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CLARK-Y 11.7% smoothed (clarkysm-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: CLARK-Y 11.7% smoothed (clarkysm-il)
Reynolds number: 100,000
Max Cl/Cd: 53.5 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarkysm-il-100000-n5.txt
Download as CSV file: xf-clarkysm-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK-Y 11.7% smoothed                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3773   0.09299   0.08788  -0.0445   1.0000   0.0380
  -9.250  -0.3873   0.08929   0.08427  -0.0447   1.0000   0.0378
  -9.000  -0.4007   0.08564   0.08070  -0.0445   1.0000   0.0376
  -8.750  -0.4185   0.08210   0.07727  -0.0439   1.0000   0.0374
  -8.500  -0.4426   0.07881   0.07409  -0.0427   1.0000   0.0372
  -8.250  -0.4739   0.07585   0.07125  -0.0408   1.0000   0.0367
  -8.000  -0.4866   0.06384   0.05912  -0.0527   0.9909   0.0363
  -7.750  -0.4970   0.05091   0.04563  -0.0622   0.9790   0.0361
  -7.500  -0.4889   0.04394   0.03807  -0.0660   0.9711   0.0369
  -7.250  -0.4789   0.03912   0.03263  -0.0668   0.9623   0.0385
  -7.000  -0.4593   0.03447   0.02711  -0.0682   0.9570   0.0408
  -6.750  -0.4386   0.03313   0.02568  -0.0679   0.9496   0.0420
  -6.500  -0.4109   0.03124   0.02348  -0.0688   0.9447   0.0438
  -6.250  -0.3855   0.02939   0.02121  -0.0691   0.9393   0.0465
  -6.000  -0.3607   0.02783   0.01932  -0.0690   0.9328   0.0492
  -5.750  -0.3287   0.02680   0.01818  -0.0703   0.9288   0.0520
  -5.500  -0.3027   0.02566   0.01677  -0.0701   0.9226   0.0554
  -5.250  -0.2744   0.02465   0.01562  -0.0704   0.9169   0.0594
  -5.000  -0.2404   0.02377   0.01463  -0.0717   0.9132   0.0639
  -4.750  -0.2141   0.02296   0.01363  -0.0714   0.9067   0.0689
  -4.500  -0.1847   0.02226   0.01294  -0.0719   0.9011   0.0741
  -4.250  -0.1493   0.02149   0.01203  -0.0733   0.8976   0.0815
  -4.000  -0.1242   0.02095   0.01150  -0.0728   0.8904   0.0879
  -3.750  -0.0934   0.02033   0.01083  -0.0734   0.8848   0.0964
  -3.500  -0.0580   0.01975   0.01018  -0.0747   0.8812   0.1071
  -3.250  -0.0358   0.01932   0.00982  -0.0737   0.8726   0.1169
  -3.000  -0.0038   0.01878   0.00930  -0.0744   0.8675   0.1313
  -2.750   0.0251   0.01834   0.00889  -0.0745   0.8613   0.1494
  -2.500   0.0517   0.01792   0.00858  -0.0742   0.8539   0.1740
  -2.250   0.0861   0.01740   0.00818  -0.0753   0.8495   0.2158
  -2.000   0.1079   0.01709   0.00805  -0.0741   0.8401   0.2631
  -1.750   0.1405   0.01657   0.00775  -0.0749   0.8347   0.3311
  -1.500   0.1643   0.01617   0.00764  -0.0740   0.8258   0.4087
  -1.250   0.1946   0.01548   0.00744  -0.0742   0.8196   0.5433
  -1.000   0.2233   0.01482   0.00749  -0.0734   0.8117   0.7454
  -0.750   0.3354   0.01447   0.00732  -0.0892   0.8091   0.9584
  -0.500   0.4064   0.01426   0.00691  -0.0976   0.8020   1.0000
  -0.250   0.4275   0.01424   0.00675  -0.0961   0.7889   1.0000
   0.000   0.4501   0.01422   0.00660  -0.0949   0.7761   1.0000
   0.250   0.4740   0.01420   0.00645  -0.0939   0.7641   1.0000
   0.500   0.4998   0.01417   0.00629  -0.0933   0.7531   1.0000
   0.750   0.5224   0.01420   0.00623  -0.0920   0.7407   1.0000
   1.000   0.5446   0.01426   0.00621  -0.0907   0.7281   1.0000
   1.250   0.5678   0.01432   0.00617  -0.0896   0.7158   1.0000
   1.500   0.5918   0.01437   0.00614  -0.0886   0.7035   1.0000
   1.750   0.6162   0.01443   0.00609  -0.0877   0.6910   1.0000
   2.000   0.6384   0.01453   0.00613  -0.0864   0.6774   1.0000
   2.250   0.6606   0.01465   0.00619  -0.0851   0.6634   1.0000
   2.500   0.6830   0.01477   0.00624  -0.0838   0.6492   1.0000
   2.750   0.7054   0.01490   0.00631  -0.0826   0.6346   1.0000
   3.000   0.7276   0.01505   0.00639  -0.0813   0.6195   1.0000
   3.250   0.7496   0.01521   0.00650  -0.0799   0.6041   1.0000
   3.500   0.7714   0.01539   0.00662  -0.0786   0.5884   1.0000
   3.750   0.7930   0.01558   0.00675  -0.0772   0.5722   1.0000
   4.000   0.8143   0.01580   0.00692  -0.0758   0.5555   1.0000
   4.250   0.8355   0.01604   0.00709  -0.0743   0.5389   1.0000
   4.500   0.8565   0.01630   0.00729  -0.0729   0.5225   1.0000
   4.750   0.8772   0.01658   0.00752  -0.0714   0.5061   1.0000
   5.000   0.8977   0.01688   0.00778  -0.0699   0.4898   1.0000
   5.250   0.9180   0.01721   0.00805  -0.0685   0.4741   1.0000
   5.500   0.9384   0.01755   0.00836  -0.0670   0.4593   1.0000
   5.750   0.9587   0.01792   0.00872  -0.0656   0.4454   1.0000
   6.000   0.9790   0.01830   0.00908  -0.0642   0.4320   1.0000
   6.250   0.9990   0.01870   0.00945  -0.0628   0.4191   1.0000
   6.500   1.0181   0.01912   0.00983  -0.0612   0.4053   1.0000
   6.750   1.0359   0.01955   0.01024  -0.0594   0.3902   1.0000
   7.000   1.0524   0.01999   0.01064  -0.0574   0.3743   1.0000
   7.250   1.0683   0.02045   0.01106  -0.0554   0.3585   1.0000
   7.500   1.0842   0.02092   0.01150  -0.0533   0.3441   1.0000
   7.750   1.0998   0.02140   0.01198  -0.0513   0.3309   1.0000
   8.000   1.1160   0.02188   0.01251  -0.0494   0.3189   1.0000
   8.250   1.1316   0.02238   0.01306  -0.0474   0.3074   1.0000
   8.500   1.1457   0.02289   0.01360  -0.0452   0.2960   1.0000
   8.750   1.1579   0.02344   0.01417  -0.0427   0.2848   1.0000
   9.000   1.1697   0.02400   0.01479  -0.0402   0.2721   1.0000
   9.250   1.1806   0.02460   0.01546  -0.0377   0.2587   1.0000
   9.500   1.1905   0.02526   0.01618  -0.0351   0.2441   1.0000
   9.750   1.1991   0.02601   0.01698  -0.0324   0.2279   1.0000
  10.000   1.2062   0.02688   0.01785  -0.0298   0.2097   1.0000
  10.250   1.2123   0.02787   0.01885  -0.0271   0.1872   1.0000
  10.500   1.2152   0.02912   0.02001  -0.0244   0.1655   1.0000
  10.750   1.2174   0.03054   0.02135  -0.0218   0.1473   1.0000
  11.000   1.2190   0.03211   0.02287  -0.0193   0.1340   1.0000
  11.250   1.2202   0.03380   0.02454  -0.0171   0.1244   1.0000
  11.500   1.2214   0.03557   0.02631  -0.0150   0.1168   1.0000
  11.750   1.2232   0.03737   0.02816  -0.0132   0.1109   1.0000
  12.000   1.2250   0.03926   0.03011  -0.0115   0.1056   1.0000
  12.250   1.2240   0.04142   0.03227  -0.0100   0.1017   1.0000
  12.500   1.2278   0.04332   0.03429  -0.0087   0.0976   1.0000
  12.750   1.2302   0.04537   0.03644  -0.0076   0.0938   1.0000
  13.000   1.2306   0.04764   0.03876  -0.0065   0.0905   1.0000
  13.250   1.2323   0.04988   0.04104  -0.0056   0.0874   1.0000
  13.500   1.2364   0.05199   0.04331  -0.0048   0.0844   1.0000
  13.750   1.2393   0.05423   0.04567  -0.0042   0.0814   1.0000
  14.000   1.2409   0.05664   0.04813  -0.0036   0.0786   1.0000
  14.250   1.2445   0.05889   0.05037  -0.0030   0.0761   1.0000
  14.500   1.2470   0.06140   0.05310  -0.0027   0.0735   1.0000
  14.750   1.2490   0.06401   0.05587  -0.0025   0.0709   1.0000
  15.000   1.2501   0.06671   0.05867  -0.0025   0.0686   1.0000
  15.250   1.2517   0.06936   0.06135  -0.0025   0.0663   1.0000
  15.500   1.2537   0.07212   0.06421  -0.0025   0.0642   1.0000
  15.750   1.2509   0.07562   0.06796  -0.0030   0.0621   1.0000
  16.000   1.2480   0.07917   0.07168  -0.0037   0.0599   1.0000
  16.250   1.2461   0.08261   0.07523  -0.0045   0.0581   1.0000
  16.500   1.2457   0.08582   0.07848  -0.0052   0.0563   1.0000
  16.750   1.2449   0.08919   0.08193  -0.0059   0.0546   1.0000
  17.000   1.2347   0.09429   0.08731  -0.0078   0.0531   1.0000
  17.250   1.2254   0.09937   0.09264  -0.0098   0.0517   1.0000
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