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

FX 78-K-140 A/20 (fx78k140a20-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 78-K-140 A/20 (fx78k140a20-il)
Reynolds number: 100,000
Max Cl/Cd: 27.77 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx78k140a20-il-100000-n5.txt
Download as CSV file: xf-fx78k140a20-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 78-K-140 A/20                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.1376   0.10985   0.10401  -0.0997   0.7968   0.0418
 -11.000  -0.0730   0.09019   0.08485  -0.0951   0.7887   0.0274
 -10.750  -0.1317   0.10121   0.09536  -0.1030   0.7945   0.0270
 -10.500  -0.1300   0.09729   0.09148  -0.1041   0.7934   0.0265
 -10.250  -0.1264   0.09415   0.08835  -0.1051   0.7922   0.0256
 -10.000  -0.1263   0.09053   0.08477  -0.1065   0.7910   0.0254
  -9.750  -0.1242   0.08755   0.08182  -0.1075   0.7895   0.0245
  -9.500  -0.1291   0.08328   0.07765  -0.1092   0.7878   0.0248
  -9.250  -0.1313   0.07974   0.07416  -0.1106   0.7861   0.0238
  -9.000  -0.1368   0.07571   0.07021  -0.1127   0.7846   0.0238
  -8.750  -0.1435   0.07168   0.06624  -0.1152   0.7829   0.0233
  -8.500  -0.1572   0.06720   0.06178  -0.1171   0.7810   0.0229
  -8.250  -0.1743   0.06375   0.05829  -0.1165   0.7791   0.0226
  -8.000  -0.1880   0.06049   0.05496  -0.1152   0.7772   0.0224
  -7.750  -0.1967   0.05736   0.05174  -0.1138   0.7750   0.0221
  -7.500  -0.2012   0.05468   0.04893  -0.1122   0.7730   0.0236
  -7.250  -0.2047   0.05150   0.04553  -0.1102   0.7711   0.0229
  -7.000  -0.2053   0.04858   0.04230  -0.1080   0.7691   0.0254
  -6.750  -0.2029   0.04558   0.03896  -0.1056   0.7672   0.0256
  -6.500  -0.1969   0.04275   0.03573  -0.1032   0.7656   0.0257
  -6.250  -0.1895   0.04006   0.03259  -0.1008   0.7638   0.0261
  -6.000  -0.1803   0.03777   0.02987  -0.0984   0.7615   0.0264
  -5.750  -0.1675   0.03570   0.02735  -0.0962   0.7591   0.0272
  -5.500  -0.1505   0.03396   0.02515  -0.0944   0.7569   0.0280
  -5.250  -0.1317   0.03215   0.02307  -0.0932   0.7550   0.0292
  -5.000  -0.1116   0.03154   0.02238  -0.0924   0.7535   0.0331
  -4.750  -0.0886   0.03058   0.02115  -0.0916   0.7522   0.0368
  -4.500  -0.0639   0.02954   0.01977  -0.0908   0.7511   0.0397
  -4.250  -0.0516   0.02909   0.01942  -0.0891   0.7475   0.0448
  -4.000  -0.0335   0.02871   0.01892  -0.0876   0.7447   0.0509
  -3.750  -0.0155   0.02811   0.01828  -0.0862   0.7426   0.0563
  -3.500   0.0048   0.02777   0.01786  -0.0851   0.7407   0.0669
  -3.250   0.0256   0.02734   0.01737  -0.0840   0.7391   0.0797
  -3.000   0.0479   0.02689   0.01695  -0.0831   0.7377   0.0979
  -2.750   0.0545   0.02715   0.01728  -0.0804   0.7333   0.1159
  -2.500   0.0689   0.02700   0.01732  -0.0786   0.7302   0.1587
  -2.250   0.0858   0.02646   0.01726  -0.0771   0.7278   0.2726
  -2.000   0.0948   0.02541   0.01723  -0.0740   0.7259   0.5196
  -1.500   0.1057   0.02650   0.01916  -0.0634   0.7193   0.8724
  -1.250   0.1288   0.02704   0.01955  -0.0618   0.7162   0.9117
  -1.000   0.3667   0.02670   0.01849  -0.0995   0.7247   0.9772
  -0.750   0.4101   0.02692   0.01857  -0.1036   0.7225   0.9860
  -0.500   0.4355   0.02753   0.01912  -0.1049   0.7183   0.9921
  -0.250   0.4652   0.02781   0.01929  -0.1063   0.7157   0.9965
   0.000   0.4956   0.02797   0.01937  -0.1076   0.7136   0.9999
   0.250   0.5147   0.02813   0.01945  -0.1065   0.7117   1.0000
   0.750   0.5189   0.02961   0.02090  -0.0994   0.7018   1.0000
   1.000   0.5352   0.02982   0.02106  -0.0977   0.6993   1.0000
   1.250   0.5560   0.02991   0.02109  -0.0966   0.6975   1.0000
   1.750   0.5497   0.03142   0.02260  -0.0878   0.6860   1.0000
   2.000   0.5715   0.03144   0.02261  -0.0868   0.6841   1.0000
   2.500   0.5562   0.03282   0.02397  -0.0762   0.6719   1.0000
   2.750   0.5798   0.03282   0.02396  -0.0755   0.6702   1.0000
   3.250   0.5623   0.03388   0.02500  -0.0644   0.6573   1.0000
   3.750   0.5653   0.03498   0.02608  -0.0572   0.6451   1.0000
   4.000   0.5922   0.03494   0.02607  -0.0570   0.6433   1.0000
   4.500   0.6094   0.03613   0.02728  -0.0525   0.6310   1.0000
   4.750   0.6381   0.03606   0.02724  -0.0526   0.6293   1.0000
   5.000   0.6348   0.03731   0.02852  -0.0495   0.6193   1.0000
   5.250   0.6630   0.03723   0.02849  -0.0495   0.6168   1.0000
   5.750   0.6921   0.03841   0.02981  -0.0471   0.6046   1.0000
   6.000   0.7207   0.03832   0.02980  -0.0472   0.6024   1.0000
   6.250   0.7242   0.03956   0.03109  -0.0452   0.5925   1.0000
   6.500   0.7521   0.03946   0.03110  -0.0452   0.5897   1.0000
   7.000   0.7863   0.04048   0.03235  -0.0436   0.5770   1.0000
   7.250   0.8165   0.04022   0.03223  -0.0437   0.5748   1.0000
   7.500   0.8210   0.04160   0.03370  -0.0421   0.5643   1.0000
   7.750   0.8515   0.04119   0.03345  -0.0422   0.5616   1.0000
   8.000   0.8587   0.04244   0.03487  -0.0408   0.5513   1.0000
   8.250   0.8881   0.04206   0.03467  -0.0407   0.5483   1.0000
   8.750   0.9290   0.04235   0.03532  -0.0393   0.5344   1.0000
   9.500   0.9969   0.03863   0.03201  -0.0344   0.4603   1.0000
   9.750   1.0165   0.03660   0.02877  -0.0304   0.3035   1.0000
  10.000   0.9973   0.03975   0.03115  -0.0269   0.2030   1.0000
  10.250   0.9855   0.04280   0.03360  -0.0245   0.1214   1.0000
  10.500   0.9738   0.04596   0.03608  -0.0220   0.0469   1.0000
  10.750   0.9744   0.04828   0.03826  -0.0205   0.0308   1.0000
  11.000   0.9797   0.05029   0.04036  -0.0192   0.0254   1.0000
  11.250   0.9846   0.05236   0.04256  -0.0181   0.0230   1.0000
  11.500   0.9867   0.05473   0.04505  -0.0170   0.0212   1.0000
  11.750   0.9893   0.05712   0.04759  -0.0159   0.0199   1.0000
  12.000   0.9960   0.05912   0.04975  -0.0151   0.0176   1.0000
  12.250   1.0018   0.06122   0.05195  -0.0143   0.0159   1.0000
  12.500   1.0082   0.06326   0.05411  -0.0134   0.0157   1.0000
  12.750   1.0136   0.06537   0.05634  -0.0126   0.0144   1.0000
  13.000   1.0228   0.06708   0.05811  -0.0110   0.0137   1.0000
  13.250   1.0383   0.06828   0.05938  -0.0096   0.0133   1.0000
  13.500   1.0581   0.06952   0.06077  -0.0081   0.0128   1.0000
  13.750   1.0748   0.07121   0.06267  -0.0071   0.0126   1.0000
  14.000   1.0888   0.07340   0.06510  -0.0062   0.0125   1.0000
  14.250   1.0980   0.07607   0.06803  -0.0054   0.0123   1.0000
  14.500   1.1011   0.07943   0.07171  -0.0048   0.0121   1.0000
  14.750   1.1021   0.08283   0.07536  -0.0045   0.0122   1.0000
  15.000   1.0942   0.08702   0.07988  -0.0044   0.0113   1.0000
  15.250   1.0900   0.09130   0.08439  -0.0045   0.0120   1.0000
  15.500   1.0793   0.09590   0.08929  -0.0052   0.0115   1.0000
  15.750   1.0669   0.10104   0.09469  -0.0063   0.0110   1.0000
  16.000   1.0549   0.10644   0.10035  -0.0077   0.0112   1.0000
  16.250   1.0416   0.11237   0.10648  -0.0096   0.0117   1.0000
  16.500   1.0271   0.11852   0.11287  -0.0124   0.0112   1.0000
  16.750   1.0104   0.12559   0.12016  -0.0157   0.0111   1.0000
  17.000   0.9973   0.13234   0.12706  -0.0191   0.0119   1.0000
  17.250   0.9827   0.13980   0.13465  -0.0230   0.0125   1.0000
  17.500   0.9650   0.14878   0.14381  -0.0287   0.0122   1.0000
  17.750   0.9481   0.15848   0.15365  -0.0348   0.0123   1.0000
  18.000   0.9334   0.16865   0.16390  -0.0411   0.0124   1.0000
  18.250   0.9317   0.17403   0.16926  -0.0439   0.0131   1.0000
  18.500   0.9184   0.18638   0.18165  -0.0511   0.0129   1.0000
  18.750   0.6626   0.16935   0.16533  -0.0390   0.0158   1.0000
<< Back to FX 78-K-140 A/20 (fx78k140a20-il)

Polar data table (+)

Polar graphs


<< Back to FX 78-K-140 A/20 (fx78k140a20-il)