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Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn)
Reynolds number: 500,000
Max Cl/Cd: 46.01 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cp-100-050-gn-500000-n5.txt
Download as CSV file: xf-cp-100-050-gn-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Cambered plate C=10% T=5% R=1.3                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.0302   0.11617   0.11308  -0.1254   0.9591   0.0283
 -10.250  -0.0199   0.11408   0.11100  -0.1261   0.9566   0.0268
 -10.000  -0.0116   0.11170   0.10861  -0.1270   0.9531   0.0273
  -9.500   0.0137   0.10630   0.10320  -0.1313   0.9493   0.0290
  -9.250   0.0303   0.10409   0.10099  -0.1338   0.9478   0.0310
  -9.000   0.0457   0.10097   0.09786  -0.1370   0.9466   0.0313
  -8.750   0.0626   0.09788   0.09475  -0.1406   0.9455   0.0313
  -8.500   0.0809   0.09480   0.09165  -0.1443   0.9445   0.0313
  -8.250   0.0868   0.09304   0.08990  -0.1437   0.9394   0.0299
  -7.750   0.1170   0.08711   0.08394  -0.1500   0.9337   0.0314
  -7.250   0.1579   0.08187   0.07867  -0.1571   0.9301   0.0307
  -7.000   0.1686   0.07965   0.07644  -0.1583   0.9256   0.0310
  -6.750   0.1796   0.07758   0.07437  -0.1595   0.9204   0.0320
  -6.500   0.1955   0.07477   0.07153  -0.1626   0.9167   0.0318
  -6.250   0.2174   0.07295   0.06970  -0.1654   0.9141   0.0324
  -6.000   0.2270   0.07155   0.06831  -0.1654   0.9087   0.0335
  -5.750   0.2360   0.06962   0.06638  -0.1659   0.9030   0.0339
  -5.500   0.2504   0.06739   0.06411  -0.1680   0.8987   0.0338
  -5.250   0.2564   0.06562   0.06235  -0.1678   0.8931   0.0338
  -5.000   0.2598   0.06403   0.06075  -0.1671   0.8864   0.0342
  -4.500   0.2862   0.06009   0.05678  -0.1702   0.8769   0.0353
  -4.250   0.2966   0.05884   0.05554  -0.1699   0.8714   0.0358
  -4.000   0.3131   0.05729   0.05397  -0.1713   0.8668   0.0372
  -3.750   0.3324   0.05509   0.05174  -0.1740   0.8630   0.0370
  -3.500   0.3416   0.05339   0.05005  -0.1740   0.8572   0.0368
  -3.250   0.3572   0.05150   0.04814  -0.1754   0.8520   0.0369
  -3.000   0.3779   0.04940   0.04600  -0.1779   0.8479   0.0372
  -2.750   0.4000   0.04657   0.04311  -0.1819   0.8434   0.0385
  -2.500   0.4146   0.04569   0.04226  -0.1809   0.8376   0.0389
  -2.250   0.4365   0.04438   0.04090  -0.1821   0.8307   0.0398
  -2.000   0.4575   0.04253   0.03902  -0.1837   0.8245   0.0400
  -1.750   0.4782   0.04062   0.03704  -0.1850   0.8145   0.0398
  -1.500   0.5009   0.03877   0.03513  -0.1865   0.8061   0.0399
  -1.250   0.5239   0.03704   0.03331  -0.1878   0.7950   0.0402
  -1.000   0.5473   0.03526   0.03147  -0.1890   0.7853   0.0411
  -0.750   0.5803   0.03224   0.02826  -0.1931   0.7738   0.0421
  -0.500   0.5952   0.03192   0.02792  -0.1910   0.7601   0.0425
  -0.250   0.6160   0.03064   0.02656  -0.1908   0.7450   0.0428
   0.000   0.6368   0.02943   0.02525  -0.1905   0.7294   0.0431
   0.250   0.6543   0.02822   0.02387  -0.1893   0.7065   0.0432
   0.500   0.6624   0.02741   0.02286  -0.1857   0.6714   0.0435
   0.750   0.6640   0.02684   0.02206  -0.1807   0.6329   0.0442
   1.000   0.6596   0.02645   0.02135  -0.1744   0.5755   0.0446
   1.250   0.6399   0.02700   0.02134  -0.1652   0.4648   0.0448
   1.500   0.6096   0.02882   0.02222  -0.1546   0.2465   0.0447
   1.750   0.6074   0.02934   0.02207  -0.1497   0.0527   0.0447
   2.000   0.6369   0.02771   0.02024  -0.1506   0.0448   0.0452
   2.250   0.6694   0.02562   0.01792  -0.1520   0.0422   0.0462
   2.500   0.6893   0.02553   0.01782  -0.1508   0.0396   0.0466
   2.750   0.7115   0.02518   0.01741  -0.1499   0.0383   0.0471
   3.000   0.7367   0.02435   0.01646  -0.1495   0.0373   0.0476
   3.250   0.7627   0.02328   0.01522  -0.1492   0.0367   0.0480
   3.500   0.7884   0.02209   0.01379  -0.1486   0.0361   0.0485
   3.750   0.8158   0.01995   0.01105  -0.1481   0.0353   0.0502
   4.000   0.8351   0.01995   0.01101  -0.1464   0.0349   0.0506
   4.250   0.8539   0.02000   0.01100  -0.1446   0.0343   0.0508
   4.500   0.8720   0.02012   0.01106  -0.1428   0.0337   0.0511
   4.750   0.8904   0.02025   0.01114  -0.1409   0.0334   0.0514
   5.000   0.9092   0.02032   0.01114  -0.1391   0.0330   0.0518
   5.250   0.9270   0.02052   0.01130  -0.1372   0.0328   0.0524
   5.500   0.9446   0.02076   0.01150  -0.1352   0.0325   0.0531
   5.750   0.9623   0.02098   0.01165  -0.1332   0.0322   0.0537
   6.000   0.9791   0.02128   0.01191  -0.1312   0.0320   0.0540
   6.250   0.9954   0.02164   0.01225  -0.1291   0.0318   0.0543
   6.500   1.0114   0.02206   0.01264  -0.1269   0.0315   0.0546
   6.750   1.0275   0.02250   0.01307  -0.1248   0.0312   0.0548
   7.000   1.0426   0.02296   0.01355  -0.1226   0.0310   0.0550
   7.250   1.0576   0.02348   0.01409  -0.1205   0.0308   0.0555
   7.500   1.0727   0.02404   0.01469  -0.1183   0.0306   0.0559
   7.750   1.0874   0.02465   0.01532  -0.1162   0.0304   0.0565
   8.000   1.1019   0.02529   0.01597  -0.1141   0.0300   0.0572
   8.250   1.1165   0.02593   0.01664  -0.1119   0.0299   0.0576
   8.500   1.1308   0.02663   0.01735  -0.1098   0.0296   0.0581
   8.750   1.1440   0.02743   0.01816  -0.1077   0.0293   0.0583
   9.000   1.1569   0.02833   0.01908  -0.1055   0.0290   0.0590
   9.250   1.1717   0.02911   0.01989  -0.1035   0.0288   0.0594
   9.500   1.1875   0.02984   0.02065  -0.1017   0.0287   0.0599
   9.750   1.2032   0.03057   0.02143  -0.1000   0.0286   0.0604
  10.000   1.2193   0.03133   0.02225  -0.0982   0.0284   0.0614
  10.250   1.2357   0.03210   0.02306  -0.0966   0.0282   0.0623
  10.500   1.2527   0.03289   0.02390  -0.0951   0.0280   0.0637
  10.750   1.2700   0.03366   0.02471  -0.0936   0.0278   0.0656
  11.000   1.2880   0.03445   0.02556  -0.0922   0.0276   0.0685
  11.250   1.3063   0.03525   0.02640  -0.0908   0.0274   0.0725
  11.750   1.3682   0.03640   0.02886  -0.0936   0.0268   1.0000
  12.000   1.3856   0.03726   0.02974  -0.0922   0.0266   1.0000
  12.250   1.4024   0.03814   0.03063  -0.0907   0.0263   1.0000
  12.500   1.4191   0.03905   0.03156  -0.0893   0.0261   1.0000
  12.750   1.4345   0.03999   0.03253  -0.0878   0.0258   1.0000
  13.000   1.4508   0.04096   0.03354  -0.0863   0.0257   1.0000
  13.250   1.4675   0.04197   0.03458  -0.0850   0.0255   1.0000
  13.500   1.4826   0.04302   0.03566  -0.0835   0.0253   1.0000
  13.750   1.4979   0.04411   0.03677  -0.0821   0.0252   1.0000
  14.000   1.5145   0.04525   0.03795  -0.0808   0.0250   1.0000
  14.250   1.5325   0.04649   0.03923  -0.0797   0.0249   1.0000
  14.500   1.5505   0.04795   0.04077  -0.0786   0.0247   1.0000
  14.750   1.5607   0.04945   0.04241  -0.0768   0.0245   1.0000
  15.000   1.5715   0.05109   0.04420  -0.0751   0.0244   1.0000
  15.250   1.5807   0.05296   0.04625  -0.0733   0.0242   1.0000
  15.500   1.5888   0.05509   0.04857  -0.0716   0.0240   1.0000
  15.750   1.5944   0.05741   0.05109  -0.0697   0.0238   1.0000
  16.000   1.5972   0.05988   0.05376  -0.0678   0.0234   1.0000
  16.250   1.5978   0.06257   0.05664  -0.0659   0.0232   1.0000
  16.500   1.5965   0.06527   0.05952  -0.0640   0.0229   1.0000
  16.750   1.5933   0.06824   0.06267  -0.0622   0.0228   1.0000
  17.000   1.5879   0.07151   0.06611  -0.0606   0.0226   1.0000
  17.250   1.5812   0.07492   0.06970  -0.0591   0.0225   1.0000
  17.500   1.5726   0.07860   0.07355  -0.0579   0.0223   1.0000
  17.750   1.5630   0.08244   0.07756  -0.0569   0.0222   1.0000
  18.000   1.5515   0.08666   0.08197  -0.0563   0.0221   1.0000
  18.250   1.5396   0.09102   0.08649  -0.0560   0.0220   1.0000
  18.500   1.5250   0.09594   0.09159  -0.0562   0.0219   1.0000
  18.750   1.5103   0.10100   0.09681  -0.0568   0.0219   1.0000
  19.000   1.4926   0.10680   0.10279  -0.0581   0.0218   1.0000
  19.250   1.4734   0.11310   0.10927  -0.0601   0.0217   1.0000
  19.500   1.4500   0.12051   0.11688  -0.0631   0.0217   1.0000
  19.750   1.4245   0.12881   0.12537  -0.0672   0.0216   1.0000
  20.000   1.3766   0.14281   0.13968  -0.0760   0.0216   1.0000
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