Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn)
Reynolds number: 500,000
Max Cl/Cd: 42.57 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cp-120-050-gn-500000-n5.txt
Download as CSV file: xf-cp-120-050-gn-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Cambered plate C=12% T=5% R=1.1                 
  
 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   0.1743   0.10427   0.10101  -0.1771   0.9338   0.0252
 -10.250   0.1929   0.10111   0.09782  -0.1812   0.9326   0.0253
 -10.000   0.1961   0.09932   0.09603  -0.1805   0.9277   0.0253
  -9.750   0.2071   0.09699   0.09370  -0.1819   0.9243   0.0255
  -9.500   0.2230   0.09465   0.09134  -0.1843   0.9220   0.0256
  -9.250   0.2414   0.09233   0.08900  -0.1873   0.9200   0.0259
  -9.000   0.2614   0.09001   0.08666  -0.1907   0.9181   0.0267
  -8.750   0.2717   0.08807   0.08471  -0.1916   0.9143   0.0278
  -8.500   0.2787   0.08622   0.08285  -0.1917   0.9096   0.0281
  -8.250   0.2925   0.08399   0.08061  -0.1936   0.9063   0.0281
  -8.000   0.3086   0.08141   0.07799  -0.1966   0.9033   0.0283
  -7.750   0.3201   0.07926   0.07581  -0.1983   0.8994   0.0284
  -7.250   0.3377   0.07590   0.07246  -0.1981   0.8907   0.0286
  -7.000   0.3540   0.07411   0.07064  -0.1998   0.8874   0.0290
  -6.750   0.3676   0.07248   0.06900  -0.2009   0.8840   0.0297
  -6.500   0.3708   0.07124   0.06778  -0.1993   0.8787   0.0299
  -6.250   0.3802   0.06966   0.06618  -0.1995   0.8742   0.0308
  -6.000   0.3917   0.06766   0.06414  -0.2009   0.8701   0.0314
  -5.750   0.3908   0.06648   0.06299  -0.1988   0.8646   0.0315
  -5.500   0.3920   0.06519   0.06170  -0.1974   0.8591   0.0315
  -5.250   0.4046   0.06335   0.05982  -0.1989   0.8550   0.0316
  -5.000   0.4172   0.06156   0.05802  -0.1995   0.8515   0.0317
  -4.750   0.4224   0.06044   0.05694  -0.1977   0.8466   0.0318
  -4.500   0.4336   0.05914   0.05564  -0.1976   0.8424   0.0322
  -4.250   0.4497   0.05759   0.05406  -0.1989   0.8388   0.0326
  -4.000   0.4659   0.05603   0.05249  -0.2002   0.8352   0.0333
  -3.750   0.4735   0.05465   0.05112  -0.1999   0.8300   0.0346
  -3.500   0.4888   0.05289   0.04935  -0.2015   0.8256   0.0348
  -3.250   0.5100   0.05091   0.04732  -0.2043   0.8221   0.0348
  -3.000   0.5318   0.04896   0.04534  -0.2071   0.8185   0.0349
  -2.500   0.5571   0.04602   0.04242  -0.2063   0.8099   0.0351
  -2.250   0.5779   0.04462   0.04099  -0.2075   0.8065   0.0354
  -2.000   0.6041   0.04327   0.03961  -0.2099   0.8035   0.0366
  -1.750   0.6257   0.04164   0.03797  -0.2118   0.7993   0.0381
  -1.500   0.6491   0.03989   0.03620  -0.2139   0.7952   0.0382
  -1.250   0.6783   0.03802   0.03427  -0.2171   0.7914   0.0383
  -1.000   0.7179   0.03581   0.03196  -0.2227   0.7867   0.0383
  -0.750   0.7250   0.03465   0.03082  -0.2198   0.7807   0.0385
  -0.500   0.7379   0.03370   0.02985  -0.2179   0.7716   0.0388
  -0.250   0.7501   0.03287   0.02901  -0.2160   0.7634   0.0395
   0.000   0.7728   0.03170   0.02775  -0.2164   0.7529   0.0406
   0.250   0.8034   0.03008   0.02604  -0.2188   0.7430   0.0419
   0.500   0.8325   0.02852   0.02435  -0.2206   0.7312   0.0420
   1.000   0.8752   0.02605   0.02172  -0.2202   0.7063   0.0424
   1.500   0.8945   0.02519   0.02065  -0.2142   0.6638   0.0431
   1.750   0.9008   0.02495   0.02022  -0.2104   0.6320   0.0436
   2.000   0.9000   0.02509   0.02010  -0.2053   0.5845   0.0441
   2.250   0.8893   0.02589   0.02051  -0.1984   0.5144   0.0443
   2.500   0.8646   0.02786   0.02183  -0.1892   0.3901   0.0443
   2.750   0.8363   0.03046   0.02360  -0.1801   0.1972   0.0442
   3.500   0.8917   0.03013   0.02253  -0.1775   0.0328   0.0450
   3.750   0.9211   0.02930   0.02158  -0.1782   0.0314   0.0456
   4.000   0.9457   0.02876   0.02095  -0.1782   0.0302   0.0449
   4.250   0.9716   0.02813   0.02020  -0.1781   0.0295   0.0447
   4.500   0.9969   0.02753   0.01945  -0.1779   0.0288   0.0448
   4.750   1.0256   0.02638   0.01802  -0.1779   0.0284   0.0458
   5.000   1.0492   0.02564   0.01698  -0.1771   0.0279   0.0461
   5.500   1.0878   0.02559   0.01663  -0.1743   0.0273   0.0468
   5.750   1.1048   0.02595   0.01694  -0.1726   0.0269   0.0471
   6.000   1.1207   0.02646   0.01746  -0.1707   0.0267   0.0475
   6.250   1.1365   0.02699   0.01798  -0.1689   0.0261   0.0482
   6.500   1.1525   0.02749   0.01843  -0.1670   0.0259   0.0487
   6.750   1.1680   0.02802   0.01890  -0.1651   0.0256   0.0491
   7.000   1.1826   0.02865   0.01949  -0.1631   0.0254   0.0494
   7.250   1.1971   0.02933   0.02015  -0.1611   0.0251   0.0497
   7.500   1.2108   0.03010   0.02091  -0.1590   0.0250   0.0500
   7.750   1.2239   0.03094   0.02175  -0.1569   0.0248   0.0503
   8.000   1.2368   0.03182   0.02263  -0.1548   0.0246   0.0505
   8.250   1.2495   0.03277   0.02358  -0.1528   0.0244   0.0510
   8.500   1.2612   0.03378   0.02463  -0.1506   0.0242   0.0516
   8.750   1.2724   0.03487   0.02576  -0.1485   0.0240   0.0520
   9.000   1.2833   0.03603   0.02695  -0.1463   0.0238   0.0523
   9.250   1.2932   0.03730   0.02826  -0.1441   0.0237   0.0525
   9.500   1.3027   0.03865   0.02966  -0.1419   0.0235   0.0529
   9.750   1.3124   0.04002   0.03106  -0.1398   0.0233   0.0534
  10.000   1.3254   0.04110   0.03220  -0.1380   0.0232   0.0540
  10.250   1.3383   0.04222   0.03336  -0.1363   0.0230   0.0545
  10.500   1.3516   0.04332   0.03452  -0.1347   0.0227   0.0553
  10.750   1.3643   0.04452   0.03576  -0.1330   0.0226   0.0562
  11.000   1.3773   0.04571   0.03700  -0.1313   0.0224   0.0574
  11.250   1.3906   0.04689   0.03823  -0.1297   0.0222   0.0591
  11.500   1.4044   0.04806   0.03945  -0.1282   0.0220   0.0613
  11.750   1.4189   0.04918   0.04062  -0.1268   0.0218   0.0657
  12.000   1.4340   0.05028   0.04178  -0.1254   0.0217   0.0776
  12.250   1.4502   0.05126   0.04307  -0.1243   0.0215   0.2916
  12.750   1.4957   0.05317   0.04576  -0.1246   0.0210   1.0000
  13.000   1.5112   0.05422   0.04683  -0.1233   0.0209   1.0000
  13.250   1.5272   0.05526   0.04790  -0.1220   0.0207   1.0000
  13.500   1.5424   0.05637   0.04905  -0.1207   0.0205   1.0000
  13.750   1.5582   0.05746   0.05018  -0.1194   0.0204   1.0000
  14.000   1.5730   0.05865   0.05140  -0.1181   0.0202   1.0000
  14.250   1.5862   0.05993   0.05271  -0.1168   0.0200   1.0000
  14.500   1.5998   0.06122   0.05405  -0.1156   0.0198   1.0000
  14.750   1.6139   0.06251   0.05536  -0.1144   0.0196   1.0000
  15.000   1.6333   0.06361   0.05650  -0.1135   0.0194   1.0000
  15.250   1.6492   0.06506   0.05806  -0.1124   0.0192   1.0000
  15.500   1.6598   0.06679   0.05993  -0.1110   0.0191   1.0000
  15.750   1.6701   0.06864   0.06194  -0.1096   0.0190   1.0000
  16.000   1.6803   0.07062   0.06409  -0.1082   0.0188   1.0000
  16.250   1.6893   0.07285   0.06651  -0.1069   0.0186   1.0000
  16.500   1.6960   0.07537   0.06923  -0.1055   0.0184   1.0000
  16.750   1.7004   0.07818   0.07225  -0.1041   0.0182   1.0000
  17.000   1.7015   0.08133   0.07562  -0.1026   0.0180   1.0000
  17.250   1.6999   0.08470   0.07920  -0.1012   0.0178   1.0000
  17.500   1.6956   0.08836   0.08307  -0.1000   0.0176   1.0000
  17.750   1.6896   0.09212   0.08704  -0.0989   0.0175   1.0000
  18.000   1.6826   0.09591   0.09100  -0.0980   0.0173   1.0000
  18.250   1.6745   0.09983   0.09510  -0.0973   0.0171   1.0000
  18.500   1.6653   0.10394   0.09938  -0.0969   0.0170   1.0000
  18.750   1.6554   0.10820   0.10380  -0.0968   0.0169   1.0000
  19.000   1.6444   0.11271   0.10847  -0.0970   0.0168   1.0000
  19.250   1.6319   0.11758   0.11351  -0.0976   0.0167   1.0000
  19.500   1.6181   0.12279   0.11889  -0.0986   0.0167   1.0000
  19.750   1.6025   0.12848   0.12477  -0.1002   0.0166   1.0000
  20.000   1.5860   0.13453   0.13098  -0.1022   0.0165   1.0000
  20.250   1.5670   0.14132   0.13795  -0.1051   0.0165   1.0000
  20.500   1.5451   0.14906   0.14588  -0.1089   0.0164   1.0000
  20.750   1.5200   0.15799   0.15501  -0.1140   0.0164   1.0000
  21.000   1.4823   0.17087   0.16815  -0.1225   0.0164   1.0000
<< Back to Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn)

Polar data table (+)

Polar graphs


<< Back to Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn)