Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 67 (naca671215-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA 67 (naca671215-il)
Reynolds number: 500,000
Max Cl/Cd: 55.45 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca671215-il-500000-n5.txt
Download as CSV file: xf-naca671215-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 67                                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -17.750  -0.6768   0.10901   0.10621  -0.0794   0.9717   0.0135
 -17.500  -0.7888   0.08096   0.07773  -0.0954   0.9709   0.0132
 -17.250  -0.8197   0.06977   0.06628  -0.1039   0.9681   0.0131
 -17.000  -0.8367   0.06173   0.05798  -0.1105   0.9649   0.0131
 -16.750  -0.8447   0.05582   0.05184  -0.1154   0.9612   0.0133
 -16.500  -0.8498   0.05108   0.04689  -0.1188   0.9568   0.0133
 -16.250  -0.8529   0.04708   0.04266  -0.1212   0.9523   0.0134
 -16.000  -0.8556   0.04382   0.03921  -0.1222   0.9475   0.0135
 -15.750  -0.8563   0.04128   0.03647  -0.1223   0.9423   0.0136
 -15.500  -0.8561   0.03896   0.03395  -0.1220   0.9376   0.0137
 -15.250  -0.8561   0.03694   0.03177  -0.1210   0.9332   0.0138
 -15.000  -0.8554   0.03513   0.02980  -0.1196   0.9286   0.0139
 -14.750  -0.8540   0.03340   0.02795  -0.1182   0.9244   0.0141
 -14.500  -0.8487   0.03205   0.02650  -0.1169   0.9209   0.0143
 -14.250  -0.8432   0.03078   0.02512  -0.1152   0.9171   0.0143
 -14.000  -0.8361   0.02965   0.02389  -0.1137   0.9134   0.0145
 -13.750  -0.8269   0.02864   0.02279  -0.1122   0.9101   0.0147
 -13.500  -0.8175   0.02764   0.02168  -0.1107   0.9071   0.0148
 -13.250  -0.8054   0.02688   0.02083  -0.1094   0.9045   0.0152
 -13.000  -0.7947   0.02596   0.01982  -0.1078   0.9016   0.0154
 -12.750  -0.7820   0.02521   0.01898  -0.1065   0.8988   0.0157
 -12.500  -0.7691   0.02441   0.01809  -0.1050   0.8961   0.0160
 -12.250  -0.7555   0.02365   0.01723  -0.1037   0.8936   0.0163
 -12.000  -0.7414   0.02291   0.01637  -0.1023   0.8912   0.0165
 -11.750  -0.7265   0.02221   0.01557  -0.1009   0.8891   0.0168
 -11.500  -0.7113   0.02155   0.01483  -0.0996   0.8869   0.0170
 -11.250  -0.6966   0.02088   0.01410  -0.0982   0.8847   0.0173
 -11.000  -0.6811   0.02025   0.01344  -0.0969   0.8826   0.0178
 -10.750  -0.6640   0.01973   0.01288  -0.0957   0.8807   0.0182
 -10.500  -0.6465   0.01924   0.01233  -0.0946   0.8790   0.0186
 -10.250  -0.6285   0.01876   0.01180  -0.0935   0.8773   0.0192
 -10.000  -0.6102   0.01830   0.01127  -0.0924   0.8758   0.0199
  -9.750  -0.5913   0.01787   0.01076  -0.0914   0.8744   0.0207
  -9.500  -0.5731   0.01742   0.01029  -0.0903   0.8730   0.0215
  -9.250  -0.5541   0.01703   0.00990  -0.0893   0.8715   0.0225
  -9.000  -0.5347   0.01668   0.00952  -0.0883   0.8700   0.0235
  -8.750  -0.5151   0.01633   0.00912  -0.0873   0.8684   0.0247
  -8.500  -0.4958   0.01595   0.00871  -0.0862   0.8668   0.0261
  -8.250  -0.4761   0.01561   0.00836  -0.0852   0.8652   0.0273
  -8.000  -0.4555   0.01532   0.00804  -0.0843   0.8639   0.0289
  -7.750  -0.4349   0.01503   0.00771  -0.0834   0.8627   0.0302
  -7.500  -0.4149   0.01471   0.00736  -0.0824   0.8615   0.0316
  -7.250  -0.3943   0.01441   0.00706  -0.0815   0.8604   0.0332
  -7.000  -0.3731   0.01415   0.00678  -0.0807   0.8594   0.0349
  -6.750  -0.3517   0.01392   0.00650  -0.0798   0.8584   0.0364
  -6.500  -0.3313   0.01368   0.00625  -0.0788   0.8573   0.0380
  -6.250  -0.3112   0.01342   0.00602  -0.0778   0.8562   0.0408
  -6.000  -0.2903   0.01321   0.00582  -0.0768   0.8550   0.0438
  -5.750  -0.2699   0.01298   0.00560  -0.0758   0.8536   0.0471
  -5.500  -0.2496   0.01275   0.00539  -0.0747   0.8522   0.0515
  -5.250  -0.2289   0.01255   0.00519  -0.0736   0.8510   0.0560
  -5.000  -0.2088   0.01231   0.00498  -0.0725   0.8498   0.0631
  -4.750  -0.1890   0.01208   0.00480  -0.0712   0.8487   0.0743
  -4.500  -0.1704   0.01180   0.00461  -0.0698   0.8476   0.0944
  -4.250  -0.1531   0.01151   0.00443  -0.0681   0.8465   0.1247
  -4.000  -0.1379   0.01118   0.00427  -0.0660   0.8454   0.1663
  -3.750  -0.1259   0.01083   0.00413  -0.0633   0.8442   0.2195
  -3.500  -0.1157   0.01049   0.00400  -0.0601   0.8428   0.2780
  -3.250  -0.1095   0.01015   0.00393  -0.0561   0.8411   0.3440
  -3.000  -0.1041   0.00976   0.00384  -0.0520   0.8393   0.4177
  -2.750  -0.1021   0.00928   0.00371  -0.0471   0.8372   0.5051
  -2.500  -0.1038   0.00861   0.00354  -0.0413   0.8349   0.6192
  -2.250  -0.0918   0.00840   0.00383  -0.0378   0.8333   0.7344
  -2.000  -0.0676   0.00855   0.00401  -0.0370   0.8324   0.7681
  -1.750  -0.0426   0.00876   0.00424  -0.0363   0.8314   0.7895
  -1.500  -0.0164   0.00916   0.00466  -0.0356   0.8305   0.8093
  -1.250   0.0136   0.00952   0.00505  -0.0357   0.8297   0.8188
  -1.000   0.0422   0.00966   0.00517  -0.0359   0.8289   0.8230
  -0.750   0.0699   0.00964   0.00512  -0.0361   0.8280   0.8251
  -0.500   0.0960   0.00962   0.00507  -0.0360   0.8269   0.8272
  -0.250   0.1159   0.00965   0.00509  -0.0347   0.8248   0.8294
   0.000   0.1400   0.00970   0.00516  -0.0342   0.8228   0.8305
   0.250   0.1652   0.00975   0.00523  -0.0339   0.8209   0.8316
   0.500   0.1913   0.00977   0.00526  -0.0337   0.8192   0.8326
   0.750   0.2182   0.00977   0.00527  -0.0337   0.8176   0.8335
   1.000   0.2462   0.00976   0.00526  -0.0340   0.8161   0.8346
   1.250   0.2761   0.00969   0.00520  -0.0346   0.8146   0.8355
   1.500   0.3093   0.00955   0.00505  -0.0358   0.8126   0.8362
   1.750   0.3303   0.00949   0.00502  -0.0345   0.8074   0.8375
   2.000   0.3557   0.00931   0.00485  -0.0340   0.8013   0.8388
   2.250   0.3922   0.00900   0.00450  -0.0357   0.7957   0.8395
   2.500   0.4066   0.00889   0.00443  -0.0330   0.7855   0.8411
   2.750   0.4275   0.00870   0.00425  -0.0315   0.7740   0.8424
   3.000   0.4429   0.00853   0.00408  -0.0289   0.7555   0.8438
   3.250   0.4607   0.00833   0.00380  -0.0267   0.7233   0.8452
   3.500   0.4658   0.00840   0.00348  -0.0216   0.6450   0.8468
   3.750   0.4504   0.00896   0.00371  -0.0127   0.5730   0.8488
   4.000   0.4413   0.00967   0.00414  -0.0055   0.5107   0.8509
   4.250   0.4387   0.01036   0.00457   0.0000   0.4514   0.8528
   4.500   0.4412   0.01102   0.00498   0.0045   0.3918   0.8546
   4.750   0.4474   0.01166   0.00536   0.0080   0.3332   0.8565
   5.000   0.4563   0.01230   0.00573   0.0110   0.2738   0.8584
   5.250   0.4680   0.01288   0.00606   0.0135   0.2199   0.8599
   5.500   0.4827   0.01339   0.00637   0.0153   0.1774   0.8612
   5.750   0.4986   0.01386   0.00669   0.0170   0.1405   0.8623
   6.000   0.5155   0.01430   0.00701   0.0185   0.1116   0.8635
   6.250   0.5328   0.01474   0.00734   0.0199   0.0872   0.8646
   6.500   0.5510   0.01514   0.00767   0.0212   0.0696   0.8658
   6.750   0.5697   0.01554   0.00801   0.0224   0.0579   0.8670
   7.000   0.5892   0.01590   0.00835   0.0234   0.0515   0.8683
   7.250   0.6084   0.01628   0.00870   0.0244   0.0451   0.8696
   7.500   0.6285   0.01661   0.00905   0.0253   0.0418   0.8711
   7.750   0.6480   0.01698   0.00941   0.0263   0.0386   0.8728
   8.000   0.6673   0.01737   0.00980   0.0273   0.0361   0.8744
   8.250   0.6875   0.01771   0.01017   0.0281   0.0342   0.8759
   8.500   0.7071   0.01810   0.01057   0.0290   0.0323   0.8773
   8.750   0.7258   0.01853   0.01100   0.0300   0.0303   0.8787
   9.000   0.7444   0.01894   0.01146   0.0310   0.0293   0.8801
   9.250   0.7633   0.01933   0.01191   0.0320   0.0276   0.8816
   9.500   0.7817   0.01977   0.01237   0.0330   0.0262   0.8832
   9.750   0.7991   0.02029   0.01290   0.0342   0.0247   0.8850
  10.000   0.8173   0.02075   0.01342   0.0351   0.0236   0.8868
  10.250   0.8355   0.02122   0.01394   0.0361   0.0218   0.8888
  10.500   0.8527   0.02175   0.01449   0.0372   0.0207   0.8908
  10.750   0.8694   0.02234   0.01511   0.0383   0.0195   0.8929
  11.000   0.8864   0.02290   0.01572   0.0393   0.0184   0.8948
  11.250   0.9026   0.02347   0.01635   0.0405   0.0176   0.8969
  11.500   0.9174   0.02413   0.01705   0.0418   0.0166   0.8993
  11.750   0.9321   0.02482   0.01779   0.0431   0.0161   0.9019
  12.000   0.9466   0.02554   0.01858   0.0443   0.0154   0.9047
  12.250   0.9613   0.02625   0.01936   0.0455   0.0152   0.9073
  12.500   0.9752   0.02704   0.02022   0.0467   0.0146   0.9100
  12.750   0.9883   0.02783   0.02108   0.0480   0.0143   0.9125
  13.000   1.0008   0.02867   0.02199   0.0494   0.0141   0.9154
  13.250   1.0124   0.02959   0.02297   0.0507   0.0136   0.9186
  13.500   1.0228   0.03062   0.02406   0.0521   0.0133   0.9220
  13.750   1.0319   0.03180   0.02531   0.0535   0.0131   0.9253
  14.000   1.0414   0.03290   0.02653   0.0549   0.0130   0.9286
  14.250   1.0501   0.03409   0.02782   0.0563   0.0130   0.9326
  14.500   1.0579   0.03541   0.02926   0.0576   0.0127   0.9367
  14.750   1.0662   0.03673   0.03069   0.0588   0.0126   0.9408
  15.000   1.0742   0.03818   0.03226   0.0597   0.0124   0.9454
  15.250   1.0823   0.03974   0.03393   0.0604   0.0123   0.9505
  15.500   1.0913   0.04153   0.03586   0.0605   0.0121   0.9552
  15.750   1.0999   0.04361   0.03807   0.0602   0.0120   0.9602
  16.000   1.1095   0.04578   0.04038   0.0595   0.0119   0.9656
  16.250   1.1193   0.04814   0.04288   0.0583   0.0118   0.9715
  16.500   1.1240   0.05088   0.04577   0.0573   0.0117   0.9893
  16.750   1.1237   0.05336   0.04835   0.0578   0.0115   1.0000
  17.000   1.1243   0.05606   0.05115   0.0577   0.0113   1.0000
  17.250   1.1240   0.05895   0.05416   0.0574   0.0113   1.0000
  17.500   1.1204   0.06235   0.05768   0.0569   0.0112   1.0000
  17.750   1.1148   0.06618   0.06164   0.0560   0.0111   1.0000
  18.000   1.1089   0.07020   0.06579   0.0548   0.0111   1.0000
  18.250   1.1017   0.07462   0.07034   0.0532   0.0110   1.0000
  18.500   1.0897   0.07993   0.07580   0.0511   0.0110   1.0000
  18.750   1.0802   0.08511   0.08111   0.0486   0.0109   1.0000
  19.000   1.0677   0.09099   0.08713   0.0456   0.0109   1.0000
  19.250   1.0514   0.09777   0.09406   0.0421   0.0108   1.0000
<< Back to NACA 67 (naca671215-il)

Polar data table (+)

Polar graphs


<< Back to NACA 67 (naca671215-il)