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=14% T=5% R=0.96 (cp-140-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=1


Details Polar file
Airfoil: Cambered plate C=14% T=5% R=0.96 (cp-140-050-gn)
Reynolds number: 1,000,000
Max Cl/Cd: 46.26 at α=5.25°
Description: Mach=0 Ncrit=1
Source: Xfoil prediction
Download polar: xf-cp-140-050-gn-1000000-n1.txt
Download as CSV file: xf-cp-140-050-gn-1000000-n1.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Cambered plate C=14% T=5% R=0.96                
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000   0.2507   0.11126   0.10796  -0.2107   0.8212   0.0076
 -12.750   0.2589   0.10898   0.10567  -0.2117   0.8179   0.0078
 -12.500   0.2671   0.10682   0.10349  -0.2126   0.8141   0.0080
 -12.250   0.2768   0.10511   0.10176  -0.2134   0.8108   0.0082
 -12.000   0.2856   0.10316   0.09979  -0.2142   0.8073   0.0082
 -11.750   0.2948   0.10129   0.09790  -0.2151   0.8036   0.0085
 -11.500   0.3032   0.09927   0.09587  -0.2158   0.7999   0.0091
 -11.250   0.3120   0.09740   0.09399  -0.2165   0.7969   0.0091
 -11.000   0.3198   0.09556   0.09213  -0.2169   0.7932   0.0094
 -10.750   0.3283   0.09367   0.09023  -0.2175   0.7896   0.0096
 -10.500   0.3366   0.09188   0.08842  -0.2180   0.7850   0.0096
 -10.250   0.3447   0.09003   0.08656  -0.2184   0.7820   0.0098
 -10.000   0.3529   0.08837   0.08489  -0.2187   0.7788   0.0100
  -9.750   0.3606   0.08673   0.08323  -0.2188   0.7749   0.0102
  -9.500   0.3683   0.08504   0.08153  -0.2189   0.7704   0.0107
  -9.250   0.3757   0.08344   0.07993  -0.2189   0.7666   0.0110
  -9.000   0.3819   0.08186   0.07834  -0.2186   0.7627   0.0113
  -8.750   0.3876   0.08030   0.07677  -0.2181   0.7597   0.0115
  -8.500   0.3929   0.07874   0.07520  -0.2175   0.7555   0.0117
  -8.250   0.3981   0.07748   0.07394  -0.2165   0.7508   0.0117
  -8.000   0.4018   0.07608   0.07254  -0.2154   0.7474   0.0119
  -7.750   0.4043   0.07487   0.07132  -0.2138   0.7436   0.0119
  -7.500   0.4079   0.07361   0.07007  -0.2125   0.7397   0.0124
  -7.250   0.4099   0.07241   0.06888  -0.2108   0.7351   0.0127
  -7.000   0.4106   0.07133   0.06780  -0.2086   0.7308   0.0128
  -6.750   0.4091   0.07035   0.06682  -0.2059   0.7266   0.0132
  -6.500   0.4078   0.06940   0.06589  -0.2032   0.7228   0.0131
  -6.250   0.4021   0.06860   0.06510  -0.1995   0.7179   0.0134
  -6.000   0.3970   0.06771   0.06422  -0.1959   0.7134   0.0137
  -5.750   0.3955   0.06663   0.06315  -0.1933   0.7099   0.0138
  -5.500   0.3971   0.06543   0.06196  -0.1915   0.7057   0.0140
  -5.250   0.3986   0.06424   0.06078  -0.1897   0.7009   0.0142
  -5.000   0.3991   0.06305   0.05959  -0.1876   0.6966   0.0144
  -4.750   0.4036   0.06189   0.05844  -0.1863   0.6935   0.0145
  -4.500   0.4105   0.06058   0.05714  -0.1856   0.6898   0.0149
  -4.250   0.4159   0.05935   0.05591  -0.1845   0.6852   0.0152
  -4.000   0.4228   0.05802   0.05457  -0.1837   0.6807   0.0153
  -3.750   0.4319   0.05654   0.05308  -0.1835   0.6772   0.0157
  -3.500   0.4437   0.05495   0.05150  -0.1840   0.6740   0.0160
  -3.250   0.4556   0.05348   0.05001  -0.1842   0.6693   0.0162
  -3.000   0.4702   0.05181   0.04833  -0.1852   0.6650   0.0165
  -2.750   0.4871   0.05002   0.04652  -0.1867   0.6615   0.0167
  -2.500   0.5062   0.04854   0.04503  -0.1882   0.6588   0.0169
  -2.250   0.5261   0.04697   0.04345  -0.1899   0.6550   0.0176
  -2.000   0.5481   0.04533   0.04179  -0.1920   0.6508   0.0179
  -1.750   0.5721   0.04364   0.04006  -0.1946   0.6467   0.0183
  -1.500   0.5987   0.04191   0.03830  -0.1976   0.6436   0.0188
  -1.250   0.6284   0.04018   0.03654  -0.2011   0.6402   0.0190
  -1.000   0.6609   0.03833   0.03465  -0.2053   0.6363   0.0194
  -0.750   0.6912   0.03686   0.03314  -0.2085   0.6324   0.0199
  -0.500   0.7212   0.03546   0.03171  -0.2115   0.6282   0.0205
  -0.250   0.7421   0.03450   0.03064  -0.2125   0.6107   0.0208
   0.000   0.7608   0.03375   0.02974  -0.2130   0.5850   0.0212
   0.250   0.7930   0.03249   0.02839  -0.2162   0.5759   0.0216
   0.500   0.8030   0.03244   0.02812  -0.2147   0.5348   0.0218
   1.000   0.8272   0.03257   0.02774  -0.2124   0.4414   0.0224
   1.250   0.7989   0.03502   0.02954  -0.2034   0.2991   0.0226
   1.500   0.7854   0.03685   0.03083  -0.1976   0.1393   0.0227
   1.750   0.8019   0.03700   0.03068  -0.1974   0.0197   0.0232
   2.000   0.8360   0.03609   0.02969  -0.2004   0.0175   0.0237
   2.250   0.8701   0.03521   0.02873  -0.2032   0.0162   0.0243
   2.500   0.9034   0.03441   0.02785  -0.2058   0.0149   0.0246
   2.750   0.9373   0.03358   0.02693  -0.2085   0.0145   0.0252
   3.000   0.9655   0.03314   0.02644  -0.2097   0.0143   0.0257
   3.250   0.9946   0.03266   0.02589  -0.2111   0.0140   0.0261
   3.500   1.0241   0.03217   0.02532  -0.2125   0.0139   0.0267
   3.750   1.0536   0.03167   0.02474  -0.2138   0.0136   0.0273
   4.000   1.0827   0.03120   0.02418  -0.2149   0.0136   0.0277
   4.250   1.1115   0.03075   0.02362  -0.2158   0.0134   0.0283
   4.500   1.1368   0.03054   0.02334  -0.2160   0.0131   0.0289
   4.750   1.1627   0.03026   0.02295  -0.2162   0.0130   0.0295
   5.000   1.1903   0.02979   0.02233  -0.2167   0.0128   0.0303
   5.250   1.2348   0.02669   0.01830  -0.2196   0.0128   0.0335
   5.500   1.2523   0.02716   0.01871  -0.2181   0.0126   0.0337
   5.750   1.2698   0.02766   0.01916  -0.2166   0.0125   0.0340
   6.000   1.2870   0.02820   0.01967  -0.2150   0.0122   0.0342
   6.250   1.3032   0.02884   0.02029  -0.2133   0.0122   0.0343
   6.500   1.3192   0.02951   0.02096  -0.2116   0.0121   0.0346
   6.750   1.3353   0.03019   0.02164  -0.2099   0.0119   0.0347
   7.000   1.3515   0.03089   0.02233  -0.2083   0.0119   0.0348
   7.250   1.3667   0.03167   0.02313  -0.2066   0.0117   0.0349
   7.500   1.3815   0.03249   0.02396  -0.2048   0.0117   0.0349
   7.750   1.3967   0.03330   0.02478  -0.2031   0.0116   0.0350
   8.000   1.4118   0.03413   0.02563  -0.2014   0.0115   0.0352
   8.250   1.4262   0.03502   0.02654  -0.1996   0.0115   0.0354
   8.500   1.4399   0.03599   0.02753  -0.1978   0.0114   0.0355
   8.750   1.4542   0.03692   0.02849  -0.1961   0.0114   0.0355
   9.000   1.4684   0.03788   0.02946  -0.1944   0.0114   0.0358
   9.250   1.4815   0.03894   0.03055  -0.1926   0.0114   0.0362
   9.500   1.4946   0.04002   0.03166  -0.1908   0.0114   0.0361
   9.750   1.5079   0.04109   0.03276  -0.1891   0.0113   0.0365
  10.000   1.5209   0.04221   0.03391  -0.1874   0.0113   0.0367
  10.250   1.5326   0.04347   0.03520  -0.1856   0.0112   0.0370
  10.500   1.5453   0.04464   0.03641  -0.1839   0.0112   0.0373
  10.750   1.5578   0.04586   0.03766  -0.1822   0.0111   0.0373
  11.000   1.5691   0.04720   0.03905  -0.1805   0.0110   0.0380
  11.250   1.5803   0.04858   0.04046  -0.1788   0.0110   0.0384
  11.500   1.5920   0.04990   0.04183  -0.1771   0.0110   0.0385
  11.750   1.6026   0.05137   0.04334  -0.1754   0.0109   0.0391
  12.000   1.6125   0.05292   0.04493  -0.1737   0.0109   0.0392
  12.250   1.6234   0.05439   0.04645  -0.1721   0.0109   0.0395
  12.500   1.6333   0.05599   0.04810  -0.1705   0.0108   0.0401
  12.750   1.6429   0.05763   0.04979  -0.1689   0.0108   0.0401
  13.000   1.6527   0.05927   0.05149  -0.1674   0.0107   0.0410
  13.250   1.6620   0.06097   0.05324  -0.1658   0.0107   0.0414
  13.750   1.6802   0.06449   0.05701  -0.1629   0.0106   0.2070
  14.750   1.7224   0.07212   0.06560  -0.1595   0.0104   1.0000
  15.000   1.7290   0.07420   0.06773  -0.1581   0.0103   1.0000
  15.250   1.7363   0.07618   0.06976  -0.1567   0.0103   1.0000
  15.500   1.7434   0.07822   0.07184  -0.1553   0.0101   1.0000
  15.750   1.7498   0.08036   0.07404  -0.1540   0.0100   1.0000
  16.000   1.7570   0.08239   0.07612  -0.1528   0.0099   1.0000
  16.250   1.7639   0.08449   0.07827  -0.1516   0.0098   1.0000
  16.500   1.7695   0.08678   0.08061  -0.1505   0.0097   1.0000
  16.750   1.7767   0.08884   0.08273  -0.1494   0.0096   1.0000
  17.000   1.7828   0.09105   0.08500  -0.1483   0.0095   1.0000
  17.250   1.7885   0.09332   0.08733  -0.1473   0.0094   1.0000
  17.500   1.7950   0.09549   0.08955  -0.1464   0.0094   1.0000
  17.750   1.8015   0.09764   0.09176  -0.1455   0.0093   1.0000
  18.000   1.8066   0.10001   0.09419  -0.1446   0.0092   1.0000
  18.250   1.8129   0.10219   0.09644  -0.1438   0.0092   1.0000
  18.500   1.8194   0.10434   0.09864  -0.1431   0.0091   1.0000
  18.750   1.8249   0.10663   0.10100  -0.1424   0.0090   1.0000
  19.000   1.8312   0.10880   0.10322  -0.1417   0.0090   1.0000
  19.250   1.8376   0.11091   0.10539  -0.1411   0.0089   1.0000
  19.500   1.8425   0.11325   0.10780  -0.1406   0.0089   1.0000
  19.750   1.8482   0.11547   0.11008  -0.1401   0.0088   1.0000
  20.000   1.8543   0.11759   0.11225  -0.1396   0.0088   1.0000
  20.250   1.8595   0.11987   0.11459  -0.1393   0.0087   1.0000
  20.500   1.8641   0.12219   0.11699  -0.1389   0.0087   1.0000
  20.750   1.8690   0.12443   0.11930  -0.1386   0.0087   1.0000
  21.000   1.8732   0.12676   0.12170  -0.1383   0.0086   1.0000
  21.250   1.8771   0.12913   0.12415  -0.1381   0.0086   1.0000
  21.500   1.8814   0.13140   0.12650  -0.1379   0.0085   1.0000
  21.750   1.8853   0.13372   0.12890  -0.1379   0.0085   1.0000
  22.000   1.8883   0.13616   0.13143  -0.1379   0.0085   1.0000
  22.250   1.8917   0.13850   0.13385  -0.1379   0.0084   1.0000
  22.500   1.8948   0.14087   0.13631  -0.1380   0.0084   1.0000
  22.750   1.8967   0.14343   0.13896  -0.1382   0.0083   1.0000
  23.000   1.8991   0.14588   0.14151  -0.1384   0.0083   1.0000
  23.250   1.9008   0.14842   0.14414  -0.1388   0.0082   1.0000
  23.500   1.9018   0.15109   0.14692  -0.1392   0.0081   1.0000
  23.750   1.9028   0.15371   0.14964  -0.1398   0.0080   1.0000
  24.000   1.9028   0.15653   0.15255  -0.1405   0.0079   1.0000
  24.250   1.9024   0.15939   0.15553  -0.1413   0.0078   1.0000
<< Back to Cambered plate C=14% T=5% R=0.96 (cp-140-050-gn)

Polar data table (+)

Polar graphs


<< Back to Cambered plate C=14% T=5% R=0.96 (cp-140-050-gn)