516
 -10.000  -0.9318   0.03418   0.02510  -0.0477   1.0000   0.0536
  -9.750  -0.9193   0.03288   0.02368  -0.0468   1.0000   0.0561
  -9.500  -0.9077   0.03153   0.02237  -0.0461   1.0000   0.0585
  -9.250  -0.8937   0.03032   0.02112  -0.0453   1.0000   0.0617
  -9.000  -0.8786   0.02915   0.01987  -0.0445   1.0000   0.0653
  -8.750  -0.8630   0.02794   0.01869  -0.0441   1.0000   0.0694
  -8.500  -0.8454   0.02686   0.01757  -0.0437   1.0000   0.0755
  -8.250  -0.8268   0.02577   0.01649  -0.0436   1.0000   0.0830
  -8.000  -0.8069   0.02472   0.01546  -0.0436   1.0000   0.0929
  -7.750  -0.7858   0.02371   0.01449  -0.0438   1.0000   0.1053
  -7.500  -0.7635   0.02277   0.01358  -0.0440   1.0000   0.1207
  -7.250  -0.7401   0.02191   0.01272  -0.0444   1.0000   0.1381
  -7.000  -0.7159   0.02104   0.01190  -0.0449   1.0000   0.1573
  -6.750  -0.6908   0.02015   0.01111  -0.0457   1.0000   0.1803
  -6.500  -0.6646   0.01923   0.01032  -0.0467   1.0000   0.2103
  -6.250  -0.6373   0.01826   0.00960  -0.0480   1.0000   0.2543
  -6.000  -0.6097   0.01747   0.00917  -0.0492   1.0000   0.3165
  -5.750  -0.5832   0.01716   0.00910  -0.0494   1.0000   0.3723
  -5.500  -0.5569   0.01708   0.00907  -0.0493   1.0000   0.4097
  -5.250  -0.5312   0.01712   0.00911  -0.0489   1.0000   0.4346
  -5.000  -0.5050   0.01714   0.00906  -0.0487   1.0000   0.4545
  -4.750  -0.4792   0.01721   0.00905  -0.0483   1.0000   0.4702
  -4.500  -0.4538   0.01729   0.00910  -0.0478   1.0000   0.4828
  -4.250  -0.4280   0.01736   0.00910  -0.0474   1.0000   0.4947
  -4.000  -0.4012   0.01738   0.00902  -0.0474   1.0000   0.5071
  -3.750  -0.3770   0.01755   0.00920  -0.0465   1.0000   0.5163
  -3.500  -0.3510   0.01763   0.00923  -0.0462   1.0000   0.5264
  -3.250  -0.3255   0.01777   0.00934  -0.0457   1.0000   0.5374
  -3.000  -0.3021   0.01804   0.00965  -0.0446   1.0000   0.5472
  -2.750  -0.2758   0.01815   0.00973  -0.0444   1.0000   0.5585
  -2.500  -0.2519   0.01829   0.00992  -0.0434   1.0000   0.5644
  -2.250  -0.2245   0.01826   0.00985  -0.0437   1.0000   0.5711
  -2.000  -0.1974   0.01823   0.00980  -0.0438   1.0000   0.5765
  -1.750  -0.1723   0.01829   0.00990  -0.0433   1.0000   0.5807
  -1.500  -0.1455   0.01829   0.00991  -0.0434   1.0000   0.5860
  -1.250  -0.1169   0.01825   0.00984  -0.0440   1.0000   0.5923
  -1.000  -0.0920   0.01833   0.01000  -0.0435   1.0000   0.5959
  -0.750  -0.0663   0.01840   0.01013  -0.0433   1.0000   0.6003
  -0.500  -0.0391   0.01845   0.01021  -0.0436   1.0000   0.6058
  -0.250  -0.0118   0.01850   0.01031  -0.0439   1.0000   0.6107
   0.250   0.0426   0.01875   0.01076  -0.0441   0.9985   0.6190
   0.500   0.0781   0.01886   0.01096  -0.0460   0.9956   0.6246
   0.750   0.1842   0.01810   0.01045  -0.0603   0.9520   0.6298
   1.000   0.2584   0.01665   0.00921  -0.0666   0.8959   0.6345
   1.250   0.3047   0.01797   0.00784  -0.0670   0.2373   0.6390
   1.500   0.3300   0.01900   0.00817  -0.0669   0.1150   0.6442
   1.750   0.3549   0.01952   0.00861  -0.0661   0.0924   0.6476
   2.000   0.3803   0.02003   0.00910  -0.0655   0.0825   0.6517
   2.250   0.4068   0.02048   0.00956  -0.0651   0.0751   0.6565
   2.500   0.4335   0.02105   0.01009  -0.0650   0.0698   0.6617
   2.750   0.4582   0.02162   0.01076  -0.0642   0.0663   0.6652
   3.000   0.4835   0.02228   0.01140  -0.0636   0.0630   0.6696
   3.250   0.5099   0.02307   0.01215  -0.0633   0.0599   0.6747
   3.500   0.5378   0.02381   0.01297  -0.0632   0.0571   0.6796
   3.750   0.5642   0.02467   0.01390  -0.0627   0.0552   0.6836
   4.000   0.5912   0.02560   0.01483  -0.0625   0.0532   0.6885
   4.250   0.6195   0.02669   0.01599  -0.0625   0.0511   0.6942
   4.500   0.6469   0.02776   0.01729  -0.0622   0.0490   0.6987
   4.750   0.6738   0.02904   0.01876  -0.0617   0.0476   0.7033
   5.000   0.7008   0.03035   0.02022  -0.0615   0.0464   0.7090
   5.250   0.7268   0.03163   0.02156  -0.0613   0.0449   0.7145
   5.500   0.7509   0.03334   0.02369  -0.0604   0.0433   0.7193
   5.750   0.7748   0.03541   0.02621  -0.0595   0.0421   0.7249
   6.000   0.7973   0.03778   0.02900  -0.0585   0.0414   0.7304
   6.250   0.8168   0.04033   0.03199  -0.0571   0.0408   0.7354
   6.500   0.8355   0.04286   0.03489  -0.0559   0.0400   0.7414
   6.750   0.8544   0.04483   0.03707  -0.0549   0.0390   0.7473
   7.000   0.8740   0.04628   0.03854  -0.0543   0.0382   0.7532
   7.250   0.8820   0.05060   0.04353  -0.0520   0.0374   0.7590
   7.500   0.8886   0.05490   0.04832  -0.0498   0.0373   0.7644
   7.750   0.8924   0.05928   0.05313  -0.0478   0.0373   0.7701
   8.000   0.8941   0.06380   0.05800  -0.0461   0.0373   0.7765
   8.250   0.8929   0.06818   0.06267  -0.0445   0.0375   0.7821
   8.500   0.8897   0.07252   0.06725  -0.0431   0.0377   0.7885
   8.750   0.8854   0.07666   0.07157  -0.0420   0.0378   0.7954
   9.000   0.8792   0.08059   0.07565  -0.0409   0.0380   0.8024
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