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NACA 66 (p51hroot-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 66 (p51hroot-il)
Reynolds number: 500,000
Max Cl/Cd: 55.58 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-p51hroot-il-500000-n5.txt
Download as CSV file: xf-p51hroot-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
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.7890   0.08451   0.08148  -0.0678   0.9289   0.0122
 -16.500  -0.8216   0.07429   0.07099  -0.0742   0.9184   0.0122
 -16.250  -0.8477   0.06656   0.06301  -0.0784   0.9086   0.0122
 -16.000  -0.8729   0.05998   0.05617  -0.0811   0.8996   0.0123
 -15.750  -0.8880   0.05533   0.05131  -0.0825   0.8912   0.0123
 -15.500  -0.8993   0.05160   0.04739  -0.0829   0.8838   0.0124
 -15.250  -0.9074   0.04836   0.04399  -0.0830   0.8768   0.0125
 -15.000  -0.9146   0.04543   0.04086  -0.0826   0.8702   0.0125
 -14.750  -0.9146   0.04340   0.03873  -0.0821   0.8645   0.0126
 -14.500  -0.9155   0.04127   0.03646  -0.0813   0.8588   0.0127
 -14.250  -0.9149   0.03936   0.03439  -0.0803   0.8536   0.0128
 -14.000  -0.9059   0.03846   0.03345  -0.0796   0.8490   0.0131
 -13.750  -0.9048   0.03650   0.03133  -0.0784   0.8443   0.0131
 -13.500  -0.8997   0.03509   0.02979  -0.0772   0.8397   0.0133
 -13.250  -0.8940   0.03368   0.02822  -0.0759   0.8356   0.0135
 -13.000  -0.8865   0.03239   0.02681  -0.0747   0.8318   0.0138
 -12.750  -0.8776   0.03124   0.02552  -0.0734   0.8278   0.0141
 -12.500  -0.8688   0.02989   0.02401  -0.0720   0.8240   0.0144
 -12.250  -0.8584   0.02862   0.02254  -0.0707   0.8206   0.0146
 -12.000  -0.8463   0.02747   0.02122  -0.0694   0.8175   0.0149
 -11.750  -0.8326   0.02640   0.02000  -0.0683   0.8144   0.0151
 -11.500  -0.8181   0.02544   0.01891  -0.0672   0.8112   0.0154
 -11.250  -0.8036   0.02450   0.01790  -0.0661   0.8082   0.0157
 -11.000  -0.7880   0.02376   0.01709  -0.0651   0.8053   0.0160
 -10.750  -0.7718   0.02321   0.01647  -0.0640   0.8027   0.0164
 -10.500  -0.7546   0.02247   0.01566  -0.0631   0.8002   0.0166
 -10.250  -0.7368   0.02191   0.01504  -0.0622   0.7974   0.0170
 -10.000  -0.7185   0.02123   0.01429  -0.0613   0.7947   0.0174
  -9.750  -0.6999   0.02061   0.01358  -0.0604   0.7921   0.0179
  -9.500  -0.6811   0.02001   0.01289  -0.0595   0.7899   0.0184
  -9.250  -0.6619   0.01949   0.01226  -0.0586   0.7878   0.0188
  -9.000  -0.6438   0.01890   0.01161  -0.0576   0.7858   0.0194
  -8.750  -0.6251   0.01833   0.01103  -0.0566   0.7840   0.0198
  -8.500  -0.6057   0.01787   0.01054  -0.0557   0.7820   0.0203
  -8.250  -0.5858   0.01744   0.01009  -0.0549   0.7800   0.0210
  -8.000  -0.5664   0.01697   0.00958  -0.0539   0.7781   0.0215
  -7.750  -0.5472   0.01652   0.00907  -0.0528   0.7762   0.0221
  -7.500  -0.5274   0.01613   0.00863  -0.0518   0.7744   0.0227
  -7.250  -0.5077   0.01576   0.00819  -0.0508   0.7728   0.0232
  -7.000  -0.4917   0.01522   0.00763  -0.0491   0.7712   0.0240
  -6.750  -0.4739   0.01486   0.00724  -0.0477   0.7697   0.0247
  -6.500  -0.4551   0.01455   0.00690  -0.0464   0.7683   0.0254
  -6.250  -0.4352   0.01424   0.00659  -0.0453   0.7669   0.0262
  -6.000  -0.4140   0.01395   0.00628  -0.0444   0.7654   0.0272
  -5.750  -0.3922   0.01368   0.00597  -0.0436   0.7638   0.0280
  -5.500  -0.3708   0.01336   0.00563  -0.0427   0.7622   0.0288
  -5.250  -0.3495   0.01304   0.00529  -0.0419   0.7606   0.0300
  -5.000  -0.3268   0.01278   0.00502  -0.0412   0.7593   0.0314
  -4.750  -0.3035   0.01255   0.00478  -0.0407   0.7580   0.0329
  -4.500  -0.2796   0.01236   0.00455  -0.0402   0.7569   0.0345
  -4.250  -0.2564   0.01211   0.00431  -0.0396   0.7558   0.0378
  -4.000  -0.2324   0.01192   0.00411  -0.0392   0.7547   0.0421
  -3.750  -0.2090   0.01168   0.00392  -0.0386   0.7537   0.0522
  -3.500  -0.1882   0.01129   0.00370  -0.0377   0.7526   0.0920
  -3.250  -0.1703   0.01072   0.00346  -0.0364   0.7515   0.1722
  -3.000  -0.1551   0.00999   0.00319  -0.0346   0.7503   0.2842
  -2.750  -0.1422   0.00914   0.00289  -0.0325   0.7490   0.4190
  -2.500  -0.1349   0.00805   0.00262  -0.0291   0.7475   0.6057
  -2.250  -0.1114   0.00796   0.00274  -0.0282   0.7462   0.6827
  -2.000  -0.0850   0.00800   0.00284  -0.0280   0.7450   0.7104
  -1.750  -0.0575   0.00806   0.00292  -0.0280   0.7440   0.7267
  -1.500  -0.0297   0.00813   0.00300  -0.0280   0.7430   0.7380
  -1.250  -0.0019   0.00822   0.00306  -0.0281   0.7421   0.7488
  -1.000   0.0267   0.00827   0.00313  -0.0283   0.7410   0.7543
  -0.750   0.0554   0.00825   0.00306  -0.0286   0.7377   0.7580
  -0.500   0.0829   0.00815   0.00293  -0.0286   0.7289   0.7606
  -0.250   0.1113   0.00809   0.00281  -0.0289   0.7237   0.7626
   0.000   0.1400   0.00807   0.00273  -0.0292   0.7201   0.7640
   0.250   0.1686   0.00805   0.00273  -0.0296   0.7178   0.7653
   0.500   0.1971   0.00803   0.00273  -0.0300   0.7147   0.7665
   0.750   0.2257   0.00802   0.00273  -0.0303   0.7118   0.7680
   1.000   0.2543   0.00801   0.00274  -0.0307   0.7094   0.7695
   1.250   0.2829   0.00800   0.00269  -0.0310   0.7051   0.7711
   1.500   0.3106   0.00797   0.00271  -0.0312   0.6986   0.7727
   1.750   0.3385   0.00794   0.00266  -0.0313   0.6912   0.7743
   2.000   0.3661   0.00792   0.00266  -0.0315   0.6821   0.7761
   2.250   0.3932   0.00791   0.00263  -0.0315   0.6695   0.7780
   2.500   0.4200   0.00791   0.00261  -0.0315   0.6522   0.7799
   2.750   0.4435   0.00798   0.00254  -0.0307   0.6074   0.7816
   3.000   0.4513   0.00865   0.00277  -0.0271   0.5131   0.7836
   3.250   0.4567   0.00944   0.00320  -0.0233   0.4301   0.7859
   3.500   0.4610   0.01019   0.00362  -0.0193   0.3537   0.7884
   3.750   0.4640   0.01084   0.00401  -0.0151   0.2874   0.7913
   4.000   0.4641   0.01151   0.00441  -0.0103   0.2246   0.7944
   4.250   0.4551   0.01279   0.00515  -0.0046   0.1105   0.7980
   4.500   0.4597   0.01368   0.00575  -0.0011   0.0405   0.8009
   4.750   0.4782   0.01402   0.00608   0.0001   0.0326   0.8036
   5.000   0.4977   0.01434   0.00640   0.0011   0.0292   0.8064
   5.250   0.5176   0.01465   0.00672   0.0021   0.0267   0.8093
   5.500   0.5372   0.01499   0.00706   0.0030   0.0248   0.8123
   5.750   0.5574   0.01531   0.00739   0.0039   0.0239   0.8151
   6.000   0.5768   0.01564   0.00777   0.0049   0.0227   0.8178
   6.250   0.5959   0.01600   0.00816   0.0059   0.0219   0.8209
   6.500   0.6147   0.01639   0.00856   0.0069   0.0213   0.8243
   6.750   0.6340   0.01677   0.00898   0.0078   0.0211   0.8279
   7.000   0.6527   0.01719   0.00942   0.0088   0.0206   0.8314
   7.250   0.6710   0.01761   0.00989   0.0098   0.0203   0.8348
   7.500   0.6893   0.01804   0.01036   0.0109   0.0199   0.8387
   7.750   0.7072   0.01850   0.01087   0.0119   0.0196   0.8429
   8.000   0.7250   0.01900   0.01140   0.0129   0.0194   0.8473
   8.250   0.7424   0.01948   0.01193   0.0140   0.0191   0.8517
   8.500   0.7589   0.02002   0.01250   0.0152   0.0187   0.8568
   8.750   0.7750   0.02061   0.01312   0.0163   0.0182   0.8624
   9.000   0.7912   0.02119   0.01376   0.0175   0.0179   0.8677
   9.250   0.8069   0.02179   0.01442   0.0187   0.0176   0.8736
   9.500   0.8221   0.02244   0.01513   0.0199   0.0175   0.8801
   9.750   0.8368   0.02311   0.01586   0.0212   0.0171   0.8867
  10.000   0.8510   0.02381   0.01663   0.0225   0.0169   0.8946
  10.250   0.8646   0.02454   0.01743   0.0239   0.0166   0.9029
  10.500   0.8779   0.02530   0.01825   0.0252   0.0164   0.9131
  10.750   0.8908   0.02612   0.01915   0.0265   0.0161   0.9252
  11.000   0.9048   0.02705   0.02015   0.0274   0.0159   0.9402
  11.250   0.9227   0.02827   0.02144   0.0272   0.0156   0.9570
  11.500   0.9480   0.02933   0.02260   0.0255   0.0154   0.9783
  11.750   0.9623   0.03031   0.02363   0.0262   0.0152   1.0000
  12.000   0.9757   0.03134   0.02473   0.0271   0.0150   1.0000
  12.250   0.9890   0.03239   0.02584   0.0279   0.0148   1.0000
  12.500   1.0018   0.03352   0.02702   0.0288   0.0145   1.0000
  12.750   1.0146   0.03467   0.02824   0.0296   0.0144   1.0000
  13.000   1.0271   0.03587   0.02950   0.0304   0.0142   1.0000
  13.250   1.0392   0.03712   0.03081   0.0312   0.0140   1.0000
  13.500   1.0510   0.03841   0.03216   0.0319   0.0138   1.0000
  13.750   1.0625   0.03980   0.03357   0.0326   0.0136   1.0000
  14.000   1.0752   0.04128   0.03507   0.0333   0.0133   1.0000
  14.250   1.0831   0.04297   0.03690   0.0341   0.0130   1.0000
  14.500   1.0908   0.04465   0.03872   0.0348   0.0130   1.0000
  14.750   1.0961   0.04654   0.04078   0.0356   0.0128   1.0000
  15.000   1.1006   0.04860   0.04300   0.0362   0.0126   1.0000
  15.250   1.1055   0.05069   0.04522   0.0368   0.0126   1.0000
  15.500   1.1068   0.05313   0.04783   0.0373   0.0123   1.0000
  15.750   1.1063   0.05591   0.05077   0.0377   0.0122   1.0000
  16.000   1.1068   0.05860   0.05360   0.0378   0.0122   1.0000
  16.250   1.1040   0.06173   0.05689   0.0378   0.0120   1.0000
  16.500   1.0987   0.06533   0.06067   0.0376   0.0119   1.0000
  16.750   1.0953   0.06875   0.06422   0.0370   0.0118   1.0000
  17.000   1.0874   0.07299   0.06863   0.0361   0.0117   1.0000
  17.250   1.0780   0.07761   0.07343   0.0347   0.0117   1.0000
  17.500   1.0681   0.08254   0.07852   0.0330   0.0116   1.0000
  17.750   1.0593   0.08751   0.08362   0.0309   0.0115   1.0000
  18.000   1.0417   0.09427   0.09059   0.0278   0.0115   1.0000
  18.250   1.0283   0.10055   0.09702   0.0245   0.0115   1.0000
  18.500   1.0093   0.10829   0.10494   0.0202   0.0114   1.0000
  18.750   0.9745   0.11998   0.11691   0.0133   0.0115   1.0000
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