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

N-14 (n14-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: N-14 (n14-il)
Reynolds number: 500,000
Max Cl/Cd: 56.1 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n14-il-500000.txt
Download as CSV file: xf-n14-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-14                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.500  -0.9901   0.08438   0.08106  -0.0401   1.0000   0.0195
 -16.250  -1.0146   0.07615   0.07266  -0.0453   1.0000   0.0195
 -16.000  -1.0359   0.06911   0.06546  -0.0495   1.0000   0.0196
 -15.750  -1.0496   0.06373   0.05995  -0.0524   1.0000   0.0198
 -15.500  -1.0577   0.05954   0.05567  -0.0544   1.0000   0.0200
 -15.250  -1.0634   0.05595   0.05200  -0.0559   1.0000   0.0202
 -15.000  -1.0754   0.05174   0.04763  -0.0572   1.0000   0.0203
 -14.750  -1.0779   0.04911   0.04493  -0.0577   1.0000   0.0206
 -14.500  -1.0844   0.04614   0.04182  -0.0577   1.0000   0.0209
 -14.250  -1.0881   0.04374   0.03931  -0.0572   1.0000   0.0212
 -14.000  -1.0912   0.04150   0.03693  -0.0562   1.0000   0.0215
 -13.750  -1.0928   0.03962   0.03493  -0.0549   1.0000   0.0220
 -13.500  -1.0955   0.03773   0.03288  -0.0531   1.0000   0.0224
 -13.250  -1.0974   0.03608   0.03106  -0.0508   1.0000   0.0229
 -13.000  -1.0976   0.03493   0.02974  -0.0483   1.0000   0.0233
 -12.750  -1.0973   0.03378   0.02844  -0.0454   1.0000   0.0235
 -12.500  -1.0982   0.03117   0.02567  -0.0426   1.0000   0.0242
 -12.250  -1.0918   0.03009   0.02458  -0.0401   1.0000   0.0247
 -12.000  -1.0858   0.02918   0.02361  -0.0372   1.0000   0.0252
 -11.750  -1.0805   0.02848   0.02284  -0.0340   1.0000   0.0257
 -11.500  -1.0759   0.02776   0.02204  -0.0304   1.0000   0.0263
 -11.250  -1.0702   0.02707   0.02126  -0.0269   1.0000   0.0269
 -11.000  -1.0609   0.02633   0.02042  -0.0239   1.0000   0.0276
 -10.750  -1.0510   0.02589   0.01986  -0.0210   1.0000   0.0284
 -10.500  -1.0404   0.02513   0.01897  -0.0182   1.0000   0.0289
 -10.250  -1.0283   0.02328   0.01706  -0.0161   1.0000   0.0299
 -10.000  -1.0158   0.02253   0.01630  -0.0137   1.0000   0.0306
  -9.750  -1.0026   0.02198   0.01572  -0.0112   1.0000   0.0315
  -9.500  -0.9891   0.02140   0.01509  -0.0088   1.0000   0.0324
  -9.250  -0.9751   0.02086   0.01449  -0.0064   1.0000   0.0334
  -9.000  -0.9608   0.02033   0.01388  -0.0039   1.0000   0.0341
  -8.750  -0.9461   0.01992   0.01339  -0.0016   1.0000   0.0347
  -8.500  -0.9348   0.01885   0.01225   0.0013   1.0000   0.0356
  -8.250  -0.9245   0.01797   0.01137   0.0043   1.0000   0.0367
  -8.000  -0.9120   0.01748   0.01086   0.0070   1.0000   0.0378
  -7.750  -0.8995   0.01703   0.01038   0.0097   1.0000   0.0387
  -7.500  -0.8871   0.01661   0.00992   0.0125   1.0000   0.0396
  -7.250  -0.8605   0.01614   0.00940   0.0124   0.9986   0.0409
  -7.000  -0.8268   0.01576   0.00896   0.0109   0.9961   0.0420
  -6.750  -0.7958   0.01493   0.00809   0.0097   0.9936   0.0439
  -6.500  -0.7660   0.01431   0.00746   0.0089   0.9901   0.0457
  -6.250  -0.7336   0.01386   0.00699   0.0076   0.9870   0.0479
  -6.000  -0.6992   0.01347   0.00655   0.0060   0.9847   0.0502
  -5.750  -0.6650   0.01297   0.00605   0.0044   0.9827   0.0542
  -5.500  -0.6372   0.01252   0.00561   0.0042   0.9775   0.0593
  -5.250  -0.6048   0.01203   0.00536   0.0030   0.9742   0.0908
  -5.000  -0.5684   0.01184   0.00520   0.0010   0.9721   0.1099
  -4.750  -0.5323   0.01153   0.00494  -0.0009   0.9705   0.1207
  -4.500  -0.5061   0.01128   0.00468  -0.0007   0.9643   0.1277
  -4.250  -0.4729   0.01100   0.00442  -0.0019   0.9612   0.1351
  -4.000  -0.4378   0.01071   0.00417  -0.0036   0.9591   0.1435
  -3.750  -0.4016   0.01036   0.00391  -0.0055   0.9574   0.1587
  -3.500  -0.3745   0.00990   0.00366  -0.0055   0.9515   0.2001
  -3.250  -0.3422   0.00937   0.00339  -0.0067   0.9472   0.2609
  -3.000  -0.3069   0.00889   0.00314  -0.0084   0.9443   0.3147
  -2.750  -0.2764   0.00838   0.00290  -0.0092   0.9394   0.3781
  -2.500  -0.2531   0.00782   0.00268  -0.0083   0.9318   0.4610
  -2.250  -0.2261   0.00719   0.00248  -0.0082   0.9269   0.5646
  -2.000  -0.2063   0.00685   0.00239  -0.0063   0.9173   0.6293
  -1.750  -0.1758   0.00659   0.00227  -0.0067   0.9112   0.6784
  -1.500  -0.1532   0.00644   0.00224  -0.0053   0.9005   0.7158
  -1.250  -0.1255   0.00633   0.00220  -0.0049   0.8916   0.7492
  -1.000  -0.0986   0.00626   0.00218  -0.0044   0.8825   0.7725
  -0.750  -0.0719   0.00623   0.00217  -0.0038   0.8741   0.7914
  -0.500  -0.0440   0.00621   0.00216  -0.0036   0.8655   0.8075
  -0.250  -0.0181   0.00620   0.00217  -0.0029   0.8554   0.8217
   0.000   0.0097   0.00620   0.00216  -0.0025   0.8452   0.8350
   0.250   0.0358   0.00621   0.00216  -0.0018   0.8329   0.8484
   0.500   0.0617   0.00622   0.00218  -0.0011   0.8192   0.8606
   0.750   0.0897   0.00624   0.00221  -0.0008   0.8057   0.8705
   1.000   0.1158   0.00628   0.00223  -0.0001   0.7921   0.8810
   1.250   0.1434   0.00632   0.00227   0.0003   0.7763   0.8908
   1.500   0.1721   0.00639   0.00231   0.0004   0.7549   0.9006
   1.750   0.1984   0.00650   0.00238   0.0012   0.7283   0.9125
   2.000   0.2268   0.00672   0.00248   0.0015   0.6874   0.9230
   2.250   0.2562   0.00702   0.00260   0.0015   0.6348   0.9303
   2.500   0.2834   0.00743   0.00277   0.0019   0.5733   0.9370
   2.750   0.3086   0.00789   0.00295   0.0025   0.5014   0.9434
   3.000   0.3411   0.00844   0.00318   0.0014   0.4260   0.9462
   3.250   0.3746   0.00890   0.00343   0.0001   0.3772   0.9497
   3.500   0.3992   0.00925   0.00364   0.0007   0.3446   0.9566
   3.750   0.4386   0.00962   0.00389  -0.0018   0.3145   0.9584
   4.000   0.4742   0.00992   0.00410  -0.0036   0.2870   0.9604
   4.250   0.5072   0.01022   0.00427  -0.0049   0.2528   0.9632
   4.500   0.5335   0.01059   0.00446  -0.0047   0.2090   0.9684
   4.750   0.5632   0.01106   0.00471  -0.0055   0.1641   0.9716
   5.000   0.5967   0.01152   0.00500  -0.0070   0.1309   0.9736
   5.250   0.6282   0.01204   0.00533  -0.0081   0.0941   0.9766
   5.500   0.6567   0.01253   0.00567  -0.0085   0.0718   0.9807
   5.750   0.6874   0.01292   0.00603  -0.0093   0.0654   0.9839
   6.000   0.7208   0.01339   0.00649  -0.0108   0.0601   0.9860
   6.250   0.7538   0.01375   0.00690  -0.0121   0.0572   0.9886
   6.500   0.7846   0.01421   0.00736  -0.0131   0.0541   0.9917
   6.750   0.8128   0.01502   0.00818  -0.0136   0.0507   0.9947
   7.000   0.8469   0.01530   0.00853  -0.0152   0.0489   0.9969
   7.250   0.8797   0.01568   0.00895  -0.0166   0.0464   0.9992
   7.500   0.9007   0.01610   0.00938  -0.0156   0.0445   1.0000
   7.750   0.9097   0.01681   0.01009  -0.0123   0.0427   1.0000
   8.000   0.9216   0.01732   0.01066  -0.0094   0.0414   1.0000
   8.250   0.9359   0.01760   0.01101  -0.0069   0.0401   1.0000
   8.500   0.9494   0.01796   0.01141  -0.0043   0.0388   1.0000
   8.750   0.9631   0.01830   0.01177  -0.0018   0.0372   1.0000
   9.000   0.9751   0.01879   0.01225   0.0010   0.0359   1.0000
   9.250   0.9834   0.01978   0.01328   0.0043   0.0344   1.0000
   9.500   0.9977   0.02010   0.01369   0.0068   0.0334   1.0000
   9.750   1.0111   0.02052   0.01418   0.0093   0.0322   1.0000
  10.000   1.0244   0.02089   0.01458   0.0119   0.0310   1.0000
  10.250   1.0364   0.02137   0.01507   0.0145   0.0300   1.0000
  10.500   1.0430   0.02258   0.01629   0.0178   0.0286   1.0000
  10.750   1.0546   0.02289   0.01670   0.0207   0.0278   1.0000
  11.000   1.0624   0.02340   0.01731   0.0241   0.0270   1.0000
  11.250   1.0700   0.02389   0.01786   0.0275   0.0261   1.0000
  11.500   1.0781   0.02447   0.01848   0.0306   0.0254   1.0000
  11.750   1.0867   0.02506   0.01910   0.0334   0.0247   1.0000
  12.000   1.0928   0.02605   0.02013   0.0363   0.0240   1.0000
  12.250   1.0973   0.02740   0.02159   0.0392   0.0233   1.0000
  12.500   1.1052   0.02823   0.02256   0.0416   0.0227   1.0000
  12.750   1.1117   0.02930   0.02374   0.0439   0.0221   1.0000
  13.000   1.1186   0.03027   0.02480   0.0460   0.0214   1.0000
  13.250   1.1264   0.03115   0.02574   0.0477   0.0208   1.0000
  13.500   1.1324   0.03233   0.02697   0.0494   0.0203   1.0000
  13.750   1.1361   0.03380   0.02851   0.0510   0.0200   1.0000
  14.000   1.1348   0.03593   0.03073   0.0526   0.0195   1.0000
  14.250   1.1305   0.03846   0.03342   0.0541   0.0192   1.0000
  14.500   1.1284   0.04081   0.03595   0.0550   0.0190   1.0000
  14.750   1.1259   0.04331   0.03861   0.0554   0.0186   1.0000
  15.000   1.1203   0.04638   0.04184   0.0555   0.0185   1.0000
  15.250   1.1158   0.04946   0.04508   0.0550   0.0180   1.0000
  15.500   1.1054   0.05358   0.04936   0.0539   0.0179   1.0000
  15.750   1.0957   0.05788   0.05382   0.0522   0.0177   1.0000
  16.000   1.0838   0.06282   0.05892   0.0498   0.0175   1.0000
  16.250   1.0695   0.06850   0.06476   0.0467   0.0174   1.0000
  16.500   1.0487   0.07562   0.07206   0.0427   0.0174   1.0000
  16.750   1.0302   0.08275   0.07934   0.0384   0.0173   1.0000
  17.000   0.9966   0.09288   0.08968   0.0324   0.0174   1.0000
  17.250   0.9338   0.10954   0.10665   0.0225   0.0179   1.0000
  17.500   0.6707   0.18978   0.18715  -0.0136   0.0243   1.0000
  17.750   0.6805   0.19185   0.18922  -0.0140   0.0240   1.0000
<< Back to N-14 (n14-il)

Polar data table (+)

Polar graphs


<< Back to N-14 (n14-il)