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Supermarine 371-II (tip) (supermarine371ii-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Supermarine 371-II (tip) (supermarine371ii-il)
Reynolds number: 100,000
Max Cl/Cd: 37.54 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-supermarine371ii-il-100000-n5.txt
Download as CSV file: xf-supermarine371ii-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Supermarine 371-II (tip)                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4395   0.08901   0.08453  -0.0219   1.0000   0.0173
  -9.000  -0.5281   0.09404   0.08925  -0.0202   1.0000   0.0182
  -8.750  -0.5288   0.08954   0.08482  -0.0227   1.0000   0.0175
  -8.500  -0.5297   0.08519   0.08052  -0.0256   1.0000   0.0166
  -8.250  -0.5340   0.08045   0.07583  -0.0295   1.0000   0.0163
  -8.000  -0.5400   0.07636   0.07177  -0.0319   1.0000   0.0158
  -7.750  -0.5443   0.07224   0.06763  -0.0336   1.0000   0.0153
  -7.500  -0.5457   0.06808   0.06341  -0.0348   1.0000   0.0147
  -7.250  -0.5455   0.06388   0.05913  -0.0355   1.0000   0.0141
  -7.000  -0.5439   0.05977   0.05490  -0.0355   1.0000   0.0137
  -6.750  -0.5413   0.05597   0.05096  -0.0347   1.0000   0.0131
  -6.500  -0.5414   0.05254   0.04735  -0.0324   1.0000   0.0124
  -6.250  -0.5402   0.04927   0.04388  -0.0300   0.9977   0.0122
  -6.000  -0.5167   0.04425   0.03842  -0.0316   0.9875   0.0118
  -5.750  -0.4925   0.04015   0.03389  -0.0330   0.9794   0.0120
  -5.500  -0.4669   0.03788   0.03118  -0.0348   0.9728   0.0161
  -5.250  -0.4376   0.03474   0.02746  -0.0353   0.9664   0.0196
  -5.000  -0.4102   0.03142   0.02357  -0.0354   0.9601   0.0201
  -4.750  -0.3813   0.02844   0.02005  -0.0356   0.9548   0.0203
  -4.500  -0.3507   0.02582   0.01689  -0.0357   0.9505   0.0209
  -4.250  -0.3225   0.02320   0.01391  -0.0355   0.9454   0.0218
  -4.000  -0.2931   0.02099   0.01156  -0.0359   0.9415   0.0245
  -3.750  -0.2631   0.02002   0.01036  -0.0363   0.9376   0.0334
  -3.500  -0.2392   0.01854   0.00886  -0.0357   0.9319   0.0363
  -3.250  -0.2128   0.01759   0.00777  -0.0355   0.9275   0.0400
  -3.000  -0.1885   0.01685   0.00686  -0.0349   0.9223   0.0465
  -2.750  -0.1643   0.01617   0.00616  -0.0343   0.9174   0.0693
  -2.500  -0.1621   0.01328   0.00613  -0.0299   0.9127   0.6917
  -2.250  -0.1503   0.01368   0.00663  -0.0242   0.9074   0.8244
  -2.000  -0.1153   0.01455   0.00744  -0.0213   0.9073   0.9045
  -1.750  -0.0800   0.01459   0.00724  -0.0228   0.9045   0.9158
  -1.500  -0.0471   0.01452   0.00698  -0.0242   0.9015   0.9202
  -1.250  -0.0193   0.01448   0.00679  -0.0247   0.8978   0.9260
  -1.000   0.0132   0.01446   0.00665  -0.0261   0.8943   0.9296
  -0.750   0.0442   0.01445   0.00650  -0.0273   0.8911   0.9343
  -0.500   0.0741   0.01444   0.00641  -0.0282   0.8883   0.9394
  -0.250   0.1090   0.01443   0.00634  -0.0301   0.8860   0.9426
   0.000   0.1387   0.01448   0.00638  -0.0311   0.8820   0.9479
   0.250   0.1691   0.01453   0.00642  -0.0323   0.8789   0.9532
   0.500   0.2042   0.01457   0.00649  -0.0343   0.8764   0.9567
   0.750   0.2375   0.01460   0.00656  -0.0360   0.8741   0.9611
   1.000   0.2697   0.01469   0.00670  -0.0375   0.8712   0.9662
   1.250   0.3030   0.01479   0.00690  -0.0394   0.8679   0.9712
   1.500   0.3351   0.01489   0.00712  -0.0409   0.8647   0.9767
   1.750   0.3697   0.01497   0.00734  -0.0428   0.8622   0.9813
   2.000   0.4032   0.01506   0.00774  -0.0445   0.8599   0.9865
   2.250   0.4357   0.01525   0.00816  -0.0463   0.8558   0.9929
   2.500   0.4677   0.01502   0.00814  -0.0466   0.8430   0.9983
   2.750   0.4803   0.01371   0.00678  -0.0397   0.7889   1.0000
   3.000   0.4888   0.01302   0.00602  -0.0339   0.7269   1.0000
   3.250   0.4825   0.01366   0.00506  -0.0257   0.3688   1.0000
   3.500   0.4793   0.01605   0.00588  -0.0214   0.0808   1.0000
   3.750   0.4940   0.01688   0.00661  -0.0191   0.0561   1.0000
   4.000   0.5105   0.01765   0.00745  -0.0171   0.0477   1.0000
   4.250   0.5270   0.01858   0.00850  -0.0151   0.0437   1.0000
   4.500   0.5449   0.01949   0.00950  -0.0134   0.0381   1.0000
   4.750   0.5634   0.02066   0.01093  -0.0119   0.0306   1.0000
   5.000   0.5842   0.02225   0.01259  -0.0105   0.0267   1.0000
   5.250   0.6082   0.02510   0.01544  -0.0096   0.0241   1.0000
   5.500   0.6338   0.02657   0.01734  -0.0085   0.0204   1.0000
   5.750   0.6546   0.02776   0.01871  -0.0078   0.0152   1.0000
   6.000   0.6762   0.03063   0.02191  -0.0067   0.0143   1.0000
   6.250   0.6947   0.03432   0.02605  -0.0053   0.0139   1.0000
   6.500   0.7107   0.03793   0.03009  -0.0035   0.0137   1.0000
   6.750   0.7248   0.04135   0.03396  -0.0018   0.0136   1.0000
   7.000   0.7359   0.04503   0.03803   0.0000   0.0137   1.0000
   7.250   0.7464   0.04844   0.04184   0.0017   0.0138   1.0000
   7.500   0.7550   0.05181   0.04553   0.0034   0.0140   1.0000
   7.750   0.7632   0.05501   0.04906   0.0052   0.0143   1.0000
   8.000   0.7692   0.05871   0.05309   0.0070   0.0149   1.0000
   8.250   0.7664   0.06367   0.05840   0.0088   0.0158   1.0000
   8.500   0.7597   0.06828   0.06324   0.0100   0.0166   1.0000
   8.750   0.7488   0.07240   0.06749   0.0110   0.0171   1.0000
   9.000   0.7353   0.07640   0.07158   0.0113   0.0175   1.0000
   9.250   0.7220   0.08094   0.07618   0.0099   0.0178   1.0000
   9.500   0.7100   0.08628   0.08155   0.0069   0.0183   1.0000
   9.750   0.7008   0.09243   0.08770   0.0026   0.0186   1.0000
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