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FX 78-K-150/20 (fx78k150-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 78-K-150/20 (fx78k150-il)
Reynolds number: 200,000
Max Cl/Cd: 46.22 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx78k150-il-200000.txt
Download as CSV file: xf-fx78k150-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 78-K-150/20                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.1148   0.10995   0.10551  -0.1131   0.8042   0.0501
 -11.750  -0.1229   0.10690   0.10254  -0.1163   0.8028   0.0510
 -11.500  -0.1287   0.10364   0.09934  -0.1189   0.8016   0.0513
 -11.250  -0.1289   0.10025   0.09599  -0.1207   0.8004   0.0514
 -11.000  -0.1210   0.09502   0.09078  -0.1197   0.7996   0.0527
 -10.750  -0.1086   0.09279   0.08854  -0.1189   0.7983   0.0541
 -10.500  -0.1020   0.09037   0.08613  -0.1190   0.7972   0.0559
 -10.250  -0.1010   0.08754   0.08332  -0.1199   0.7960   0.0567
 -10.000  -0.1024   0.08441   0.08022  -0.1208   0.7948   0.0578
  -9.750  -0.1067   0.08112   0.07696  -0.1220   0.7934   0.0595
  -9.500  -0.1368   0.07540   0.07133  -0.1280   0.7918   0.0631
  -9.250  -0.1655   0.07129   0.06722  -0.1303   0.7902   0.0635
  -9.000  -0.1830   0.06862   0.06457  -0.1291   0.7886   0.0635
  -8.750  -0.2134   0.06731   0.06319  -0.1253   0.7868   0.0638
  -8.500  -0.2345   0.06596   0.06168  -0.1221   0.7848   0.0641
  -8.250  -0.2436   0.06374   0.05930  -0.1196   0.7828   0.0642
  -8.000  -0.2813   0.04972   0.04474  -0.1150   0.7812   0.0404
  -7.750  -0.2787   0.04578   0.04077  -0.1134   0.7799   0.0383
  -7.500  -0.2812   0.04262   0.03731  -0.1102   0.7787   0.0367
  -7.250  -0.2794   0.04014   0.03441  -0.1069   0.7776   0.0380
  -7.000  -0.2761   0.03836   0.03227  -0.1039   0.7753   0.0390
  -6.750  -0.2702   0.03673   0.03028  -0.1011   0.7726   0.0396
  -6.250  -0.2514   0.03275   0.02568  -0.0965   0.7690   0.0422
  -6.000  -0.2339   0.03235   0.02522  -0.0953   0.7673   0.0450
  -5.750  -0.2139   0.03142   0.02404  -0.0940   0.7658   0.0482
  -5.500  -0.1907   0.03052   0.02280  -0.0929   0.7645   0.0509
  -5.250  -0.1673   0.02917   0.02136  -0.0923   0.7634   0.0557
  -5.000  -0.1689   0.02991   0.02212  -0.0890   0.7597   0.0584
  -4.750  -0.1635   0.03019   0.02233  -0.0861   0.7566   0.0617
  -4.500  -0.1474   0.02972   0.02174  -0.0844   0.7542   0.0663
  -4.250  -0.1287   0.02944   0.02148  -0.0832   0.7525   0.0722
  -4.000  -0.1053   0.02918   0.02108  -0.0825   0.7512   0.0785
  -3.750  -0.0816   0.02863   0.02059  -0.0819   0.7501   0.0873
  -3.500  -0.1066   0.03001   0.02197  -0.0746   0.7444   0.0885
  -3.250  -0.1277   0.03097   0.02290  -0.0673   0.7409   0.0894
  -3.000  -0.1110   0.03075   0.02270  -0.0657   0.7386   0.0983
  -2.750  -0.0795   0.03027   0.02225  -0.0662   0.7369   0.1150
  -2.500  -0.0476   0.02981   0.02189  -0.0668   0.7357   0.1418
  -2.250  -0.0178   0.02896   0.02151  -0.0670   0.7348   0.2345
  -0.500   0.1751   0.03099   0.02544  -0.0652   0.7196   0.9596
  -0.250   0.3210   0.03155   0.02579  -0.0875   0.7201   0.9780
   0.000   0.4397   0.03137   0.02547  -0.1052   0.7204   0.9910
   0.250   0.5103   0.03111   0.02512  -0.1137   0.7200   0.9985
   0.500   0.4421   0.03388   0.02799  -0.1011   0.7083   1.0000
   0.750   0.4744   0.03380   0.02784  -0.1020   0.7070   1.0000
   1.000   0.5052   0.03373   0.02771  -0.1024   0.7061   1.0000
   1.250   0.5367   0.03366   0.02760  -0.1029   0.7053   1.0000
   1.500   0.4417   0.03582   0.02980  -0.0847   0.6925   1.0000
   1.750   0.4565   0.03616   0.03011  -0.0829   0.6898   1.0000
   2.000   0.5145   0.03574   0.02965  -0.0874   0.6908   1.0000
   2.250   0.4426   0.03698   0.03090  -0.0727   0.6783   1.0000
   2.500   0.3983   0.03808   0.03199  -0.0625   0.6686   1.0000
   2.750   0.4184   0.03813   0.03202  -0.0613   0.6660   1.0000
   3.000   0.4480   0.03806   0.03191  -0.0614   0.6645   1.0000
   3.250   0.4816   0.03793   0.03176  -0.0620   0.6634   1.0000
   3.500   0.4615   0.03919   0.03301  -0.0565   0.6525   1.0000
   3.750   0.4917   0.03922   0.03304  -0.0569   0.6509   1.0000
   4.000   0.4964   0.04022   0.03404  -0.0548   0.6435   1.0000
   4.250   0.5184   0.04055   0.03437  -0.0545   0.6394   1.0000
   4.500   0.5485   0.04061   0.03445  -0.0549   0.6375   1.0000
   4.750   0.5811   0.04057   0.03443  -0.0556   0.6362   1.0000
   5.000   0.6158   0.04041   0.03430  -0.0564   0.6353   1.0000
   5.250   0.6096   0.04207   0.03598  -0.0538   0.6242   1.0000
   5.500   0.6430   0.04190   0.03587  -0.0545   0.6227   1.0000
   5.750   0.6777   0.04167   0.03568  -0.0553   0.6217   1.0000
   6.000   0.6752   0.04333   0.03738  -0.0531   0.6108   1.0000
   6.250   0.7077   0.04315   0.03726  -0.0537   0.6092   1.0000
   6.500   0.7137   0.04453   0.03869  -0.0524   0.6004   1.0000
   6.750   0.7402   0.04469   0.03894  -0.0526   0.5973   1.0000
   7.000   0.7740   0.04433   0.03867  -0.0531   0.5956   1.0000
   7.250   0.8072   0.04404   0.03848  -0.0538   0.5943   1.0000
   7.500   0.8453   0.04312   0.03770  -0.0545   0.5929   1.0000
   8.000   0.9818   0.03205   0.02696  -0.0570   0.5811   1.0000
   8.250   1.0529   0.02278   0.01654  -0.0543   0.3889   1.0000
   8.500   1.0294   0.02584   0.01911  -0.0497   0.3146   1.0000
   8.750   0.9992   0.02961   0.02225  -0.0448   0.2197   1.0000
   9.000   0.9682   0.03365   0.02552  -0.0404   0.1082   1.0000
   9.250   0.9514   0.03708   0.02848  -0.0371   0.0492   1.0000
   9.500   0.9562   0.03896   0.03040  -0.0356   0.0413   1.0000
   9.750   0.9617   0.04084   0.03234  -0.0343   0.0379   1.0000
  10.000   0.9612   0.04328   0.03487  -0.0326   0.0351   1.0000
  10.250   0.9667   0.04523   0.03691  -0.0312   0.0329   1.0000
  10.500   0.9743   0.04696   0.03870  -0.0301   0.0317   1.0000
  10.750   0.9824   0.04864   0.04043  -0.0289   0.0306   1.0000
  11.000   0.9883   0.05040   0.04212  -0.0274   0.0274   1.0000
  11.250   1.0030   0.05120   0.04289  -0.0252   0.0263   1.0000
  11.500   1.0238   0.05173   0.04346  -0.0241   0.0260   1.0000
  11.750   1.0488   0.05210   0.04392  -0.0229   0.0255   1.0000
  12.000   1.0858   0.05214   0.04406  -0.0217   0.0253   1.0000
  12.250   1.1299   0.05281   0.04488  -0.0212   0.0252   1.0000
  12.500   1.1737   0.05458   0.04689  -0.0211   0.0254   1.0000
  12.750   1.1791   0.05636   0.04890  -0.0198   0.0239   1.0000
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