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NACA/LANGLEY SYMMETRICAL (n0011sc-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA/LANGLEY SYMMETRICAL (n0011sc-il)
Reynolds number: 200,000
Max Cl/Cd: 39.19 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n0011sc-il-200000-n5.txt
Download as CSV file: xf-n0011sc-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA/LANGLEY SYMMETRICAL                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.8375   0.07160   0.06689  -0.0550   1.0000   0.0261
 -13.250  -0.8984   0.06026   0.05517  -0.0605   1.0000   0.0258
 -13.000  -0.9259   0.05550   0.05019  -0.0602   1.0000   0.0258
 -12.750  -0.9482   0.05194   0.04642  -0.0582   1.0000   0.0260
 -12.500  -0.9709   0.04865   0.04290  -0.0548   1.0000   0.0261
 -12.250  -0.9881   0.04614   0.04018  -0.0508   1.0000   0.0262
 -12.000  -1.0028   0.04398   0.03780  -0.0462   1.0000   0.0264
 -11.750  -1.0167   0.04201   0.03561  -0.0410   1.0000   0.0266
 -11.500  -1.0283   0.04034   0.03372  -0.0357   1.0000   0.0268
 -11.250  -1.0388   0.03881   0.03198  -0.0300   1.0000   0.0270
 -11.000  -1.0473   0.03734   0.03028  -0.0243   1.0000   0.0272
 -10.750  -1.0501   0.03577   0.02845  -0.0196   1.0000   0.0275
 -10.500  -1.0494   0.03424   0.02666  -0.0153   1.0000   0.0278
 -10.250  -1.0448   0.03289   0.02509  -0.0116   1.0000   0.0281
 -10.000  -1.0363   0.03182   0.02396  -0.0086   1.0000   0.0284
  -9.750  -1.0271   0.03090   0.02297  -0.0056   1.0000   0.0288
  -9.500  -1.0169   0.02995   0.02194  -0.0027   1.0000   0.0291
  -9.250  -1.0061   0.02908   0.02097   0.0002   1.0000   0.0296
  -9.000  -0.9943   0.02817   0.01995   0.0029   1.0000   0.0301
  -8.750  -0.9817   0.02733   0.01899   0.0055   1.0000   0.0308
  -8.500  -0.9682   0.02650   0.01801   0.0081   1.0000   0.0317
  -8.250  -0.9539   0.02571   0.01704   0.0105   1.0000   0.0325
  -8.000  -0.9399   0.02492   0.01623   0.0129   1.0000   0.0332
  -7.750  -0.9254   0.02429   0.01559   0.0152   1.0000   0.0339
  -7.500  -0.9103   0.02366   0.01492   0.0175   1.0000   0.0346
  -7.250  -0.8949   0.02301   0.01421   0.0198   1.0000   0.0356
  -7.000  -0.8769   0.02238   0.01348   0.0216   0.9997   0.0367
  -6.750  -0.8516   0.02173   0.01275   0.0218   0.9981   0.0379
  -6.500  -0.8260   0.02118   0.01221   0.0218   0.9961   0.0393
  -6.250  -0.7988   0.02074   0.01174   0.0216   0.9943   0.0414
  -6.000  -0.7740   0.02026   0.01118   0.0221   0.9923   0.0434
  -5.750  -0.7496   0.01974   0.01070   0.0225   0.9900   0.0455
  -5.500  -0.7232   0.01933   0.01026   0.0225   0.9877   0.0480
  -5.250  -0.6959   0.01894   0.00985   0.0224   0.9857   0.0512
  -5.000  -0.6691   0.01858   0.00951   0.0223   0.9839   0.0550
  -4.750  -0.6457   0.01819   0.00910   0.0231   0.9808   0.0590
  -4.500  -0.6200   0.01786   0.00879   0.0233   0.9780   0.0644
  -4.250  -0.5926   0.01752   0.00850   0.0232   0.9757   0.0710
  -4.000  -0.5633   0.01724   0.00823   0.0227   0.9738   0.0792
  -3.750  -0.5402   0.01692   0.00797   0.0236   0.9704   0.0896
  -3.500  -0.5157   0.01660   0.00772   0.0241   0.9669   0.1032
  -3.250  -0.4885   0.01629   0.00752   0.0241   0.9642   0.1231
  -3.000  -0.4592   0.01597   0.00735   0.0235   0.9619   0.1497
  -2.750  -0.4356   0.01561   0.00717   0.0242   0.9585   0.1855
  -2.500  -0.4145   0.01521   0.00699   0.0255   0.9539   0.2319
  -2.250  -0.3902   0.01470   0.00682   0.0259   0.9505   0.3022
  -2.000  -0.3667   0.01402   0.00665   0.0265   0.9477   0.4105
  -1.750  -0.3609   0.01325   0.00647   0.0312   0.9404   0.5343
  -1.500  -0.3393   0.01244   0.00652   0.0329   0.9371   0.7111
  -1.250  -0.2128   0.01316   0.00777   0.0126   0.9502   0.8573
  -1.000  -0.1685   0.01354   0.00815   0.0096   0.9490   0.8816
  -0.750  -0.1284   0.01383   0.00842   0.0075   0.9473   0.8977
  -0.500  -0.0978   0.01411   0.00869   0.0074   0.9420   0.9101
  -0.250  -0.0570   0.01448   0.00906   0.0052   0.9389   0.9226
   0.000  -0.0003   0.01480   0.00939   0.0000   0.9352   0.9352
   0.250   0.0573   0.01447   0.00905  -0.0053   0.9225   0.9388
   0.500   0.0979   0.01411   0.00869  -0.0074   0.9099   0.9419
   0.750   0.1288   0.01384   0.00843  -0.0076   0.8984   0.9473
   1.000   0.1684   0.01354   0.00814  -0.0096   0.8814   0.9490
   1.250   0.2125   0.01317   0.00778  -0.0125   0.8577   0.9503
   1.500   0.3393   0.01243   0.00653  -0.0329   0.7118   0.9371
   1.750   0.3609   0.01325   0.00647  -0.0312   0.5345   0.9404
   2.000   0.3669   0.01401   0.00665  -0.0266   0.4114   0.9477
   2.250   0.3901   0.01470   0.00681  -0.0259   0.3024   0.9505
   2.500   0.4146   0.01520   0.00698  -0.0255   0.2328   0.9539
   2.750   0.4356   0.01561   0.00717  -0.0242   0.1864   0.9585
   3.000   0.4593   0.01597   0.00734  -0.0236   0.1506   0.9619
   3.250   0.4885   0.01629   0.00751  -0.0241   0.1221   0.9642
   3.500   0.5158   0.01660   0.00772  -0.0242   0.1032   0.9670
   3.750   0.5402   0.01692   0.00796  -0.0236   0.0895   0.9704
   4.000   0.5633   0.01723   0.00823  -0.0228   0.0793   0.9738
   4.250   0.5926   0.01752   0.00849  -0.0233   0.0707   0.9757
   4.500   0.6201   0.01785   0.00878  -0.0234   0.0642   0.9781
   4.750   0.6456   0.01820   0.00910  -0.0231   0.0588   0.9808
   5.000   0.6691   0.01858   0.00950  -0.0223   0.0549   0.9839
   5.250   0.6961   0.01893   0.00983  -0.0224   0.0509   0.9858
   5.500   0.7232   0.01933   0.01026  -0.0225   0.0480   0.9878
   5.750   0.7497   0.01974   0.01070  -0.0225   0.0454   0.9900
   6.000   0.7741   0.02026   0.01118  -0.0221   0.0434   0.9923
   6.250   0.7989   0.02073   0.01173  -0.0217   0.0412   0.9943
   6.500   0.8262   0.02115   0.01219  -0.0219   0.0391   0.9961
   6.750   0.8516   0.02174   0.01275  -0.0218   0.0378   0.9981
   7.000   0.8770   0.02238   0.01349  -0.0216   0.0365   0.9997
   7.250   0.8948   0.02301   0.01421  -0.0198   0.0354   1.0000
   7.500   0.9102   0.02365   0.01490  -0.0175   0.0345   1.0000
   7.750   0.9252   0.02428   0.01557  -0.0152   0.0338   1.0000
   8.000   0.9396   0.02492   0.01622  -0.0129   0.0330   1.0000
   8.250   0.9538   0.02569   0.01704  -0.0105   0.0323   1.0000
   8.500   0.9681   0.02653   0.01804  -0.0081   0.0316   1.0000
   8.750   0.9815   0.02735   0.01901  -0.0055   0.0306   1.0000
   9.000   0.9942   0.02819   0.01997  -0.0029   0.0301   1.0000
   9.250   1.0060   0.02911   0.02100  -0.0002   0.0296   1.0000
   9.500   1.0170   0.02997   0.02196   0.0027   0.0291   1.0000
   9.750   1.0271   0.03088   0.02295   0.0056   0.0287   1.0000
  10.000   1.0363   0.03183   0.02396   0.0086   0.0284   1.0000
  10.250   1.0446   0.03296   0.02517   0.0116   0.0281   1.0000
  10.500   1.0494   0.03429   0.02671   0.0153   0.0278   1.0000
  10.750   1.0496   0.03584   0.02854   0.0197   0.0275   1.0000
  11.000   1.0471   0.03739   0.03033   0.0243   0.0272   1.0000
  11.250   1.0391   0.03885   0.03202   0.0299   0.0271   1.0000
  11.500   1.0281   0.04039   0.03378   0.0357   0.0268   1.0000
  11.750   1.0160   0.04210   0.03570   0.0411   0.0266   1.0000
  12.000   1.0027   0.04405   0.03787   0.0462   0.0264   1.0000
  12.250   0.9870   0.04630   0.04035   0.0508   0.0263   1.0000
  12.500   0.9708   0.04867   0.04292   0.0548   0.0260   1.0000
  12.750   0.9502   0.05176   0.04624   0.0580   0.0260   1.0000
  13.000   0.9295   0.05514   0.04981   0.0601   0.0257   1.0000
  13.250   0.8903   0.06138   0.05634   0.0601   0.0259   1.0000
  13.500   0.8395   0.07137   0.06665   0.0551   0.0262   1.0000
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