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NASA SC(2)-0518 AIRFOIL (sc20518-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0518 AIRFOIL (sc20518-il)
Reynolds number: 50,000
Max Cl/Cd: 20.86 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20518-il-50000-n5.txt
Download as CSV file: xf-sc20518-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0518 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.6513   0.09846   0.08872  -0.0558   1.0000   0.1149
 -13.250  -0.7543   0.08048   0.07034  -0.0648   1.0000   0.1148
 -13.000  -0.8035   0.07259   0.06215  -0.0670   1.0000   0.1151
 -12.750  -0.8389   0.06713   0.05640  -0.0673   1.0000   0.1158
 -12.500  -0.8427   0.06438   0.05357  -0.0666   1.0000   0.1172
 -12.250  -0.8354   0.06256   0.05177  -0.0658   1.0000   0.1191
 -12.000  -0.8382   0.06025   0.04938  -0.0646   1.0000   0.1209
 -11.750  -0.8449   0.05787   0.04687  -0.0631   1.0000   0.1226
 -11.500  -0.8529   0.05561   0.04445  -0.0610   1.0000   0.1244
 -11.250  -0.8619   0.05352   0.04218  -0.0585   1.0000   0.1261
 -11.000  -0.8735   0.05165   0.04008  -0.0553   1.0000   0.1277
 -10.750  -0.8523   0.05061   0.03917  -0.0544   1.0000   0.1303
 -10.500  -0.8430   0.04948   0.03805  -0.0525   1.0000   0.1330
 -10.250  -0.8380   0.04823   0.03673  -0.0502   1.0000   0.1358
 -10.000  -0.8332   0.04690   0.03525  -0.0480   1.0000   0.1386
  -9.750  -0.8190   0.04586   0.03419  -0.0462   1.0000   0.1416
  -9.500  -0.8018   0.04514   0.03355  -0.0445   1.0000   0.1451
  -9.250  -0.7900   0.04431   0.03269  -0.0425   1.0000   0.1490
  -9.000  -0.7797   0.04343   0.03168  -0.0403   1.0000   0.1532
  -8.750  -0.7601   0.04293   0.03133  -0.0385   1.0000   0.1574
  -8.500  -0.7471   0.04234   0.03075  -0.0363   1.0000   0.1621
  -8.250  -0.7371   0.04168   0.02999  -0.0339   1.0000   0.1675
  -8.000  -0.7255   0.04116   0.02964  -0.0315   1.0000   0.1726
  -7.750  -0.7172   0.04057   0.02910  -0.0289   1.0000   0.1786
  -7.500  -0.7092   0.03996   0.02854  -0.0264   1.0000   0.1849
  -7.250  -0.7033   0.03931   0.02800  -0.0237   1.0000   0.1918
  -7.000  -0.6969   0.03864   0.02738  -0.0212   1.0000   0.2002
  -6.750  -0.6918   0.03788   0.02676  -0.0188   1.0000   0.2093
  -6.500  -0.6860   0.03706   0.02607  -0.0166   1.0000   0.2204
  -6.250  -0.6796   0.03616   0.02531  -0.0148   1.0000   0.2346
  -6.000  -0.6722   0.03515   0.02450  -0.0133   1.0000   0.2525
  -5.750  -0.6492   0.03392   0.02361  -0.0149   0.9953   0.2859
  -5.500  -0.6233   0.03305   0.02331  -0.0163   0.9902   0.3369
  -5.250  -0.5974   0.03393   0.02483  -0.0141   0.9846   0.3979
  -5.000  -0.5642   0.03620   0.02740  -0.0114   0.9797   0.4474
  -4.750  -0.5324   0.03740   0.02857  -0.0112   0.9741   0.4856
  -4.500  -0.5035   0.03758   0.02860  -0.0127   0.9677   0.5199
  -4.250  -0.4692   0.03810   0.02897  -0.0146   0.9626   0.5464
  -4.000  -0.4440   0.03876   0.02954  -0.0140   0.9556   0.5641
  -3.750  -0.4131   0.03954   0.03022  -0.0141   0.9498   0.5806
  -3.500  -0.3833   0.04029   0.03088  -0.0141   0.9443   0.5975
  -3.250  -0.3597   0.04094   0.03148  -0.0131   0.9372   0.6146
  -3.000  -0.3294   0.04189   0.03238  -0.0126   0.9319   0.6309
  -2.750  -0.3023   0.04302   0.03349  -0.0102   0.9268   0.6413
  -2.500  -0.2812   0.04306   0.03347  -0.0099   0.9193   0.6557
  -2.000  -0.2263   0.04321   0.03350  -0.0105   0.9081   0.6758
  -1.750  -0.2045   0.04348   0.03378  -0.0086   0.9013   0.6811
  -1.500  -0.1748   0.04352   0.03378  -0.0090   0.8960   0.6890
  -1.250  -0.1489   0.04322   0.03342  -0.0104   0.8899   0.6989
  -1.000  -0.1296   0.04328   0.03349  -0.0087   0.8821   0.7038
  -0.750  -0.0988   0.04316   0.03335  -0.0095   0.8764   0.7098
  -0.500  -0.0730   0.04290   0.03306  -0.0107   0.8695   0.7169
  -0.250  -0.0522   0.04273   0.03289  -0.0105   0.8610   0.7224
   0.000  -0.0191   0.04258   0.03274  -0.0114   0.8554   0.7264
   0.250   0.0006   0.04249   0.03267  -0.0107   0.8464   0.7310
   0.500   0.0302   0.04224   0.03244  -0.0119   0.8381   0.7358
   0.750   0.0699   0.04187   0.03205  -0.0151   0.8313   0.7410
   1.000   0.0889   0.04170   0.03193  -0.0142   0.8192   0.7445
   1.250   0.1323   0.04121   0.03148  -0.0164   0.8127   0.7473
   1.500   0.1488   0.04107   0.03138  -0.0150   0.7986   0.7503
   1.750   0.1898   0.04048   0.03084  -0.0170   0.7895   0.7534
   2.000   0.2186   0.04005   0.03047  -0.0174   0.7758   0.7572
   2.250   0.2511   0.03949   0.02995  -0.0184   0.7611   0.7610
   2.500   0.2994   0.03833   0.02885  -0.0209   0.7482   0.7640
   2.750   0.3344   0.03737   0.02796  -0.0207   0.7324   0.7666
   3.000   0.3614   0.03665   0.02731  -0.0196   0.7142   0.7694
   3.250   0.3921   0.03580   0.02653  -0.0192   0.6950   0.7722
   3.500   0.4245   0.03487   0.02566  -0.0189   0.6735   0.7751
   3.750   0.4458   0.03438   0.02524  -0.0176   0.6469   0.7785
   4.000   0.4769   0.03367   0.02456  -0.0177   0.6174   0.7817
   4.250   0.4997   0.03323   0.02415  -0.0166   0.5811   0.7843
   4.500   0.5222   0.03273   0.02360  -0.0148   0.5360   0.7864
   4.750   0.5522   0.03220   0.02273  -0.0139   0.4706   0.7885
   5.000   0.5734   0.03235   0.02237  -0.0124   0.4039   0.7909
   5.250   0.5873   0.03301   0.02262  -0.0106   0.3532   0.7938
   5.500   0.6017   0.03382   0.02313  -0.0093   0.3142   0.7971
   5.750   0.6195   0.03470   0.02378  -0.0088   0.2837   0.8004
   6.000   0.6386   0.03557   0.02446  -0.0085   0.2597   0.8033
   6.250   0.6555   0.03629   0.02507  -0.0073   0.2414   0.8057
   6.500   0.6759   0.03702   0.02571  -0.0068   0.2258   0.8081
   6.750   0.6990   0.03777   0.02639  -0.0067   0.2121   0.8107
   7.000   0.7248   0.03854   0.02707  -0.0070   0.2007   0.8134
   7.250   0.7527   0.03932   0.02780  -0.0077   0.1902   0.8164
   7.500   0.7851   0.04015   0.02865  -0.0091   0.1805   0.8197
   7.750   0.8142   0.04092   0.02930  -0.0096   0.1730   0.8228
   8.000   0.8403   0.04173   0.03025  -0.0096   0.1656   0.8259
   8.250   0.8689   0.04259   0.03107  -0.0101   0.1593   0.8292
   8.500   0.8986   0.04368   0.03224  -0.0110   0.1534   0.8325
   8.750   0.9263   0.04482   0.03346  -0.0118   0.1477   0.8357
   9.000   0.9599   0.04602   0.03454  -0.0135   0.1431   0.8388
   9.250   0.9765   0.04730   0.03613  -0.0125   0.1387   0.8418
   9.500   0.9960   0.04852   0.03748  -0.0120   0.1346   0.8455
   9.750   1.0222   0.04971   0.03859  -0.0125   0.1312   0.8495
  10.000   1.0373   0.05154   0.04072  -0.0120   0.1279   0.8536
  10.250   1.0483   0.05323   0.04265  -0.0108   0.1247   0.8574
  10.500   1.0623   0.05469   0.04423  -0.0098   0.1218   0.8615
  10.750   1.0847   0.05607   0.04556  -0.0101   0.1193   0.8657
  11.000   1.0872   0.05870   0.04855  -0.0089   0.1170   0.8696
  11.250   1.0843   0.06142   0.05163  -0.0073   0.1149   0.8731
  11.500   1.0824   0.06400   0.05448  -0.0059   0.1129   0.8768
  11.750   1.0834   0.06657   0.05724  -0.0051   0.1110   0.8810
  12.000   1.0911   0.06892   0.05969  -0.0050   0.1093   0.8855
  12.250   1.0950   0.07128   0.06214  -0.0042   0.1079   0.8900
  12.500   1.0639   0.07658   0.06789  -0.0036   0.1072   0.8935
  12.750   1.0247   0.08347   0.07521  -0.0047   0.1068   0.8963
  13.000   0.9684   0.09366   0.08583  -0.0087   0.1067   0.8976
  13.250   0.8383   0.12087   0.11360  -0.0257   0.1071   0.8926
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