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NACA 66 (p51htip-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 66 (p51htip-il)
Reynolds number: 500,000
Max Cl/Cd: 67.04 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-p51htip-il-500000-n5.txt
Download as CSV file: xf-p51htip-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66                                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5422   0.08222   0.07978  -0.0543   0.9100   0.0095
 -11.250  -0.5993   0.06502   0.06245  -0.0663   0.8961   0.0093
 -11.000  -0.6416   0.05720   0.05442  -0.0681   0.8848   0.0092
 -10.750  -0.6715   0.05222   0.04923  -0.0666   0.8751   0.0093
 -10.500  -0.7028   0.04734   0.04409  -0.0630   0.8662   0.0094
 -10.000  -0.7577   0.03583   0.03173  -0.0530   0.8522   0.0098
  -9.750  -0.7715   0.02984   0.02507  -0.0486   0.8467   0.0104
  -9.500  -0.7658   0.02650   0.02123  -0.0462   0.8427   0.0108
  -9.250  -0.7520   0.02421   0.01857  -0.0446   0.8386   0.0111
  -9.000  -0.7342   0.02261   0.01668  -0.0435   0.8350   0.0113
  -8.750  -0.7156   0.02122   0.01510  -0.0426   0.8318   0.0116
  -8.250  -0.6719   0.01977   0.01343  -0.0415   0.8261   0.0122
  -8.000  -0.6490   0.01901   0.01257  -0.0410   0.8231   0.0125
  -7.750  -0.6260   0.01827   0.01172  -0.0405   0.8202   0.0129
  -7.500  -0.6027   0.01754   0.01087  -0.0401   0.8176   0.0134
  -7.250  -0.5790   0.01691   0.01012  -0.0396   0.8153   0.0140
  -7.000  -0.5548   0.01636   0.00945  -0.0392   0.8130   0.0147
  -6.750  -0.5313   0.01565   0.00865  -0.0388   0.8105   0.0151
  -6.500  -0.5084   0.01497   0.00794  -0.0383   0.8079   0.0159
  -6.250  -0.4841   0.01457   0.00751  -0.0379   0.8054   0.0165
  -6.000  -0.4598   0.01416   0.00704  -0.0375   0.8031   0.0173
  -5.750  -0.4356   0.01375   0.00656  -0.0371   0.8009   0.0182
  -5.500  -0.4112   0.01336   0.00611  -0.0367   0.7990   0.0190
  -5.250  -0.3860   0.01305   0.00575  -0.0365   0.7969   0.0197
  -5.000  -0.3627   0.01253   0.00522  -0.0359   0.7948   0.0211
  -4.750  -0.3374   0.01224   0.00492  -0.0357   0.7927   0.0224
  -4.500  -0.3120   0.01196   0.00462  -0.0355   0.7908   0.0239
  -4.250  -0.2863   0.01171   0.00433  -0.0353   0.7890   0.0253
  -4.000  -0.2604   0.01149   0.00407  -0.0352   0.7874   0.0263
  -3.750  -0.2359   0.01111   0.00364  -0.0347   0.7858   0.0284
  -3.500  -0.2101   0.01087   0.00338  -0.0346   0.7843   0.0306
  -3.250  -0.1837   0.01067   0.00317  -0.0345   0.7825   0.0330
  -3.000  -0.1570   0.01050   0.00299  -0.0345   0.7806   0.0357
  -2.750  -0.1308   0.01028   0.00279  -0.0344   0.7787   0.0434
  -2.500  -0.1049   0.01003   0.00262  -0.0343   0.7771   0.0645
  -2.250  -0.0823   0.00944   0.00241  -0.0337   0.7754   0.1680
  -2.000  -0.0625   0.00859   0.00217  -0.0329   0.7738   0.3366
  -1.750  -0.0500   0.00723   0.00189  -0.0307   0.7722   0.6119
  -1.500  -0.0272   0.00700   0.00202  -0.0296   0.7709   0.7261
  -1.250  -0.0004   0.00702   0.00208  -0.0293   0.7696   0.7547
  -1.000   0.0267   0.00705   0.00217  -0.0291   0.7679   0.7756
  -0.750   0.0542   0.00709   0.00224  -0.0291   0.7663   0.7893
  -0.500   0.0818   0.00714   0.00231  -0.0291   0.7648   0.8004
  -0.250   0.1102   0.00717   0.00233  -0.0293   0.7634   0.8052
   0.000   0.1389   0.00718   0.00232  -0.0296   0.7619   0.8080
   0.250   0.1677   0.00719   0.00231  -0.0300   0.7603   0.8107
   0.500   0.1963   0.00720   0.00233  -0.0303   0.7588   0.8129
   0.750   0.2249   0.00721   0.00234  -0.0306   0.7571   0.8151
   1.000   0.2535   0.00723   0.00236  -0.0309   0.7549   0.8173
   1.250   0.2817   0.00723   0.00240  -0.0312   0.7516   0.8198
   1.500   0.3101   0.00723   0.00242  -0.0314   0.7480   0.8225
   1.750   0.3385   0.00723   0.00243  -0.0317   0.7443   0.8255
   2.000   0.3666   0.00721   0.00242  -0.0318   0.7389   0.8279
   2.250   0.3939   0.00714   0.00238  -0.0317   0.7283   0.8303
   2.500   0.4210   0.00709   0.00235  -0.0315   0.7148   0.8329
   2.750   0.4481   0.00707   0.00233  -0.0314   0.6994   0.8359
   3.000   0.4733   0.00706   0.00224  -0.0308   0.6568   0.8391
   3.250   0.4805   0.00812   0.00245  -0.0271   0.4716   0.8430
   3.500   0.4898   0.00923   0.00296  -0.0242   0.3299   0.8471
   3.750   0.5024   0.01014   0.00339  -0.0219   0.2156   0.8518
   4.250   0.5332   0.01160   0.00417  -0.0183   0.0568   0.8604
   4.500   0.5540   0.01197   0.00447  -0.0172   0.0387   0.8646
   4.750   0.5764   0.01225   0.00476  -0.0165   0.0332   0.8690
   5.000   0.5977   0.01257   0.00509  -0.0155   0.0287   0.8732
   5.250   0.6194   0.01283   0.00540  -0.0145   0.0271   0.8776
   5.500   0.6405   0.01312   0.00574  -0.0135   0.0253   0.8827
   5.750   0.6609   0.01345   0.00610  -0.0124   0.0236   0.8879
   6.000   0.6772   0.01391   0.00660  -0.0105   0.0213   0.8939
   6.250   0.6957   0.01420   0.00694  -0.0090   0.0206   0.9006
   6.500   0.7125   0.01453   0.00735  -0.0072   0.0198   0.9076
   6.750   0.7292   0.01495   0.00782  -0.0054   0.0189   0.9158
   7.000   0.7454   0.01535   0.00829  -0.0036   0.0181   0.9244
   7.250   0.7623   0.01578   0.00877  -0.0019   0.0174   0.9342
   7.500   0.7790   0.01629   0.00933  -0.0004   0.0167   0.9460
   7.750   0.7960   0.01716   0.01025   0.0008   0.0159   0.9599
   8.000   0.8228   0.01768   0.01086   0.0002   0.0154   0.9721
   8.250   0.8512   0.01833   0.01158  -0.0009   0.0148   0.9875
   8.500   0.8716   0.01900   0.01230  -0.0004   0.0143   1.0000
   8.750   0.8891   0.01967   0.01303   0.0007   0.0138   1.0000
   9.000   0.9068   0.02038   0.01380   0.0018   0.0135   1.0000
   9.250   0.9244   0.02111   0.01458   0.0029   0.0131   1.0000
   9.500   0.9421   0.02179   0.01530   0.0039   0.0128   1.0000
   9.750   0.9592   0.02257   0.01612   0.0049   0.0124   1.0000
  10.000   0.9756   0.02357   0.01717   0.0060   0.0121   1.0000
  10.250   0.9923   0.02482   0.01853   0.0070   0.0118   1.0000
  10.500   1.0095   0.02584   0.01968   0.0080   0.0116   1.0000
  10.750   1.0261   0.02698   0.02096   0.0090   0.0115   1.0000
  11.000   1.0417   0.02806   0.02219   0.0101   0.0111   1.0000
  11.250   1.0560   0.02919   0.02346   0.0112   0.0107   1.0000
  11.500   1.0688   0.03058   0.02501   0.0125   0.0105   1.0000
  11.750   1.0796   0.03210   0.02670   0.0139   0.0102   1.0000
  12.000   1.0889   0.03360   0.02838   0.0153   0.0100   1.0000
  12.250   1.0960   0.03534   0.03029   0.0169   0.0098   1.0000
  12.500   1.1019   0.03694   0.03203   0.0184   0.0097   1.0000
  12.750   1.1057   0.03878   0.03404   0.0199   0.0095   1.0000
  13.000   1.1085   0.04064   0.03603   0.0213   0.0094   1.0000
  13.250   1.1087   0.04280   0.03835   0.0227   0.0093   1.0000
  13.500   1.1067   0.04521   0.04092   0.0240   0.0092   1.0000
  13.750   1.1058   0.04745   0.04329   0.0250   0.0091   1.0000
  14.000   1.1008   0.05023   0.04622   0.0258   0.0090   1.0000
  14.250   1.0916   0.05369   0.04986   0.0264   0.0089   1.0000
  14.500   1.0781   0.05780   0.05415   0.0266   0.0089   1.0000
  14.750   1.0626   0.06243   0.05896   0.0260   0.0088   1.0000
  15.000   1.0432   0.06811   0.06486   0.0246   0.0088   1.0000
  15.250   1.0176   0.07554   0.07253   0.0216   0.0088   1.0000
  15.500   0.9960   0.08318   0.08034   0.0175   0.0088   1.0000
  15.750   0.9539   0.09685   0.09431   0.0090   0.0089   1.0000
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