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Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn) Xfoil prediction polar at RE=500,000 Ncrit=1


Details Polar file
Airfoil: Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn)
Reynolds number: 500,000
Max Cl/Cd: 46.05 at α=5.75°
Description: Mach=0 Ncrit=1
Source: Xfoil prediction
Download polar: xf-cp-120-050-gn-500000-n1.txt
Download as CSV file: xf-cp-120-050-gn-500000-n1.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 =   1.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500   0.1622   0.10648   0.10258  -0.1837   0.8608   0.0119
 -11.250   0.1715   0.10426   0.10034  -0.1848   0.8573   0.0121
 -11.000   0.1804   0.10192   0.09798  -0.1859   0.8536   0.0125
 -10.750   0.1899   0.09987   0.09591  -0.1869   0.8499   0.0125
 -10.500   0.1996   0.09797   0.09399  -0.1877   0.8450   0.0128
 -10.250   0.2090   0.09596   0.09196  -0.1885   0.8410   0.0129
 -10.000   0.2187   0.09410   0.09008  -0.1893   0.8373   0.0130
  -9.750   0.2278   0.09218   0.08814  -0.1900   0.8329   0.0134
  -9.500   0.2367   0.09029   0.08623  -0.1905   0.8284   0.0136
  -9.250   0.2451   0.08830   0.08423  -0.1911   0.8242   0.0141
  -9.000   0.2532   0.08634   0.08225  -0.1916   0.8203   0.0146
  -8.750   0.2616   0.08449   0.08038  -0.1920   0.8161   0.0147
  -8.500   0.2702   0.08274   0.07862  -0.1922   0.8112   0.0149
  -8.250   0.2789   0.08108   0.07695  -0.1925   0.8069   0.0149
  -8.000   0.2874   0.07946   0.07531  -0.1926   0.8030   0.0153
  -7.750   0.2957   0.07783   0.07368  -0.1927   0.7985   0.0155
  -7.500   0.3034   0.07620   0.07204  -0.1926   0.7934   0.0157
  -7.250   0.3105   0.07459   0.07042  -0.1924   0.7891   0.0162
  -7.000   0.3166   0.07291   0.06873  -0.1920   0.7849   0.0167
  -6.750   0.3223   0.07128   0.06709  -0.1916   0.7802   0.0170
  -6.500   0.3274   0.06979   0.06560  -0.1908   0.7748   0.0172
  -6.250   0.3325   0.06850   0.06432  -0.1898   0.7709   0.0173
  -6.000   0.3361   0.06727   0.06310  -0.1884   0.7664   0.0175
  -5.750   0.3382   0.06610   0.06193  -0.1867   0.7614   0.0177
  -5.500   0.3430   0.06482   0.06065  -0.1857   0.7562   0.0179
  -5.250   0.3492   0.06341   0.05923  -0.1851   0.7520   0.0183
  -5.000   0.3563   0.06192   0.05775  -0.1848   0.7477   0.0187
  -4.750   0.3633   0.06041   0.05623  -0.1844   0.7426   0.0192
  -4.500   0.3706   0.05890   0.05471  -0.1840   0.7379   0.0195
  -4.250   0.3791   0.05744   0.05325  -0.1837   0.7340   0.0196
  -4.000   0.3865   0.05599   0.05181  -0.1830   0.7293   0.0197
  -3.750   0.3939   0.05470   0.05051  -0.1821   0.7241   0.0199
  -3.500   0.4030   0.05333   0.04914  -0.1815   0.7200   0.0201
  -3.250   0.4149   0.05184   0.04764  -0.1815   0.7164   0.0204
  -3.000   0.4281   0.05029   0.04608  -0.1818   0.7117   0.0209
  -2.750   0.4418   0.04866   0.04444  -0.1822   0.7067   0.0215
  -2.500   0.4577   0.04700   0.04275  -0.1830   0.7026   0.0219
  -2.250   0.4768   0.04533   0.04107  -0.1843   0.6992   0.0221
  -2.000   0.4974   0.04360   0.03931  -0.1859   0.6946   0.0224
  -1.750   0.5186   0.04200   0.03769  -0.1874   0.6900   0.0227
  -1.500   0.5409   0.04048   0.03613  -0.1889   0.6861   0.0230
  -1.250   0.5659   0.03888   0.03451  -0.1909   0.6825   0.0235
  -1.000   0.5936   0.03711   0.03271  -0.1935   0.6785   0.0244
  -0.750   0.6217   0.03546   0.03101  -0.1960   0.6740   0.0248
  -0.500   0.6454   0.03401   0.02948  -0.1973   0.6645   0.0251
  -0.250   0.6667   0.03276   0.02813  -0.1978   0.6503   0.0254
   0.000   0.6805   0.03198   0.02722  -0.1965   0.6249   0.0256
   0.250   0.6887   0.03147   0.02651  -0.1939   0.5916   0.0259
   0.500   0.6837   0.03167   0.02639  -0.1885   0.5314   0.0262
   0.750   0.6522   0.03357   0.02760  -0.1782   0.3869   0.0262
   1.000   0.6444   0.03473   0.02817  -0.1730   0.2447   0.0266
   1.250   0.6441   0.03568   0.02852  -0.1694   0.0286   0.0271
   1.750   0.7089   0.03343   0.02606  -0.1741   0.0210   0.0280
   2.250   0.7692   0.03161   0.02408  -0.1773   0.0197   0.0287
   2.500   0.7982   0.03081   0.02319  -0.1784   0.0194   0.0294
   2.750   0.8279   0.02994   0.02221  -0.1796   0.0190   0.0304
   3.000   0.8566   0.02915   0.02132  -0.1805   0.0189   0.0308
   3.250   0.8848   0.02836   0.02042  -0.1812   0.0186   0.0313
   3.750   0.9365   0.02718   0.01902  -0.1813   0.0181   0.0320
   4.000   0.9622   0.02655   0.01826  -0.1812   0.0179   0.0333
   4.250   0.9879   0.02587   0.01741  -0.1810   0.0178   0.0338
   4.500   1.0157   0.02470   0.01593  -0.1810   0.0177   0.0347
   4.750   1.0391   0.02410   0.01508  -0.1802   0.0176   0.0353
   5.000   1.0616   0.02347   0.01411  -0.1792   0.0174   0.0372
   5.250   1.0805   0.02357   0.01407  -0.1777   0.0173   0.0377
   5.500   1.0985   0.02387   0.01432  -0.1760   0.0171   0.0379
   5.750   1.1162   0.02424   0.01464  -0.1744   0.0171   0.0382
   6.000   1.1337   0.02465   0.01503  -0.1727   0.0170   0.0384
   6.250   1.1503   0.02518   0.01557  -0.1709   0.0169   0.0385
   6.500   1.1667   0.02574   0.01614  -0.1691   0.0169   0.0388
   6.750   1.1830   0.02631   0.01672  -0.1673   0.0167   0.0392
   7.000   1.1993   0.02689   0.01731  -0.1655   0.0167   0.0394
   7.250   1.2149   0.02752   0.01796  -0.1636   0.0165   0.0396
   7.500   1.2300   0.02821   0.01866  -0.1617   0.0165   0.0397
   7.750   1.2455   0.02889   0.01936  -0.1599   0.0163   0.0399
   8.000   1.2607   0.02960   0.02009  -0.1581   0.0162   0.0400
   8.250   1.2752   0.03038   0.02089  -0.1562   0.0160   0.0402
   8.500   1.2897   0.03119   0.02172  -0.1544   0.0159   0.0403
   8.750   1.3039   0.03202   0.02258  -0.1525   0.0158   0.0405
   9.000   1.3177   0.03292   0.02350  -0.1506   0.0157   0.0407
   9.250   1.3311   0.03385   0.02447  -0.1487   0.0157   0.0408
   9.500   1.3443   0.03482   0.02548  -0.1469   0.0156   0.0411
   9.750   1.3575   0.03581   0.02651  -0.1450   0.0156   0.0414
  10.000   1.3699   0.03689   0.02762  -0.1432   0.0155   0.0416
  10.250   1.3824   0.03799   0.02877  -0.1413   0.0155   0.0417
  10.500   1.3948   0.03910   0.02993  -0.1395   0.0154   0.0420
  10.750   1.4062   0.04033   0.03121  -0.1377   0.0154   0.0426
  11.000   1.4180   0.04154   0.03247  -0.1359   0.0153   0.0437
  11.250   1.4293   0.04281   0.03381  -0.1341   0.0153   0.0448
  11.500   1.4402   0.04414   0.03519  -0.1324   0.0152   0.0454
  11.750   1.4514   0.04548   0.03658  -0.1307   0.0151   0.0457
  12.000   1.4620   0.04689   0.03805  -0.1290   0.0151   0.0464
  12.250   1.4723   0.04834   0.03956  -0.1273   0.0150   0.0474
  12.500   1.4828   0.04979   0.04108  -0.1257   0.0148   0.0487
  12.750   1.4932   0.05129   0.04265  -0.1241   0.0147   0.0541
  13.500   1.5399   0.05592   0.04843  -0.1233   0.0140   1.0000
  13.750   1.5488   0.05758   0.05013  -0.1217   0.0139   1.0000
  14.000   1.5582   0.05919   0.05180  -0.1201   0.0137   1.0000
  14.250   1.5674   0.06082   0.05348  -0.1186   0.0136   1.0000
  14.500   1.5765   0.06250   0.05523  -0.1171   0.0135   1.0000
  14.750   1.5858   0.06417   0.05695  -0.1157   0.0134   1.0000
  15.000   1.5951   0.06584   0.05868  -0.1143   0.0133   1.0000
  15.250   1.6045   0.06751   0.06040  -0.1130   0.0132   1.0000
  15.500   1.6135   0.06923   0.06219  -0.1117   0.0131   1.0000
  15.750   1.6226   0.07096   0.06399  -0.1104   0.0130   1.0000
  16.000   1.6318   0.07267   0.06577  -0.1092   0.0129   1.0000
  16.250   1.6409   0.07442   0.06758  -0.1080   0.0128   1.0000
  16.500   1.6495   0.07625   0.06949  -0.1069   0.0127   1.0000
  16.750   1.6580   0.07809   0.07140  -0.1058   0.0127   1.0000
  17.000   1.6665   0.07993   0.07332  -0.1047   0.0126   1.0000
  17.250   1.6748   0.08180   0.07529  -0.1036   0.0125   1.0000
  17.500   1.6825   0.08376   0.07734  -0.1025   0.0125   1.0000
  17.750   1.6901   0.08575   0.07945  -0.1015   0.0124   1.0000
  18.000   1.6976   0.08777   0.08160  -0.1005   0.0122   1.0000
  18.250   1.7049   0.08985   0.08382  -0.0995   0.0120   1.0000
  18.500   1.7114   0.09206   0.08618  -0.0986   0.0117   1.0000
  18.750   1.7163   0.09449   0.08876  -0.0978   0.0115   1.0000
  19.000   1.7198   0.09712   0.09154  -0.0971   0.0114   1.0000
  19.250   1.7221   0.09994   0.09453  -0.0965   0.0113   1.0000
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