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NACA 63-215 AIRFOIL (n63215-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-215 AIRFOIL (n63215-il)
Reynolds number: 50,000
Max Cl/Cd: 28.52 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n63215-il-50000-n5.txt
Download as CSV file: xf-n63215-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-215 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.6930   0.08621   0.07839  -0.0455   1.0000   0.0617
 -12.500  -0.7193   0.07934   0.07138  -0.0494   1.0000   0.0615
 -12.250  -0.7432   0.07354   0.06542  -0.0523   1.0000   0.0614
 -12.000  -0.7642   0.06867   0.06035  -0.0541   1.0000   0.0615
 -11.750  -0.7837   0.06439   0.05584  -0.0549   1.0000   0.0616
 -11.500  -0.7997   0.06073   0.05190  -0.0548   1.0000   0.0619
 -11.250  -0.7992   0.05774   0.04883  -0.0543   1.0000   0.0627
 -11.000  -0.7966   0.05518   0.04616  -0.0535   1.0000   0.0638
 -10.750  -0.7942   0.05289   0.04376  -0.0525   1.0000   0.0653
 -10.500  -0.7906   0.05066   0.04137  -0.0513   1.0000   0.0672
 -10.250  -0.7856   0.04831   0.03877  -0.0502   1.0000   0.0693
 -10.000  -0.7779   0.04595   0.03607  -0.0489   1.0000   0.0713
  -9.750  -0.7630   0.04375   0.03366  -0.0481   1.0000   0.0735
  -9.500  -0.7446   0.04212   0.03205  -0.0474   1.0000   0.0768
  -9.250  -0.7278   0.04054   0.03034  -0.0464   1.0000   0.0806
  -9.000  -0.7071   0.03896   0.02847  -0.0455   1.0000   0.0844
  -8.750  -0.6857   0.03764   0.02730  -0.0447   1.0000   0.0889
  -8.500  -0.6684   0.03651   0.02610  -0.0433   1.0000   0.0944
  -8.250  -0.6520   0.03543   0.02496  -0.0416   1.0000   0.0998
  -8.000  -0.6443   0.03449   0.02410  -0.0391   1.0000   0.1050
  -7.750  -0.6401   0.03370   0.02323  -0.0360   1.0000   0.1113
  -7.500  -0.6431   0.03288   0.02254  -0.0323   1.0000   0.1167
  -7.250  -0.6459   0.03215   0.02181  -0.0284   1.0000   0.1236
  -7.000  -0.6494   0.03133   0.02105  -0.0247   1.0000   0.1306
  -6.750  -0.6347   0.03003   0.01984  -0.0245   0.9930   0.1476
  -6.500  -0.6111   0.02825   0.01833  -0.0263   0.9814   0.1833
  -6.250  -0.5904   0.02636   0.01700  -0.0279   0.9701   0.2524
  -6.000  -0.5671   0.02534   0.01677  -0.0285   0.9599   0.3647
  -5.750  -0.5397   0.02544   0.01705  -0.0285   0.9497   0.4457
  -5.500  -0.5078   0.02590   0.01746  -0.0288   0.9411   0.4983
  -5.250  -0.4761   0.02644   0.01784  -0.0291   0.9322   0.5385
  -5.000  -0.4441   0.02733   0.01865  -0.0284   0.9240   0.5660
  -4.750  -0.4121   0.02779   0.01894  -0.0285   0.9160   0.5896
  -4.500  -0.3825   0.02826   0.01925  -0.0279   0.9073   0.6071
  -4.250  -0.3504   0.02855   0.01939  -0.0281   0.8998   0.6233
  -4.000  -0.3239   0.02869   0.01938  -0.0275   0.8908   0.6371
  -3.750  -0.2905   0.02890   0.01944  -0.0278   0.8836   0.6470
  -3.500  -0.2669   0.02878   0.01917  -0.0273   0.8743   0.6583
  -3.250  -0.2371   0.02869   0.01894  -0.0277   0.8669   0.6685
  -3.000  -0.2134   0.02866   0.01879  -0.0270   0.8578   0.6772
  -2.750  -0.1869   0.02841   0.01839  -0.0273   0.8503   0.6882
  -2.500  -0.1627   0.02848   0.01839  -0.0264   0.8416   0.6951
  -2.250  -0.1376   0.02821   0.01798  -0.0266   0.8340   0.7058
  -2.000  -0.1131   0.02829   0.01801  -0.0258   0.8258   0.7122
  -1.750  -0.0891   0.02808   0.01768  -0.0258   0.8181   0.7225
  -1.500  -0.0632   0.02812   0.01767  -0.0252   0.8107   0.7287
  -1.250  -0.0408   0.02801   0.01747  -0.0249   0.8025   0.7383
  -1.000  -0.0121   0.02797   0.01739  -0.0248   0.7966   0.7450
  -0.750   0.0065   0.02798   0.01735  -0.0239   0.7873   0.7543
  -0.500   0.0365   0.02790   0.01723  -0.0241   0.7820   0.7613
  -0.250   0.0538   0.02800   0.01731  -0.0230   0.7726   0.7705
   0.000   0.0813   0.02797   0.01725  -0.0228   0.7666   0.7781
   0.250   0.1004   0.02807   0.01734  -0.0219   0.7584   0.7875
   0.500   0.1251   0.02811   0.01738  -0.0214   0.7516   0.7953
   0.750   0.1498   0.02812   0.01737  -0.0211   0.7455   0.8050
   1.000   0.1689   0.02832   0.01762  -0.0200   0.7369   0.8132
   1.250   0.1967   0.02826   0.01755  -0.0201   0.7319   0.8232
   1.500   0.2132   0.02858   0.01793  -0.0187   0.7228   0.8322
   1.750   0.2394   0.02860   0.01797  -0.0184   0.7169   0.8419
   2.000   0.2595   0.02883   0.01825  -0.0176   0.7094   0.8524
   2.250   0.2828   0.02899   0.01847  -0.0171   0.7021   0.8624
   2.500   0.3137   0.02891   0.01843  -0.0173   0.6976   0.8728
   2.750   0.3275   0.02941   0.01903  -0.0160   0.6874   0.8852
   3.000   0.3610   0.02936   0.01906  -0.0167   0.6823   0.8952
   3.250   0.3798   0.02984   0.01965  -0.0162   0.6728   0.9083
   3.500   0.4133   0.02984   0.01973  -0.0172   0.6668   0.9201
   3.750   0.4397   0.03027   0.02030  -0.0180   0.6579   0.9338
   4.000   0.4794   0.03033   0.02048  -0.0202   0.6510   0.9447
   4.250   0.5147   0.03070   0.02102  -0.0225   0.6421   0.9575
   4.500   0.5578   0.03072   0.02119  -0.0254   0.6345   0.9688
   4.750   0.5948   0.03112   0.02176  -0.0281   0.6241   0.9834
   5.000   0.6422   0.03079   0.02161  -0.0311   0.6165   0.9960
   5.250   0.6388   0.03143   0.02231  -0.0275   0.6046   1.0000
   5.500   0.6554   0.03143   0.02237  -0.0257   0.5950   1.0000
   5.750   0.6785   0.03125   0.02230  -0.0247   0.5844   1.0000
   6.000   0.6947   0.03150   0.02263  -0.0232   0.5709   1.0000
   6.250   0.7168   0.03146   0.02270  -0.0222   0.5572   1.0000
   6.500   0.7421   0.03118   0.02254  -0.0213   0.5427   1.0000
   6.750   0.7671   0.03079   0.02228  -0.0201   0.5258   1.0000
   7.000   0.7923   0.03020   0.02180  -0.0188   0.5059   1.0000
   7.250   0.8140   0.02972   0.02139  -0.0170   0.4822   1.0000
   7.500   0.8326   0.02937   0.02110  -0.0150   0.4536   1.0000
   7.750   0.8438   0.02959   0.02135  -0.0128   0.4197   1.0000
   8.000   0.8529   0.02995   0.02166  -0.0103   0.3790   1.0000
   8.250   0.8612   0.03043   0.02190  -0.0077   0.3294   1.0000
   8.500   0.8644   0.03160   0.02269  -0.0053   0.2772   1.0000
   8.750   0.8631   0.03344   0.02414  -0.0032   0.2330   1.0000
   9.000   0.8614   0.03561   0.02602  -0.0017   0.1984   1.0000
   9.250   0.8600   0.03797   0.02810  -0.0005   0.1719   1.0000
   9.500   0.8620   0.04023   0.03022   0.0005   0.1512   1.0000
   9.750   0.8652   0.04247   0.03233   0.0013   0.1352   1.0000
  10.000   0.8708   0.04460   0.03438   0.0021   0.1226   1.0000
  10.250   0.8783   0.04661   0.03629   0.0028   0.1133   1.0000
  10.500   0.8898   0.04841   0.03815   0.0035   0.1042   1.0000
  10.750   0.9028   0.05013   0.03987   0.0042   0.0971   1.0000
  11.000   0.9184   0.05174   0.04153   0.0049   0.0907   1.0000
  11.250   0.9368   0.05327   0.04309   0.0056   0.0852   1.0000
  11.500   0.9545   0.05497   0.04499   0.0062   0.0800   1.0000
  11.750   0.9785   0.05632   0.04625   0.0068   0.0757   1.0000
  12.000   0.9923   0.05867   0.04893   0.0072   0.0722   1.0000
  12.250   1.0034   0.06111   0.05159   0.0075   0.0690   1.0000
  12.500   1.0154   0.06344   0.05400   0.0077   0.0663   1.0000
  12.750   1.0299   0.06591   0.05653   0.0079   0.0641   1.0000
  13.000   1.0243   0.06982   0.06083   0.0076   0.0627   1.0000
  13.250   1.0165   0.07408   0.06541   0.0069   0.0615   1.0000
  13.500   1.0059   0.07873   0.07035   0.0058   0.0604   1.0000
  13.750   0.9923   0.08391   0.07579   0.0041   0.0596   1.0000
  14.000   0.9741   0.09001   0.08214   0.0016   0.0593   1.0000
  14.250   0.9488   0.09752   0.08991  -0.0022   0.0592   1.0000
  14.500   0.9130   0.10770   0.10033  -0.0082   0.0599   1.0000
  14.750   0.8686   0.12149   0.11433  -0.0169   0.0610   1.0000
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