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Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=1


Details Polar file
Airfoil: Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn)
Reynolds number: 1,000,000
Max Cl/Cd: 62.15 at α=6°
Description: Mach=0 Ncrit=1
Source: Xfoil prediction
Download polar: xf-cp-100-050-gn-1000000-n1.txt
Download as CSV file: xf-cp-100-050-gn-1000000-n1.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 =     1.000 e 6     Ncrit =   1.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.0783   0.09338   0.09030  -0.1608   0.8469   0.0169
  -9.500   0.0890   0.09140   0.08831  -0.1619   0.8427   0.0170
  -9.250   0.0969   0.08886   0.08575  -0.1631   0.8370   0.0174
  -9.000   0.1077   0.08708   0.08394  -0.1639   0.8310   0.0175
  -8.750   0.1175   0.08508   0.08192  -0.1648   0.8265   0.0177
  -8.500   0.1275   0.08312   0.07995  -0.1657   0.8215   0.0179
  -8.250   0.1370   0.08121   0.07802  -0.1664   0.8154   0.0183
  -8.000   0.1457   0.07924   0.07602  -0.1670   0.8098   0.0185
  -7.750   0.1536   0.07708   0.07384  -0.1677   0.8044   0.0193
  -7.500   0.1610   0.07500   0.07174  -0.1683   0.7982   0.0197
  -7.250   0.1712   0.07351   0.07024  -0.1685   0.7930   0.0197
  -7.000   0.1786   0.07146   0.06818  -0.1690   0.7881   0.0199
  -6.750   0.1879   0.06989   0.06661  -0.1692   0.7825   0.0203
  -6.500   0.1953   0.06825   0.06495  -0.1691   0.7768   0.0205
  -6.250   0.2018   0.06655   0.06324  -0.1690   0.7718   0.0208
  -6.000   0.2070   0.06494   0.06163  -0.1686   0.7658   0.0211
  -5.750   0.2084   0.06342   0.06010  -0.1674   0.7588   0.0217
  -5.500   0.2124   0.06143   0.05810  -0.1676   0.7539   0.0223
  -5.250   0.2214   0.05962   0.05629  -0.1682   0.7486   0.0225
  -5.000   0.2313   0.05795   0.05460  -0.1687   0.7423   0.0227
  -4.750   0.2434   0.05635   0.05299  -0.1695   0.7377   0.0228
  -4.500   0.2566   0.05471   0.05134  -0.1704   0.7325   0.0232
  -4.250   0.2699   0.05287   0.04949  -0.1715   0.7273   0.0236
  -4.000   0.2838   0.05107   0.04766  -0.1726   0.7218   0.0242
  -3.750   0.2995   0.04889   0.04546  -0.1744   0.7173   0.0248
  -3.500   0.3164   0.04692   0.04346  -0.1760   0.7113   0.0251
  -3.250   0.3309   0.04508   0.04154  -0.1769   0.6967   0.0254
  -3.000   0.3436   0.04380   0.04016  -0.1765   0.6735   0.0256
  -2.750   0.3542   0.04266   0.03886  -0.1755   0.6427   0.0259
  -2.500   0.3682   0.04134   0.03742  -0.1752   0.6187   0.0262
  -2.250   0.3393   0.04231   0.03768  -0.1647   0.4548   0.0263
  -2.000   0.3235   0.04250   0.03736  -0.1574   0.3189   0.0265
  -1.750   0.3084   0.04277   0.03701  -0.1503   0.0836   0.0267
  -1.500   0.3278   0.04100   0.03511  -0.1511   0.0288   0.0275
  -1.250   0.3523   0.03887   0.03290  -0.1530   0.0273   0.0280
  -1.000   0.3778   0.03685   0.03081  -0.1547   0.0266   0.0284
  -0.750   0.4015   0.03553   0.02943  -0.1555   0.0252   0.0286
  -0.500   0.4266   0.03406   0.02790  -0.1565   0.0250   0.0290
  -0.250   0.4522   0.03259   0.02636  -0.1574   0.0246   0.0296
   0.500   0.5358   0.02719   0.02064  -0.1614   0.0238   0.0316
   0.750   0.5612   0.02608   0.01945  -0.1616   0.0237   0.0319
   1.000   0.5874   0.02484   0.01811  -0.1619   0.0232   0.0325
   1.250   0.6159   0.02306   0.01616  -0.1627   0.0229   0.0337
   1.500   0.6573   0.01426   0.00595  -0.1671   0.0230   0.0386
   1.750   0.6795   0.01426   0.00589  -0.1658   0.0228   0.0388
   2.000   0.7015   0.01424   0.00581  -0.1645   0.0226   0.0390
   2.250   0.7231   0.01425   0.00577  -0.1631   0.0224   0.0393
   2.500   0.7445   0.01427   0.00574  -0.1616   0.0222   0.0396
   2.750   0.7657   0.01431   0.00574  -0.1601   0.0219   0.0400
   3.000   0.7870   0.01438   0.00577  -0.1586   0.0218   0.0405
   3.250   0.8082   0.01445   0.00580  -0.1571   0.0217   0.0408
   3.500   0.8292   0.01455   0.00589  -0.1556   0.0217   0.0410
   3.750   0.8496   0.01468   0.00599  -0.1539   0.0214   0.0412
   4.000   0.8699   0.01482   0.00611  -0.1523   0.0214   0.0414
   4.250   0.8902   0.01499   0.00626  -0.1506   0.0213   0.0415
   4.500   0.9106   0.01516   0.00642  -0.1490   0.0212   0.0415
   4.750   0.9307   0.01535   0.00661  -0.1474   0.0211   0.0416
   5.000   0.9502   0.01556   0.00681  -0.1456   0.0210   0.0418
   5.250   0.9696   0.01579   0.00704  -0.1438   0.0210   0.0419
   5.500   0.9890   0.01603   0.00728  -0.1421   0.0209   0.0419
   5.750   1.0086   0.01628   0.00753  -0.1404   0.0207   0.0422
   6.000   1.0279   0.01654   0.00780  -0.1386   0.0207   0.0423
   6.250   1.0465   0.01684   0.00812  -0.1368   0.0207   0.0426
   6.500   1.0649   0.01715   0.00843  -0.1349   0.0206   0.0428
   6.750   1.0835   0.01746   0.00875  -0.1331   0.0205   0.0429
   7.000   1.1020   0.01779   0.00910  -0.1313   0.0205   0.0431
   7.250   1.1199   0.01815   0.00947  -0.1294   0.0205   0.0433
   7.500   1.1376   0.01852   0.00986  -0.1275   0.0204   0.0434
   7.750   1.1552   0.01891   0.01026  -0.1256   0.0203   0.0435
   8.000   1.1727   0.01932   0.01069  -0.1237   0.0203   0.0439
   8.250   1.1900   0.01975   0.01113  -0.1218   0.0202   0.0441
   8.500   1.2065   0.02021   0.01162  -0.1198   0.0202   0.0444
   8.750   1.2233   0.02068   0.01211  -0.1179   0.0201   0.0444
   9.000   1.2399   0.02117   0.01263  -0.1160   0.0200   0.0448
   9.250   1.2561   0.02169   0.01317  -0.1140   0.0200   0.0449
   9.500   1.2719   0.02224   0.01375  -0.1121   0.0199   0.0450
   9.750   1.2880   0.02279   0.01432  -0.1102   0.0197   0.0451
  10.000   1.3039   0.02336   0.01492  -0.1083   0.0196   0.0454
  10.250   1.3195   0.02396   0.01555  -0.1063   0.0194   0.0455
  10.500   1.3342   0.02462   0.01624  -0.1043   0.0194   0.0458
  10.750   1.3496   0.02525   0.01691  -0.1025   0.0191   0.0464
  11.000   1.3642   0.02595   0.01765  -0.1005   0.0191   0.0472
  11.250   1.3785   0.02668   0.01841  -0.0986   0.0189   0.0478
  11.500   1.3931   0.02741   0.01917  -0.0967   0.0187   0.0482
  11.750   1.4075   0.02816   0.01996  -0.0948   0.0187   0.0484
  12.000   1.4211   0.02897   0.02081  -0.0929   0.0186   0.0488
  12.250   1.4349   0.02980   0.02167  -0.0911   0.0184   0.0496
  12.750   1.4620   0.03152   0.02348  -0.0875   0.0182   0.0527
  13.000   1.4752   0.03242   0.02445  -0.0857   0.0181   0.0738
  13.250   1.4855   0.03281   0.02568  -0.0834   0.0181   0.7711
  13.750   1.5581   0.03529   0.02861  -0.0901   0.0178   1.0000
  14.000   1.5701   0.03635   0.02969  -0.0883   0.0177   1.0000
  14.250   1.5820   0.03743   0.03080  -0.0865   0.0176   1.0000
  14.500   1.5936   0.03854   0.03195  -0.0848   0.0176   1.0000
  14.750   1.6040   0.03977   0.03322  -0.0829   0.0175   1.0000
  15.000   1.6149   0.04095   0.03443  -0.0812   0.0175   1.0000
  15.250   1.6244   0.04227   0.03580  -0.0794   0.0173   1.0000
  15.500   1.6340   0.04360   0.03718  -0.0776   0.0173   1.0000
  15.750   1.6442   0.04489   0.03851  -0.0759   0.0173   1.0000
  16.000   1.6533   0.04630   0.03997  -0.0742   0.0171   1.0000
  16.250   1.6620   0.04775   0.04147  -0.0726   0.0170   1.0000
  16.500   1.6716   0.04913   0.04289  -0.0710   0.0169   1.0000
  16.750   1.6793   0.05070   0.04452  -0.0694   0.0168   1.0000
  17.000   1.6876   0.05224   0.04612  -0.0679   0.0168   1.0000
  17.250   1.6956   0.05383   0.04776  -0.0664   0.0167   1.0000
  17.500   1.7030   0.05550   0.04949  -0.0649   0.0166   1.0000
  17.750   1.7108   0.05715   0.05119  -0.0635   0.0165   1.0000
  18.000   1.7177   0.05891   0.05302  -0.0622   0.0165   1.0000
  18.250   1.7246   0.06068   0.05485  -0.0609   0.0163   1.0000
  18.500   1.7316   0.06246   0.05668  -0.0597   0.0163   1.0000
  18.750   1.7376   0.06439   0.05868  -0.0585   0.0162   1.0000
  19.000   1.7435   0.06635   0.06071  -0.0574   0.0161   1.0000
  19.250   1.7487   0.06841   0.06284  -0.0563   0.0161   1.0000
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