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NPL 9626 AIRFOIL (npl9626-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NPL 9626 AIRFOIL (npl9626-il)
Reynolds number: 500,000
Max Cl/Cd: 65.27 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-npl9626-il-500000.txt
Download as CSV file: xf-npl9626-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -1.0250   0.04949   0.04557  -0.0408   1.0000   0.0155
 -13.000  -1.0453   0.04464   0.04043  -0.0414   1.0000   0.0154
 -12.750  -1.0557   0.04135   0.03693  -0.0406   1.0000   0.0155
 -12.500  -1.0619   0.03871   0.03409  -0.0390   1.0000   0.0155
 -12.250  -1.0649   0.03648   0.03168  -0.0369   1.0000   0.0156
 -12.000  -1.0648   0.03460   0.02964  -0.0343   1.0000   0.0156
 -11.750  -1.0611   0.03289   0.02777  -0.0319   1.0000   0.0157
 -11.500  -1.0525   0.03127   0.02598  -0.0300   1.0000   0.0159
 -11.250  -1.0416   0.02972   0.02427  -0.0283   1.0000   0.0160
 -11.000  -1.0289   0.02825   0.02264  -0.0267   1.0000   0.0162
 -10.750  -1.0145   0.02687   0.02112  -0.0252   1.0000   0.0164
 -10.500  -0.9989   0.02558   0.01970  -0.0237   1.0000   0.0166
 -10.250  -0.9824   0.02436   0.01833  -0.0223   1.0000   0.0168
 -10.000  -0.9651   0.02321   0.01705  -0.0209   1.0000   0.0171
  -9.750  -0.9469   0.02222   0.01592  -0.0195   1.0000   0.0175
  -9.500  -0.9282   0.02133   0.01490  -0.0181   1.0000   0.0179
  -9.250  -0.9109   0.02032   0.01389  -0.0167   1.0000   0.0184
  -9.000  -0.8916   0.01970   0.01325  -0.0154   1.0000   0.0189
  -8.750  -0.8726   0.01905   0.01256  -0.0139   1.0000   0.0196
  -8.500  -0.8539   0.01838   0.01181  -0.0123   1.0000   0.0204
  -8.250  -0.8354   0.01770   0.01103  -0.0107   1.0000   0.0213
  -8.000  -0.8182   0.01697   0.01032  -0.0089   1.0000   0.0222
  -7.750  -0.7992   0.01648   0.00981  -0.0074   1.0000   0.0233
  -7.500  -0.7799   0.01603   0.00929  -0.0058   1.0000   0.0244
  -7.250  -0.7631   0.01534   0.00859  -0.0038   1.0000   0.0256
  -7.000  -0.7445   0.01488   0.00812  -0.0022   1.0000   0.0267
  -6.750  -0.7253   0.01447   0.00769  -0.0006   1.0000   0.0281
  -6.500  -0.7071   0.01396   0.00715   0.0011   1.0000   0.0297
  -6.250  -0.6879   0.01355   0.00675   0.0026   1.0000   0.0315
  -6.000  -0.6642   0.01326   0.00641   0.0033   0.9995   0.0336
  -5.750  -0.6255   0.01271   0.00589   0.0007   0.9964   0.0367
  -5.500  -0.5868   0.01233   0.00548  -0.0018   0.9939   0.0397
  -5.250  -0.5521   0.01196   0.00514  -0.0034   0.9903   0.0429
  -5.000  -0.5161   0.01161   0.00481  -0.0052   0.9870   0.0468
  -4.750  -0.4786   0.01130   0.00451  -0.0074   0.9844   0.0522
  -4.500  -0.4434   0.01092   0.00419  -0.0090   0.9806   0.0620
  -4.250  -0.4082   0.01049   0.00386  -0.0107   0.9761   0.0804
  -4.000  -0.3726   0.00986   0.00349  -0.0127   0.9723   0.1296
  -3.750  -0.3435   0.00905   0.00315  -0.0134   0.9652   0.2324
  -3.500  -0.3124   0.00851   0.00292  -0.0143   0.9584   0.3069
  -3.250  -0.2841   0.00814   0.00276  -0.0144   0.9488   0.3606
  -3.000  -0.2547   0.00783   0.00260  -0.0146   0.9397   0.4031
  -2.750  -0.2283   0.00756   0.00245  -0.0141   0.9271   0.4408
  -2.500  -0.2026   0.00728   0.00233  -0.0135   0.9133   0.4855
  -2.250  -0.1774   0.00702   0.00222  -0.0128   0.8984   0.5341
  -2.000  -0.1526   0.00677   0.00212  -0.0119   0.8816   0.5860
  -1.750  -0.1282   0.00655   0.00205  -0.0108   0.8631   0.6397
  -1.500  -0.1034   0.00640   0.00200  -0.0099   0.8436   0.6855
  -1.250  -0.0786   0.00628   0.00196  -0.0089   0.8236   0.7271
  -1.000  -0.0532   0.00621   0.00194  -0.0080   0.8021   0.7614
  -0.750  -0.0275   0.00619   0.00193  -0.0072   0.7786   0.7899
  -0.250   0.0241   0.00625   0.00192  -0.0056   0.7286   0.8356
   0.000   0.0498   0.00634   0.00194  -0.0048   0.7027   0.8563
   0.250   0.0758   0.00642   0.00198  -0.0041   0.6771   0.8754
   0.500   0.1016   0.00654   0.00202  -0.0033   0.6524   0.8930
   0.750   0.1277   0.00666   0.00208  -0.0026   0.6283   0.9089
   1.000   0.1540   0.00682   0.00215  -0.0020   0.6025   0.9228
   1.250   0.1818   0.00699   0.00223  -0.0017   0.5759   0.9342
   1.500   0.2102   0.00716   0.00231  -0.0016   0.5532   0.9449
   1.750   0.2386   0.00733   0.00240  -0.0015   0.5345   0.9554
   2.000   0.2726   0.00752   0.00251  -0.0026   0.5166   0.9614
   2.250   0.3042   0.00772   0.00261  -0.0033   0.4971   0.9694
   2.500   0.3418   0.00790   0.00272  -0.0054   0.4772   0.9734
   2.750   0.3806   0.00807   0.00282  -0.0077   0.4574   0.9768
   3.000   0.4159   0.00824   0.00292  -0.0093   0.4381   0.9818
   3.250   0.4541   0.00841   0.00302  -0.0116   0.4181   0.9850
   3.500   0.4933   0.00857   0.00312  -0.0141   0.4008   0.9883
   3.750   0.5309   0.00876   0.00324  -0.0163   0.3802   0.9924
   4.000   0.5696   0.00893   0.00335  -0.0187   0.3530   0.9955
   4.250   0.6077   0.00931   0.00345  -0.0212   0.2877   0.9985
   4.500   0.6325   0.01059   0.00395  -0.0217   0.1360   1.0000
   4.750   0.6514   0.01132   0.00437  -0.0204   0.0824   1.0000
   5.000   0.6724   0.01166   0.00465  -0.0192   0.0715   1.0000
   5.250   0.6932   0.01200   0.00496  -0.0179   0.0657   1.0000
   5.500   0.7144   0.01227   0.00524  -0.0167   0.0624   1.0000
   5.750   0.7347   0.01264   0.00558  -0.0154   0.0590   1.0000
   6.000   0.7549   0.01301   0.00597  -0.0140   0.0563   1.0000
   6.250   0.7756   0.01332   0.00631  -0.0127   0.0538   1.0000
   6.500   0.7955   0.01372   0.00670  -0.0113   0.0513   1.0000
   6.750   0.8131   0.01435   0.00733  -0.0095   0.0488   1.0000
   7.000   0.8341   0.01466   0.00769  -0.0082   0.0470   1.0000
   7.250   0.8544   0.01506   0.00810  -0.0069   0.0449   1.0000
   7.500   0.8730   0.01561   0.00864  -0.0054   0.0430   1.0000
   7.750   0.8897   0.01637   0.00943  -0.0036   0.0412   1.0000
   8.000   0.9109   0.01673   0.00985  -0.0024   0.0398   1.0000
   8.250   0.9317   0.01718   0.01032  -0.0013   0.0383   1.0000
   8.500   0.9520   0.01767   0.01082  -0.0002   0.0369   1.0000
   8.750   0.9672   0.01873   0.01186   0.0016   0.0355   1.0000
   9.000   0.9888   0.01915   0.01235   0.0026   0.0346   1.0000
   9.250   1.0097   0.01964   0.01291   0.0036   0.0334   1.0000
   9.500   1.0302   0.02016   0.01347   0.0046   0.0323   1.0000
   9.750   1.0502   0.02069   0.01401   0.0056   0.0313   1.0000
  10.000   1.0667   0.02159   0.01491   0.0070   0.0303   1.0000
  10.250   1.0849   0.02233   0.01574   0.0082   0.0294   1.0000
  10.500   1.1035   0.02294   0.01645   0.0094   0.0284   1.0000
  10.750   1.1214   0.02357   0.01714   0.0106   0.0275   1.0000
  11.000   1.1384   0.02420   0.01780   0.0119   0.0267   1.0000
  11.250   1.1518   0.02498   0.01859   0.0136   0.0261   1.0000
  11.500   1.1611   0.02629   0.01995   0.0158   0.0254   1.0000
  11.750   1.1730   0.02724   0.02103   0.0176   0.0248   1.0000
  12.000   1.1840   0.02832   0.02223   0.0193   0.0242   1.0000
  12.250   1.1942   0.02949   0.02350   0.0209   0.0237   1.0000
  12.500   1.2040   0.03070   0.02480   0.0223   0.0232   1.0000
  12.750   1.2131   0.03197   0.02615   0.0236   0.0229   1.0000
  13.000   1.2216   0.03336   0.02760   0.0247   0.0225   1.0000
  13.250   1.2290   0.03493   0.02923   0.0257   0.0223   1.0000
  13.500   1.2345   0.03681   0.03119   0.0266   0.0220   1.0000
  13.750   1.2361   0.03935   0.03384   0.0276   0.0217   1.0000
  14.000   1.2365   0.04194   0.03660   0.0282   0.0215   1.0000
  14.250   1.2362   0.04461   0.03945   0.0284   0.0214   1.0000
  14.500   1.2336   0.04766   0.04268   0.0283   0.0213   1.0000
  14.750   1.2288   0.05112   0.04632   0.0278   0.0212   1.0000
  15.000   1.2211   0.05507   0.05047   0.0268   0.0211   1.0000
  15.250   1.2106   0.05956   0.05515   0.0254   0.0210   1.0000
  15.500   1.1970   0.06465   0.06044   0.0234   0.0210   1.0000
  15.750   1.1799   0.07048   0.06648   0.0208   0.0209   1.0000
  16.000   1.1593   0.07713   0.07333   0.0174   0.0210   1.0000
  16.250   1.1353   0.08475   0.08115   0.0133   0.0210   1.0000
  16.500   1.1073   0.09353   0.09014   0.0082   0.0211   1.0000
  16.750   1.0742   0.10383   0.10065   0.0021   0.0212   1.0000
  17.000   1.0331   0.11662   0.11365  -0.0058   0.0213   1.0000
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