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NPL 9510 AIRFOIL (npl9510-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NPL 9510 AIRFOIL (npl9510-il)
Reynolds number: 100,000
Max Cl/Cd: 18.37 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-npl9510-il-100000.txt
Download as CSV file: xf-npl9510-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7340   0.10970   0.10381  -0.0279   1.0000   0.0865
 -12.500  -0.7251   0.10755   0.10166  -0.0274   1.0000   0.0875
 -12.250  -0.9433   0.06977   0.06327  -0.0562   1.0000   0.0749
 -12.000  -0.9642   0.06544   0.05875  -0.0571   1.0000   0.0745
 -11.750  -0.9805   0.06126   0.05440  -0.0575   1.0000   0.0743
 -11.500  -0.9918   0.05718   0.05006  -0.0577   1.0000   0.0742
 -11.250  -0.9985   0.05336   0.04592  -0.0574   1.0000   0.0742
 -11.000  -1.0004   0.04980   0.04200  -0.0569   1.0000   0.0744
 -10.750  -0.9964   0.04630   0.03815  -0.0564   1.0000   0.0750
 -10.500  -0.9831   0.04341   0.03522  -0.0557   1.0000   0.0766
 -10.250  -0.9680   0.04149   0.03323  -0.0550   1.0000   0.0788
 -10.000  -0.9536   0.03937   0.03090  -0.0544   1.0000   0.0812
  -9.750  -0.9387   0.03708   0.02828  -0.0537   1.0000   0.0835
  -9.500  -0.9218   0.03501   0.02578  -0.0530   1.0000   0.0857
  -9.250  -0.9025   0.03294   0.02387  -0.0520   1.0000   0.0891
  -9.000  -0.8832   0.03155   0.02239  -0.0513   1.0000   0.0940
  -8.750  -0.8636   0.02988   0.02056  -0.0504   1.0000   0.0993
  -8.500  -0.8436   0.02855   0.01934  -0.0495   1.0000   0.1056
  -8.250  -0.8235   0.02711   0.01786  -0.0486   1.0000   0.1140
  -8.000  -0.8026   0.02589   0.01660  -0.0481   1.0000   0.1256
  -7.750  -0.7821   0.02454   0.01539  -0.0476   1.0000   0.1410
  -7.500  -0.7612   0.02313   0.01421  -0.0473   1.0000   0.1617
  -7.250  -0.7389   0.02170   0.01297  -0.0475   1.0000   0.1901
  -7.000  -0.7151   0.02035   0.01188  -0.0480   1.0000   0.2238
  -6.750  -0.6894   0.01907   0.01092  -0.0490   1.0000   0.2679
  -6.500  -0.6627   0.01802   0.01036  -0.0500   1.0000   0.3326
  -6.250  -0.6374   0.01793   0.01063  -0.0496   1.0000   0.4004
  -6.000  -0.6135   0.01849   0.01125  -0.0483   1.0000   0.4452
  -5.750  -0.5905   0.01922   0.01193  -0.0465   1.0000   0.4750
  -5.500  -0.5700   0.02008   0.01282  -0.0439   1.0000   0.4940
  -5.250  -0.5490   0.02080   0.01353  -0.0415   1.0000   0.5103
  -5.000  -0.5271   0.02135   0.01402  -0.0396   1.0000   0.5254
  -4.750  -0.5040   0.02174   0.01432  -0.0382   1.0000   0.5401
  -4.500  -0.4871   0.02248   0.01514  -0.0344   1.0000   0.5471
  -4.250  -0.4639   0.02266   0.01524  -0.0333   1.0000   0.5597
  -4.000  -0.4449   0.02313   0.01572  -0.0305   1.0000   0.5684
  -3.750  -0.4231   0.02330   0.01586  -0.0289   1.0000   0.5789
  -3.500  -0.3973   0.02327   0.01574  -0.0288   1.0000   0.5922
  -3.250  -0.3819   0.02373   0.01628  -0.0250   1.0000   0.5980
  -3.000  -0.3553   0.02358   0.01604  -0.0252   1.0000   0.6106
  -2.750  -0.3401   0.02399   0.01652  -0.0215   1.0000   0.6176
  -2.500  -0.3173   0.02402   0.01654  -0.0204   1.0000   0.6298
  -2.250  -0.2976   0.02418   0.01672  -0.0183   1.0000   0.6398
  -2.000  -0.2740   0.02402   0.01656  -0.0176   1.0000   0.6481
  -1.750  -0.2500   0.02385   0.01640  -0.0170   1.0000   0.6553
  -1.500  -0.2199   0.02347   0.01597  -0.0185   1.0000   0.6633
  -1.250  -0.1982   0.02335   0.01590  -0.0172   1.0000   0.6687
  -1.000  -0.1676   0.02306   0.01559  -0.0188   1.0000   0.6765
  -0.750  -0.1422   0.02284   0.01541  -0.0188   1.0000   0.6821
  -0.500  -0.1179   0.02271   0.01533  -0.0184   1.0000   0.6877
  -0.250  -0.0846   0.02248   0.01509  -0.0208   1.0000   0.6953
   0.000  -0.0619   0.02235   0.01505  -0.0199   1.0000   0.6999
   0.250  -0.0364   0.02226   0.01504  -0.0199   1.0000   0.7056
   0.500  -0.0027   0.02214   0.01495  -0.0224   1.0000   0.7128
   0.750   0.0189   0.02208   0.01503  -0.0213   1.0000   0.7172
   1.000   0.0450   0.02206   0.01512  -0.0216   1.0000   0.7228
   1.250   0.0770   0.02207   0.01522  -0.0235   1.0000   0.7296
   1.500   0.0991   0.02208   0.01541  -0.0227   1.0000   0.7342
   1.750   0.2989   0.02153   0.01205  -0.0461   0.1639   0.7415
   2.000   0.3253   0.02225   0.01259  -0.0459   0.1367   0.7472
   2.250   0.3480   0.02288   0.01314  -0.0446   0.1235   0.7520
   2.500   0.3758   0.02361   0.01374  -0.0448   0.1144   0.7576
   2.750   0.4064   0.02456   0.01463  -0.0453   0.1089   0.7633
   3.000   0.4328   0.02522   0.01535  -0.0446   0.1031   0.7685
   3.250   0.4638   0.02639   0.01642  -0.0453   0.0986   0.7747
   3.500   0.4955   0.02790   0.01799  -0.0459   0.0965   0.7801
   3.750   0.5230   0.02883   0.01921  -0.0452   0.0943   0.7855
   4.000   0.5535   0.03013   0.02077  -0.0455   0.0917   0.7922
   4.250   0.5812   0.03183   0.02278  -0.0449   0.0919   0.7978
   4.500   0.6077   0.03384   0.02514  -0.0441   0.0928   0.8036
   4.750   0.6364   0.03612   0.02779  -0.0442   0.0929   0.8102
   5.000   0.6584   0.03868   0.03067  -0.0428   0.0948   0.8158
   5.250   0.6994   0.05153   0.04651  -0.0421   0.2551   0.8193
   5.500   0.7173   0.05416   0.04913  -0.0414   0.2342   0.8263
   5.750   0.7301   0.05665   0.05165  -0.0397   0.2157   0.8324
   6.000   0.7443   0.05939   0.05445  -0.0390   0.1981   0.8395
   6.250   0.7524   0.06204   0.05731  -0.0379   0.1825   0.8461
   6.500   0.7592   0.06547   0.06090  -0.0373   0.1709   0.8536
   6.750   0.7744   0.06828   0.06373  -0.0363   0.1637   0.8614
   7.000   0.7716   0.07220   0.06791  -0.0364   0.1540   0.8690
   7.250   0.7818   0.07510   0.07087  -0.0355   0.1479   0.8776
   7.500   0.8095   0.08008   0.07558  -0.0346   0.1446   0.8883
   7.750   0.7695   0.08340   0.07949  -0.0363   0.1371   0.8966
   8.000   0.7696   0.08668   0.08285  -0.0360   0.1326   0.9094
   8.250   0.7985   0.08956   0.08564  -0.0329   0.1290   0.9278
   8.500   0.7906   0.09513   0.09130  -0.0335   0.1270   0.9653
   8.750   0.7427   0.10100   0.09735  -0.0425   0.1248   1.0000
   9.000   0.7295   0.10771   0.10403  -0.0514   0.1203   1.0000
   9.250   0.7395   0.11184   0.10813  -0.0533   0.1159   1.0000
   9.500   0.6019   0.10909   0.10557  -0.0309   0.1269   0.9512
   9.750   0.5633   0.11429   0.11074  -0.0377   0.1236   0.9766
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