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NPL 9626 AIRFOIL (npl9626-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NPL 9626 AIRFOIL (npl9626-il)
Reynolds number: 100,000
Max Cl/Cd: 39.86 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-npl9626-il-100000-n5.txt
Download as CSV file: xf-npl9626-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NPL 9626 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6848   0.10792   0.10235  -0.0083   1.0000   0.0289
 -12.250  -0.7105   0.09608   0.09050  -0.0151   1.0000   0.0286
 -12.000  -0.7433   0.08375   0.07809  -0.0240   1.0000   0.0282
 -11.750  -0.7744   0.07395   0.06811  -0.0317   1.0000   0.0278
 -11.500  -0.8019   0.06669   0.06064  -0.0366   1.0000   0.0276
 -11.250  -0.8261   0.06120   0.05492  -0.0387   1.0000   0.0276
 -11.000  -0.8472   0.05687   0.05034  -0.0385   1.0000   0.0276
 -10.750  -0.8651   0.05330   0.04649  -0.0364   1.0000   0.0277
 -10.500  -0.8773   0.04981   0.04267  -0.0339   1.0000   0.0279
 -10.250  -0.8837   0.04632   0.03874  -0.0316   1.0000   0.0283
 -10.000  -0.8854   0.04289   0.03481  -0.0292   1.0000   0.0288
  -9.750  -0.8753   0.04082   0.03258  -0.0277   1.0000   0.0294
  -9.500  -0.8621   0.03935   0.03100  -0.0264   1.0000   0.0304
  -9.250  -0.8492   0.03772   0.02916  -0.0249   1.0000   0.0319
  -9.000  -0.8377   0.03550   0.02646  -0.0230   1.0000   0.0337
  -8.750  -0.8204   0.03435   0.02534  -0.0220   1.0000   0.0351
  -8.500  -0.8031   0.03295   0.02378  -0.0207   1.0000   0.0367
  -8.250  -0.7857   0.03128   0.02173  -0.0191   1.0000   0.0389
  -8.000  -0.7669   0.03011   0.02061  -0.0181   1.0000   0.0405
  -7.750  -0.7475   0.02888   0.01928  -0.0169   1.0000   0.0424
  -7.500  -0.7273   0.02750   0.01770  -0.0156   1.0000   0.0443
  -7.250  -0.7079   0.02627   0.01645  -0.0143   1.0000   0.0460
  -7.000  -0.6889   0.02527   0.01545  -0.0129   1.0000   0.0481
  -6.750  -0.6698   0.02431   0.01440  -0.0114   1.0000   0.0506
  -6.500  -0.6515   0.02340   0.01347  -0.0099   1.0000   0.0535
  -6.250  -0.6330   0.02270   0.01277  -0.0084   1.0000   0.0577
  -6.000  -0.6147   0.02196   0.01202  -0.0069   1.0000   0.0627
  -5.750  -0.5965   0.02126   0.01131  -0.0053   1.0000   0.0677
  -5.500  -0.5788   0.02049   0.01052  -0.0036   1.0000   0.0721
  -5.250  -0.5607   0.01981   0.00984  -0.0020   1.0000   0.0785
  -5.000  -0.5427   0.01910   0.00916  -0.0004   1.0000   0.0861
  -4.750  -0.5241   0.01844   0.00851   0.0011   1.0000   0.0970
  -4.500  -0.5055   0.01772   0.00791   0.0026   1.0000   0.1171
  -4.250  -0.4879   0.01680   0.00739   0.0039   1.0000   0.1712
  -4.000  -0.4703   0.01596   0.00707   0.0052   1.0000   0.2691
  -3.750  -0.4512   0.01545   0.00687   0.0065   1.0000   0.3449
  -3.500  -0.4127   0.01491   0.00670   0.0039   0.9912   0.4302
  -3.250  -0.3744   0.01448   0.00659   0.0017   0.9819   0.5028
  -3.000  -0.3380   0.01414   0.00652   0.0001   0.9722   0.5696
  -2.750  -0.3041   0.01387   0.00651  -0.0008   0.9620   0.6355
  -2.500  -0.2680   0.01370   0.00647  -0.0020   0.9527   0.6850
  -2.250  -0.2318   0.01358   0.00640  -0.0032   0.9425   0.7196
  -2.000  -0.1981   0.01349   0.00635  -0.0038   0.9301   0.7502
  -1.750  -0.1635   0.01344   0.00630  -0.0045   0.9177   0.7790
  -1.500  -0.1285   0.01340   0.00626  -0.0053   0.9050   0.8064
  -1.250  -0.0922   0.01338   0.00623  -0.0063   0.8913   0.8300
  -1.000  -0.0576   0.01338   0.00619  -0.0069   0.8749   0.8518
  -0.750  -0.0228   0.01338   0.00613  -0.0077   0.8574   0.8714
  -0.500   0.0121   0.01340   0.00609  -0.0084   0.8386   0.8888
  -0.250   0.0475   0.01343   0.00605  -0.0094   0.8185   0.9041
   0.000   0.0837   0.01347   0.00601  -0.0105   0.7966   0.9180
   0.250   0.1199   0.01351   0.00596  -0.0116   0.7738   0.9309
   0.500   0.1554   0.01357   0.00592  -0.0127   0.7502   0.9434
   0.750   0.1928   0.01364   0.00589  -0.0144   0.7260   0.9542
   1.000   0.2324   0.01371   0.00584  -0.0165   0.7020   0.9627
   1.250   0.2694   0.01379   0.00583  -0.0183   0.6776   0.9724
   1.500   0.3088   0.01389   0.00582  -0.0206   0.6543   0.9821
   1.750   0.3511   0.01397   0.00582  -0.0235   0.6323   0.9915
   2.000   0.3926   0.01406   0.00585  -0.0265   0.6115   1.0000
   2.250   0.4156   0.01416   0.00588  -0.0257   0.5946   1.0000
   2.500   0.4387   0.01428   0.00596  -0.0249   0.5794   1.0000
   2.750   0.4617   0.01443   0.00605  -0.0241   0.5646   1.0000
   3.000   0.4846   0.01458   0.00616  -0.0232   0.5489   1.0000
   3.250   0.5070   0.01475   0.00629  -0.0222   0.5313   1.0000
   3.500   0.5288   0.01492   0.00641  -0.0210   0.5093   1.0000
   3.750   0.5496   0.01511   0.00649  -0.0197   0.4816   1.0000
   4.000   0.5698   0.01532   0.00658  -0.0182   0.4487   1.0000
   4.250   0.5904   0.01555   0.00672  -0.0169   0.4182   1.0000
   4.500   0.6117   0.01581   0.00692  -0.0157   0.3949   1.0000
   4.750   0.6329   0.01607   0.00717  -0.0145   0.3673   1.0000
   5.000   0.6533   0.01639   0.00742  -0.0131   0.3283   1.0000
   5.250   0.6714   0.01693   0.00769  -0.0115   0.2595   1.0000
   5.500   0.6850   0.01811   0.00826  -0.0096   0.1634   1.0000
   5.750   0.6999   0.01927   0.00908  -0.0078   0.1179   1.0000
   6.000   0.7167   0.02018   0.00985  -0.0061   0.1008   1.0000
   6.250   0.7343   0.02096   0.01063  -0.0045   0.0914   1.0000
   6.500   0.7519   0.02174   0.01144  -0.0029   0.0850   1.0000
   6.750   0.7694   0.02252   0.01223  -0.0014   0.0793   1.0000
   7.000   0.7863   0.02335   0.01308   0.0002   0.0750   1.0000
   7.250   0.8041   0.02412   0.01391   0.0017   0.0709   1.0000
   7.500   0.8207   0.02502   0.01479   0.0033   0.0676   1.0000
   7.750   0.8380   0.02595   0.01576   0.0048   0.0648   1.0000
   8.000   0.8560   0.02684   0.01673   0.0061   0.0618   1.0000
   8.250   0.8735   0.02781   0.01770   0.0074   0.0592   1.0000
   8.500   0.8909   0.02903   0.01884   0.0087   0.0573   1.0000
   8.750   0.9105   0.03017   0.02013   0.0098   0.0555   1.0000
   9.000   0.9298   0.03139   0.02148   0.0109   0.0535   1.0000
   9.250   0.9484   0.03260   0.02275   0.0119   0.0515   1.0000
   9.500   0.9669   0.03391   0.02402   0.0128   0.0497   1.0000
   9.750   0.9854   0.03552   0.02576   0.0137   0.0482   1.0000
  10.000   1.0025   0.03721   0.02770   0.0149   0.0469   1.0000
  10.250   1.0178   0.03888   0.02958   0.0161   0.0454   1.0000
  10.500   1.0316   0.04040   0.03124   0.0174   0.0438   1.0000
  10.750   1.0452   0.04187   0.03276   0.0185   0.0425   1.0000
  11.000   1.0557   0.04383   0.03486   0.0198   0.0413   1.0000
  11.250   1.0580   0.04604   0.03746   0.0220   0.0402   1.0000
  11.500   1.0572   0.04824   0.03996   0.0244   0.0392   1.0000
  11.750   1.0547   0.05054   0.04249   0.0265   0.0384   1.0000
  12.000   1.0512   0.05299   0.04516   0.0282   0.0378   1.0000
  12.250   1.0458   0.05574   0.04812   0.0295   0.0373   1.0000
  12.500   1.0383   0.05882   0.05141   0.0301   0.0370   1.0000
  12.750   1.0284   0.06232   0.05512   0.0302   0.0367   1.0000
  13.000   1.0152   0.06642   0.05942   0.0294   0.0365   1.0000
  13.250   0.9981   0.07132   0.06455   0.0277   0.0363   1.0000
  13.500   0.9752   0.07751   0.07098   0.0245   0.0363   1.0000
  13.750   0.9366   0.08696   0.08074   0.0185   0.0366   1.0000
  14.000   0.7925   0.12419   0.11845  -0.0068   0.0387   1.0000
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