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


Details Polar file
Airfoil: Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn)
Reynolds number: 1,000,000
Max Cl/Cd: 56.44 at α=4.75°
Description: Mach=0 Ncrit=1
Source: Xfoil prediction
Download polar: xf-cp-120-050-gn-1000000-n1.txt
Download as CSV file: xf-cp-120-050-gn-1000000-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 =     1.000 e 6     Ncrit =   1.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750   0.1921   0.09726   0.09399  -0.1894   0.8211   0.0121
 -10.500   0.2005   0.09501   0.09173  -0.1903   0.8174   0.0124
 -10.250   0.2092   0.09281   0.08952  -0.1912   0.8134   0.0126
 -10.000   0.2200   0.09116   0.08785  -0.1920   0.8092   0.0126
  -9.750   0.2292   0.08936   0.08603  -0.1926   0.8042   0.0129
  -9.500   0.2392   0.08762   0.08427  -0.1933   0.8004   0.0131
  -9.250   0.2482   0.08564   0.08228  -0.1940   0.7966   0.0134
  -9.000   0.2571   0.08379   0.08042  -0.1945   0.7918   0.0140
  -8.750   0.2654   0.08197   0.07858  -0.1949   0.7872   0.0142
  -8.500   0.2735   0.08005   0.07664  -0.1953   0.7828   0.0144
  -8.250   0.2827   0.07835   0.07494  -0.1957   0.7785   0.0145
  -8.000   0.2907   0.07658   0.07316  -0.1959   0.7738   0.0149
  -7.750   0.2995   0.07514   0.07170  -0.1959   0.7695   0.0150
  -7.500   0.3078   0.07347   0.07002  -0.1960   0.7653   0.0152
  -7.250   0.3162   0.07192   0.06847  -0.1960   0.7611   0.0155
  -7.000   0.3228   0.07032   0.06687  -0.1957   0.7565   0.0160
  -6.750   0.3275   0.06876   0.06529  -0.1950   0.7511   0.0165
  -6.500   0.3326   0.06723   0.06376  -0.1943   0.7469   0.0167
  -6.250   0.3355   0.06586   0.06239  -0.1930   0.7420   0.0169
  -6.000   0.3355   0.06465   0.06119  -0.1910   0.7365   0.0171
  -5.750   0.3407   0.06326   0.05979  -0.1903   0.7321   0.0172
  -5.500   0.3489   0.06193   0.05847  -0.1900   0.7278   0.0175
  -5.250   0.3564   0.06053   0.05706  -0.1896   0.7231   0.0177
  -5.000   0.3631   0.05920   0.05572  -0.1889   0.7179   0.0181
  -4.750   0.3715   0.05769   0.05421  -0.1887   0.7137   0.0185
  -4.500   0.3780   0.05622   0.05275  -0.1880   0.7096   0.0189
  -4.250   0.3841   0.05485   0.05137  -0.1870   0.7050   0.0191
  -4.000   0.3912   0.05340   0.04992  -0.1863   0.7003   0.0192
  -3.750   0.4025   0.05175   0.04826  -0.1865   0.6961   0.0196
  -3.500   0.4149   0.05010   0.04660  -0.1869   0.6915   0.0198
  -3.250   0.4274   0.04867   0.04516  -0.1869   0.6868   0.0200
  -3.000   0.4412   0.04723   0.04371  -0.1871   0.6826   0.0203
  -2.750   0.4584   0.04564   0.04210  -0.1881   0.6781   0.0209
  -2.500   0.4776   0.04393   0.04037  -0.1895   0.6741   0.0214
  -2.250   0.4972   0.04228   0.03869  -0.1908   0.6698   0.0217
  -2.000   0.5181   0.04057   0.03695  -0.1923   0.6654   0.0220
  -1.750   0.5398   0.03878   0.03510  -0.1940   0.6563   0.0224
  -1.500   0.5589   0.03743   0.03369  -0.1946   0.6450   0.0226
  -1.250   0.5674   0.03663   0.03276  -0.1925   0.6179   0.0228
  -1.000   0.5732   0.03597   0.03190  -0.1899   0.5794   0.0234
  -0.750   0.5911   0.03484   0.03065  -0.1900   0.5558   0.0240
  -0.500   0.5380   0.03741   0.03235  -0.1747   0.3564   0.0238
  -0.250   0.5257   0.03828   0.03264  -0.1686   0.1908   0.0240
   0.000   0.5368   0.03800   0.03196  -0.1674   0.0225   0.0243
   0.250   0.5710   0.03634   0.03022  -0.1709   0.0208   0.0248
   0.500   0.6054   0.03479   0.02858  -0.1742   0.0196   0.0252
   0.750   0.6378   0.03357   0.02729  -0.1768   0.0187   0.0255
   1.000   0.6690   0.03252   0.02617  -0.1789   0.0188   0.0262
   1.250   0.7015   0.03137   0.02494  -0.1813   0.0185   0.0269
   1.500   0.7343   0.03019   0.02367  -0.1836   0.0182   0.0274
   1.750   0.7677   0.02896   0.02233  -0.1859   0.0177   0.0280
   2.000   0.7996   0.02783   0.02110  -0.1877   0.0175   0.0284
   2.250   0.8276   0.02710   0.02029  -0.1885   0.0173   0.0287
   2.500   0.8568   0.02620   0.01929  -0.1894   0.0171   0.0298
   2.750   0.8862   0.02522   0.01819  -0.1904   0.0169   0.0304
   3.000   0.9165   0.02405   0.01687  -0.1913   0.0168   0.0310
   3.250   0.9457   0.02282   0.01546  -0.1919   0.0166   0.0316
   3.500   0.9719   0.02185   0.01430  -0.1918   0.0164   0.0327
   3.750   1.0047   0.01830   0.00984  -0.1928   0.0163   0.0356
   4.000   1.0239   0.01846   0.00994  -0.1912   0.0161   0.0362
   4.250   1.0432   0.01866   0.01008  -0.1896   0.0161   0.0367
   4.500   1.0624   0.01889   0.01028  -0.1881   0.0160   0.0369
   4.750   1.0814   0.01916   0.01052  -0.1865   0.0160   0.0373
   5.000   1.0995   0.01950   0.01084  -0.1847   0.0158   0.0374
   5.250   1.1176   0.01985   0.01118  -0.1830   0.0158   0.0376
   5.500   1.1357   0.02021   0.01153  -0.1812   0.0157   0.0377
   5.750   1.1538   0.02059   0.01191  -0.1795   0.0157   0.0378
   6.000   1.1716   0.02100   0.01231  -0.1778   0.0157   0.0379
   6.250   1.1886   0.02147   0.01278  -0.1760   0.0157   0.0380
   6.500   1.2058   0.02193   0.01325  -0.1742   0.0157   0.0381
   6.750   1.2231   0.02240   0.01373  -0.1724   0.0156   0.0383
   7.000   1.2402   0.02290   0.01424  -0.1707   0.0155   0.0384
   7.250   1.2566   0.02344   0.01480  -0.1688   0.0154   0.0385
   7.500   1.2725   0.02403   0.01541  -0.1669   0.0154   0.0386
   7.750   1.2890   0.02460   0.01599  -0.1651   0.0153   0.0387
   8.000   1.3052   0.02520   0.01661  -0.1633   0.0153   0.0388
   8.250   1.3204   0.02586   0.01730  -0.1614   0.0152   0.0389
   8.500   1.3357   0.02654   0.01800  -0.1595   0.0152   0.0391
   8.750   1.3510   0.02724   0.01872  -0.1577   0.0151   0.0392
   9.000   1.3662   0.02795   0.01946  -0.1558   0.0151   0.0393
   9.250   1.3805   0.02874   0.02027  -0.1539   0.0150   0.0394
   9.500   1.3947   0.02955   0.02112  -0.1520   0.0150   0.0397
   9.750   1.4095   0.03034   0.02193  -0.1502   0.0149   0.0399
  10.000   1.4233   0.03121   0.02284  -0.1483   0.0148   0.0402
  10.250   1.4365   0.03215   0.02381  -0.1464   0.0148   0.0403
  10.500   1.4505   0.03303   0.02472  -0.1446   0.0148   0.0405
  10.750   1.4635   0.03401   0.02574  -0.1428   0.0147   0.0408
  11.000   1.4761   0.03504   0.02681  -0.1409   0.0146   0.0412
  11.250   1.4889   0.03607   0.02788  -0.1391   0.0146   0.0416
  11.500   1.5019   0.03710   0.02895  -0.1374   0.0144   0.0419
  11.750   1.5140   0.03822   0.03011  -0.1356   0.0143   0.0424
  12.000   1.5263   0.03934   0.03128  -0.1338   0.0141   0.0437
  12.250   1.5385   0.04049   0.03248  -0.1321   0.0140   0.0451
  12.500   1.5500   0.04171   0.03374  -0.1304   0.0138   0.0460
  12.750   1.5611   0.04299   0.03507  -0.1287   0.0138   0.0472
  13.000   1.5730   0.04422   0.03635  -0.1270   0.0136   0.0515
  13.250   1.6110   0.04559   0.03883  -0.1315   0.0135   1.0000
  13.500   1.6206   0.04701   0.04029  -0.1296   0.0134   1.0000
  13.750   1.6301   0.04844   0.04175  -0.1278   0.0133   1.0000
  14.000   1.6404   0.04981   0.04315  -0.1261   0.0132   1.0000
  14.250   1.6488   0.05138   0.04477  -0.1244   0.0131   1.0000
  14.500   1.6584   0.05285   0.04627  -0.1227   0.0130   1.0000
  14.750   1.6681   0.05433   0.04779  -0.1211   0.0130   1.0000
  15.000   1.6765   0.05596   0.04947  -0.1195   0.0129   1.0000
  15.250   1.6860   0.05749   0.05103  -0.1180   0.0128   1.0000
  15.500   1.6944   0.05915   0.05273  -0.1165   0.0128   1.0000
  15.750   1.7027   0.06082   0.05445  -0.1150   0.0127   1.0000
  16.000   1.7113   0.06248   0.05615  -0.1136   0.0127   1.0000
  16.250   1.7192   0.06425   0.05797  -0.1122   0.0126   1.0000
  16.500   1.7255   0.06621   0.05999  -0.1107   0.0126   1.0000
  16.750   1.7333   0.06800   0.06184  -0.1094   0.0125   1.0000
  17.000   1.7398   0.06999   0.06387  -0.1081   0.0125   1.0000
  17.250   1.7462   0.07199   0.06595  -0.1068   0.0124   1.0000
  17.500   1.7535   0.07389   0.06790  -0.1057   0.0124   1.0000
  17.750   1.7590   0.07604   0.07012  -0.1045   0.0123   1.0000
  18.000   1.7654   0.07810   0.07224  -0.1035   0.0123   1.0000
  18.250   1.7718   0.08016   0.07436  -0.1024   0.0122   1.0000
  18.500   1.7770   0.08240   0.07668  -0.1015   0.0121   1.0000
  18.750   1.7828   0.08458   0.07893  -0.1006   0.0120   1.0000
  19.000   1.7891   0.08671   0.08112  -0.0998   0.0120   1.0000
  19.250   1.7936   0.08908   0.08356  -0.0990   0.0118   1.0000
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