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NACA 642-015 AIRFOIL (n64015-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 642-015 AIRFOIL (n64015-il)
Reynolds number: 50,000
Max Cl/Cd: 27.61 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64015-il-50000.txt
Download as CSV file: xf-n64015-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 642-015 AIRFOIL                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.7022   0.09685   0.08975  -0.0232   1.0000   0.1450
 -11.500  -0.8154   0.08237   0.07508  -0.0332   1.0000   0.1310
 -11.250  -0.8229   0.07723   0.06989  -0.0338   1.0000   0.1301
 -11.000  -0.8393   0.07256   0.06511  -0.0338   1.0000   0.1290
 -10.750  -0.8592   0.06847   0.06088  -0.0327   1.0000   0.1280
 -10.500  -0.8769   0.06466   0.05685  -0.0310   1.0000   0.1273
 -10.250  -0.8892   0.06093   0.05285  -0.0293   1.0000   0.1270
 -10.000  -0.8953   0.05738   0.04898  -0.0275   1.0000   0.1271
  -9.750  -0.8962   0.05397   0.04522  -0.0257   1.0000   0.1276
  -9.500  -0.8924   0.05071   0.04157  -0.0240   1.0000   0.1283
  -9.250  -0.8836   0.04761   0.03805  -0.0224   1.0000   0.1292
  -9.000  -0.8746   0.04502   0.03495  -0.0205   1.0000   0.1312
  -8.750  -0.8473   0.04196   0.03205  -0.0209   1.0000   0.1373
  -8.500  -0.8271   0.03963   0.02943  -0.0200   1.0000   0.1427
  -8.250  -0.7993   0.03713   0.02684  -0.0198   1.0000   0.1501
  -8.000  -0.7741   0.03528   0.02479  -0.0192   1.0000   0.1607
  -7.750  -0.7315   0.03299   0.02279  -0.0205   1.0000   0.1794
  -7.500  -0.7011   0.03117   0.02118  -0.0202   1.0000   0.2057
  -7.250  -0.6882   0.02928   0.01980  -0.0179   1.0000   0.2408
  -7.000  -0.6962   0.02745   0.01865  -0.0130   1.0000   0.2859
  -6.750  -0.7170   0.02597   0.01828  -0.0057   1.0000   0.3562
  -6.500  -0.7313   0.02777   0.02105   0.0049   1.0000   0.5124
  -6.250  -0.4865   0.04727   0.03925   0.0053   1.0000   0.6469
  -5.750  -0.3832   0.04903   0.04042   0.0048   1.0000   0.7144
  -5.500  -0.3317   0.04855   0.03969   0.0026   1.0000   0.7419
  -5.250  -0.3132   0.04786   0.03891   0.0033   1.0000   0.7634
  -5.000  -0.3006   0.04722   0.03822   0.0047   1.0000   0.7817
  -4.750  -0.2864   0.04657   0.03753   0.0058   1.0000   0.7980
  -4.500  -0.2723   0.04593   0.03682   0.0068   1.0000   0.8127
  -4.250  -0.2638   0.04540   0.03624   0.0084   1.0000   0.8256
  -4.000  -0.2783   0.04518   0.03603   0.0130   1.0000   0.8347
  -3.750  -0.2754   0.04474   0.03555   0.0151   1.0000   0.8447
  -3.500  -0.2721   0.04424   0.03501   0.0170   1.0000   0.8540
  -3.250  -0.2792   0.04389   0.03464   0.0203   1.0000   0.8618
  -3.000  -0.2741   0.04336   0.03406   0.0217   1.0000   0.8695
  -2.750  -0.2744   0.04292   0.03357   0.0240   1.0000   0.8767
  -2.500  -0.2777   0.04245   0.03308   0.0267   1.0000   0.8834
  -2.250  -0.2655   0.04196   0.03253   0.0269   1.0000   0.8907
  -2.000  -0.2785   0.04155   0.03210   0.0313   1.0000   0.8972
  -1.750  -0.2442   0.04108   0.03155   0.0277   0.9979   0.9042
  -1.500  -0.2136   0.04081   0.03119   0.0243   0.9902   0.9115
  -1.250  -0.1616   0.04054   0.03084   0.0173   0.9831   0.9184
  -1.000  -0.1321   0.04031   0.03055   0.0143   0.9757   0.9251
  -0.750  -0.0951   0.04015   0.03035   0.0099   0.9695   0.9312
  -0.500  -0.0626   0.03998   0.03015   0.0065   0.9625   0.9375
  -0.250  -0.0327   0.04000   0.03015   0.0035   0.9561   0.9438
   0.000   0.0003   0.03987   0.03002  -0.0001   0.9496   0.9497
   0.250   0.0331   0.04000   0.03015  -0.0036   0.9438   0.9562
   0.500   0.0635   0.03997   0.03015  -0.0067   0.9373   0.9627
   0.750   0.0954   0.04015   0.03035  -0.0100   0.9312   0.9695
   1.000   0.1326   0.04030   0.03054  -0.0144   0.9251   0.9758
   1.250   0.1624   0.04053   0.03083  -0.0174   0.9183   0.9832
   1.500   0.2144   0.04080   0.03118  -0.0244   0.9115   0.9904
   1.750   0.2445   0.04107   0.03154  -0.0277   0.9043   0.9981
   2.000   0.2798   0.04154   0.03209  -0.0315   0.8971   1.0000
   2.250   0.2655   0.04195   0.03251  -0.0270   0.8907   1.0000
   2.500   0.2771   0.04243   0.03306  -0.0266   0.8835   1.0000
   2.750   0.2744   0.04290   0.03356  -0.0240   0.8767   1.0000
   3.000   0.2746   0.04334   0.03405  -0.0218   0.8694   1.0000
   3.250   0.2791   0.04387   0.03462  -0.0203   0.8617   1.0000
   3.500   0.2728   0.04422   0.03499  -0.0170   0.8538   1.0000
   3.750   0.2755   0.04472   0.03553  -0.0151   0.8448   1.0000
   4.000   0.2771   0.04514   0.03599  -0.0129   0.8349   1.0000
   4.250   0.2639   0.04537   0.03621  -0.0084   0.8255   1.0000
   4.500   0.2725   0.04592   0.03682  -0.0069   0.8129   1.0000
   4.750   0.2866   0.04655   0.03751  -0.0059   0.7981   1.0000
   5.000   0.3004   0.04719   0.03819  -0.0047   0.7817   1.0000
   5.250   0.3133   0.04783   0.03888  -0.0033   0.7633   1.0000
   5.500   0.3320   0.04853   0.03966  -0.0026   0.7418   1.0000
   5.750   0.3833   0.04901   0.04040  -0.0048   0.7144   1.0000
   6.000   0.4398   0.04859   0.04027  -0.0061   0.6825   1.0000
   6.250   0.4866   0.04726   0.03925  -0.0053   0.6469   1.0000
   6.500   0.7313   0.02776   0.02105  -0.0049   0.5124   1.0000
   6.750   0.7170   0.02597   0.01827   0.0057   0.3559   1.0000
   7.000   0.6963   0.02744   0.01864   0.0130   0.2859   1.0000
   7.250   0.6883   0.02928   0.01980   0.0179   0.2408   1.0000
   7.500   0.7012   0.03117   0.02117   0.0202   0.2057   1.0000
   7.750   0.7318   0.03301   0.02279   0.0204   0.1790   1.0000
   8.000   0.7740   0.03527   0.02479   0.0193   0.1607   1.0000
   8.250   0.7993   0.03713   0.02683   0.0198   0.1499   1.0000
   8.500   0.8272   0.03963   0.02943   0.0200   0.1427   1.0000
   8.750   0.8474   0.04196   0.03205   0.0209   0.1373   1.0000
   9.000   0.8748   0.04502   0.03496   0.0205   0.1312   1.0000
   9.250   0.8839   0.04761   0.03805   0.0224   0.1292   1.0000
   9.500   0.8923   0.05072   0.04159   0.0240   0.1282   1.0000
   9.750   0.8963   0.05398   0.04523   0.0257   0.1276   1.0000
  10.000   0.8949   0.05738   0.04899   0.0275   0.1270   1.0000
  10.250   0.8890   0.06094   0.05286   0.0293   0.1268   1.0000
  10.500   0.8769   0.06466   0.05686   0.0310   0.1272   1.0000
  10.750   0.8595   0.06848   0.06089   0.0326   0.1280   1.0000
  11.000   0.8398   0.07259   0.06514   0.0337   0.1290   1.0000
  11.250   0.8203   0.07729   0.06995   0.0338   0.1299   1.0000
  11.500   0.8168   0.08245   0.07516   0.0331   0.1311   1.0000
  11.750   0.6404   0.10788   0.10068   0.0128   0.1575   1.0000
  12.000   0.6620   0.11151   0.10435   0.0138   0.1609   1.0000
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