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

FX 68-H-120 (fx68h120-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 68-H-120 (fx68h120-il)
Reynolds number: 100,000
Max Cl/Cd: 40.23 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx68h120-il-100000.txt
Download as CSV file: xf-fx68h120-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 68-H-120                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4791   0.07575   0.07156  -0.0454   1.0000   0.0556
  -9.250  -0.4889   0.06978   0.06564  -0.0498   1.0000   0.0544
  -9.000  -0.5093   0.06453   0.06040  -0.0523   1.0000   0.0531
  -8.750  -0.5420   0.06177   0.05765  -0.0490   1.0000   0.0525
  -8.500  -0.5727   0.05918   0.05501  -0.0447   1.0000   0.0516
  -8.250  -0.6021   0.05596   0.05168  -0.0405   1.0000   0.0507
  -8.000  -0.6325   0.05154   0.04699  -0.0362   1.0000   0.0494
  -7.750  -0.6678   0.04528   0.04001  -0.0311   1.0000   0.0470
  -7.500  -0.6769   0.04143   0.03560  -0.0270   1.0000   0.0461
  -7.250  -0.6765   0.03834   0.03213  -0.0238   1.0000   0.0465
  -7.000  -0.6710   0.03576   0.02921  -0.0209   1.0000   0.0471
  -6.750  -0.6610   0.03408   0.02735  -0.0186   1.0000   0.0494
  -6.500  -0.6496   0.03227   0.02523  -0.0162   1.0000   0.0523
  -6.250  -0.6363   0.03005   0.02256  -0.0138   1.0000   0.0539
  -6.000  -0.6198   0.02810   0.02018  -0.0116   1.0000   0.0557
  -5.750  -0.6027   0.02600   0.01794  -0.0098   1.0000   0.0590
  -5.500  -0.5849   0.02477   0.01664  -0.0080   1.0000   0.0645
  -5.250  -0.5674   0.02364   0.01548  -0.0062   1.0000   0.0753
  -5.000  -0.5494   0.02278   0.01459  -0.0044   1.0000   0.0957
  -4.750  -0.5336   0.02279   0.01454  -0.0023   1.0000   0.1353
  -4.500  -0.5182   0.02295   0.01472  -0.0005   1.0000   0.1655
  -4.250  -0.5014   0.02302   0.01479   0.0010   1.0000   0.1875
  -4.000  -0.4837   0.02292   0.01454   0.0024   1.0000   0.2071
  -3.750  -0.4647   0.02263   0.01425   0.0036   1.0000   0.2230
  -3.500  -0.4430   0.02231   0.01385   0.0043   0.9994   0.2369
  -3.250  -0.4007   0.02215   0.01365   0.0010   0.9917   0.2532
  -3.000  -0.3559   0.02203   0.01345  -0.0026   0.9838   0.2687
  -2.750  -0.3160   0.02182   0.01321  -0.0053   0.9747   0.2838
  -2.500  -0.2750   0.02165   0.01305  -0.0080   0.9652   0.3006
  -2.250  -0.2312   0.02153   0.01294  -0.0113   0.9555   0.3221
  -2.000  -0.1873   0.02128   0.01287  -0.0144   0.9457   0.3512
  -1.750  -0.1522   0.02085   0.01277  -0.0159   0.9347   0.3959
  -1.500   0.0585   0.01940   0.01334  -0.0481   0.9399   0.9916
  -1.250   0.1416   0.01939   0.01303  -0.0586   0.9325   1.0000
  -1.000   0.1914   0.01931   0.01279  -0.0627   0.9207   1.0000
  -0.750   0.2444   0.01911   0.01245  -0.0672   0.9089   1.0000
  -0.500   0.2896   0.01885   0.01209  -0.0699   0.8960   1.0000
  -0.250   0.3275   0.01852   0.01168  -0.0710   0.8818   1.0000
   0.000   0.3582   0.01815   0.01124  -0.0705   0.8666   1.0000
   0.250   0.3837   0.01775   0.01078  -0.0689   0.8509   1.0000
   0.500   0.4061   0.01732   0.01029  -0.0666   0.8350   1.0000
   0.750   0.4262   0.01685   0.00977  -0.0638   0.8186   1.0000
   1.000   0.4429   0.01648   0.00937  -0.0606   0.7981   1.0000
   1.250   0.4624   0.01593   0.00877  -0.0576   0.7790   1.0000
   1.500   0.4808   0.01547   0.00826  -0.0547   0.7553   1.0000
   1.750   0.5001   0.01498   0.00772  -0.0518   0.7269   1.0000
   2.000   0.5199   0.01454   0.00717  -0.0491   0.6905   1.0000
   2.250   0.5398   0.01424   0.00667  -0.0464   0.6415   1.0000
   2.500   0.5596   0.01421   0.00625  -0.0439   0.5862   1.0000
   2.750   0.5792   0.01456   0.00616  -0.0418   0.5376   1.0000
   3.000   0.5993   0.01510   0.00635  -0.0401   0.4976   1.0000
   3.250   0.6199   0.01569   0.00662  -0.0387   0.4657   1.0000
   3.500   0.6409   0.01626   0.00696  -0.0374   0.4376   1.0000
   3.750   0.6620   0.01682   0.00737  -0.0362   0.4125   1.0000
   4.000   0.6835   0.01740   0.00776  -0.0351   0.3917   1.0000
   4.250   0.7052   0.01796   0.00822  -0.0340   0.3729   1.0000
   4.500   0.7273   0.01855   0.00871  -0.0331   0.3571   1.0000
   4.750   0.7497   0.01916   0.00925  -0.0321   0.3432   1.0000
   5.000   0.7721   0.01977   0.00979  -0.0312   0.3309   1.0000
   5.250   0.7949   0.02040   0.01033  -0.0304   0.3201   1.0000
   5.500   0.8177   0.02100   0.01090  -0.0295   0.3101   1.0000
   5.750   0.8401   0.02167   0.01163  -0.0287   0.3011   1.0000
   6.000   0.8646   0.02240   0.01227  -0.0281   0.2944   1.0000
   6.250   0.8864   0.02312   0.01317  -0.0272   0.2872   1.0000
   6.500   0.9105   0.02387   0.01388  -0.0266   0.2815   1.0000
   6.750   0.9327   0.02472   0.01488  -0.0258   0.2759   1.0000
   7.000   0.9550   0.02549   0.01575  -0.0249   0.2702   1.0000
   7.250   0.9800   0.02637   0.01660  -0.0246   0.2658   1.0000
   7.500   0.9983   0.02713   0.01766  -0.0232   0.2594   1.0000
   7.750   1.0174   0.02723   0.01770  -0.0219   0.2482   1.0000
   8.000   1.0373   0.02728   0.01760  -0.0207   0.2373   1.0000
   8.250   1.0510   0.02725   0.01774  -0.0186   0.2259   1.0000
   8.500   1.0639   0.02724   0.01783  -0.0165   0.2141   1.0000
   8.750   1.0785   0.02739   0.01808  -0.0146   0.2048   1.0000
   9.000   1.0878   0.02726   0.01805  -0.0119   0.1925   1.0000
   9.250   1.0976   0.02733   0.01815  -0.0093   0.1818   1.0000
   9.500   1.1015   0.02738   0.01837  -0.0060   0.1657   1.0000
   9.750   1.1105   0.02768   0.01880  -0.0034   0.1498   1.0000
  10.000   1.1195   0.02815   0.01931  -0.0008   0.1301   1.0000
  10.250   1.1308   0.02887   0.02006   0.0013   0.1043   1.0000
  10.500   1.1194   0.03132   0.02190   0.0050   0.0450   1.0000
  10.750   1.1172   0.03344   0.02402   0.0077   0.0392   1.0000
  11.000   1.1175   0.03539   0.02608   0.0100   0.0363   1.0000
  11.250   1.1186   0.03730   0.02819   0.0120   0.0351   1.0000
  11.500   1.1177   0.03942   0.03052   0.0138   0.0342   1.0000
  11.750   1.1143   0.04184   0.03315   0.0152   0.0336   1.0000
  12.000   1.1066   0.04482   0.03634   0.0164   0.0329   1.0000
  12.250   1.0980   0.04809   0.03982   0.0169   0.0326   1.0000
  12.500   1.0852   0.05215   0.04414   0.0167   0.0323   1.0000
  12.750   1.0695   0.05703   0.04922   0.0154   0.0320   1.0000
  13.000   1.0516   0.06289   0.05529   0.0132   0.0320   1.0000
  13.250   1.0352   0.06912   0.06170   0.0102   0.0324   1.0000
  13.500   1.0166   0.07610   0.06886   0.0068   0.0327   1.0000
  13.750   0.9956   0.08364   0.07653   0.0033   0.0326   1.0000
  14.000   0.9805   0.09013   0.08314   0.0004   0.0327   1.0000
<< Back to FX 68-H-120 (fx68h120-il)

Polar data table (+)

Polar graphs


<< Back to FX 68-H-120 (fx68h120-il)