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FX 67-K-170/17 AIRFOIL (fx67k170-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 67-K-170/17 AIRFOIL (fx67k170-il)
Reynolds number: 100,000
Max Cl/Cd: 19.85 at α=12.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx67k170-il-100000-n5.txt
Download as CSV file: xf-fx67k170-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 67-K-170/17 AIRFOIL                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.0869   0.11509   0.10938  -0.1045   0.7945   0.0527
 -11.500  -0.0967   0.11211   0.10648  -0.1085   0.7922   0.0540
 -11.250  -0.1011   0.10869   0.10310  -0.1114   0.7899   0.0543
 -11.000  -0.0914   0.10419   0.09861  -0.1111   0.7883   0.0553
 -10.750  -0.0832   0.10096   0.09537  -0.1114   0.7866   0.0559
 -10.500  -0.0832   0.09322   0.08757  -0.1137   0.7853   0.0315
 -10.250  -0.0790   0.09026   0.08461  -0.1143   0.7838   0.0306
 -10.000  -0.0784   0.08666   0.08107  -0.1160   0.7813   0.0296
  -9.750  -0.0814   0.08247   0.07694  -0.1182   0.7786   0.0287
  -9.500  -0.0880   0.07755   0.07206  -0.1212   0.7760   0.0277
  -9.000  -0.1506   0.06289   0.05710  -0.1297   0.7707   0.0245
  -8.750  -0.1656   0.06072   0.05488  -0.1282   0.7677   0.0244
  -8.500  -0.1763   0.05860   0.05267  -0.1266   0.7642   0.0242
  -8.250  -0.1850   0.05613   0.05004  -0.1248   0.7611   0.0241
  -8.000  -0.1902   0.05358   0.04727  -0.1228   0.7585   0.0240
  -7.750  -0.1916   0.05100   0.04442  -0.1208   0.7565   0.0239
  -7.500  -0.1919   0.04872   0.04186  -0.1187   0.7535   0.0238
  -7.250  -0.1912   0.04679   0.03967  -0.1165   0.7496   0.0238
  -7.000  -0.1860   0.04464   0.03716  -0.1143   0.7466   0.0239
  -6.750  -0.1765   0.04244   0.03454  -0.1123   0.7443   0.0241
  -6.500  -0.1637   0.04029   0.03192  -0.1105   0.7425   0.0249
  -6.250  -0.1462   0.03872   0.03022  -0.1098   0.7411   0.0263
  -6.000  -0.1417   0.03858   0.03002  -0.1074   0.7353   0.0274
  -5.750  -0.1267   0.03750   0.02866  -0.1059   0.7325   0.0288
  -5.500  -0.1069   0.03604   0.02688  -0.1047   0.7304   0.0296
  -5.250  -0.0836   0.03461   0.02514  -0.1038   0.7289   0.0308
  -5.000  -0.0586   0.03350   0.02372  -0.1031   0.7275   0.0323
  -4.750  -0.0564   0.03348   0.02380  -0.1002   0.7217   0.0343
  -4.500  -0.0419   0.03318   0.02347  -0.0986   0.7184   0.0370
  -4.250  -0.0214   0.03256   0.02273  -0.0975   0.7164   0.0397
  -4.000   0.0010   0.03185   0.02191  -0.0967   0.7148   0.0435
  -3.750   0.0238   0.03107   0.02111  -0.0960   0.7135   0.0469
  -3.500   0.0155   0.03203   0.02208  -0.0915   0.7061   0.0483
  -3.250   0.0311   0.03198   0.02192  -0.0900   0.7033   0.0530
  -3.000   0.0517   0.03158   0.02147  -0.0890   0.7015   0.0580
  -2.750   0.0762   0.03119   0.02095  -0.0886   0.7001   0.0655
  -2.500   0.0718   0.03201   0.02178  -0.0845   0.6937   0.0710
  -2.250   0.0795   0.03216   0.02203  -0.0820   0.6898   0.0935
  -2.000   0.0934   0.03094   0.02191  -0.0807   0.6878   0.3277
  -1.750   0.1042   0.02997   0.02223  -0.0772   0.6863   0.6234
  -1.500   0.1155   0.03026   0.02283  -0.0722   0.6850   0.7735
  -1.250   0.0947   0.03191   0.02453  -0.0656   0.6764   0.8018
  -1.000   0.0961   0.03238   0.02505  -0.0592   0.6740   0.8593
  -0.750   0.1078   0.03253   0.02514  -0.0548   0.6723   0.8971
  -0.500   0.1358   0.03265   0.02511  -0.0540   0.6712   0.9221
  -0.250   0.1385   0.03397   0.02640  -0.0520   0.6641   0.9387
   0.000   0.1714   0.03450   0.02676  -0.0540   0.6618   0.9487
   0.250   0.2071   0.03489   0.02699  -0.0563   0.6601   0.9572
   0.500   0.2467   0.03518   0.02711  -0.0592   0.6587   0.9641
   0.750   0.2862   0.03539   0.02719  -0.0620   0.6575   0.9705
   1.000   0.3273   0.03559   0.02725  -0.0651   0.6566   0.9757
   1.250   0.3346   0.03759   0.02925  -0.0657   0.6484   0.9886
   1.500   0.3648   0.03798   0.02954  -0.0672   0.6463   1.0000
   1.750   0.3795   0.03794   0.02941  -0.0654   0.6443   1.0000
   2.000   0.4000   0.03795   0.02932  -0.0646   0.6429   1.0000
   2.250   0.3815   0.03959   0.03095  -0.0599   0.6341   1.0000
   2.500   0.4042   0.03989   0.03116  -0.0598   0.6318   1.0000
   2.750   0.4301   0.04012   0.03132  -0.0601   0.6301   1.0000
   3.000   0.4586   0.04026   0.03139  -0.0606   0.6289   1.0000
   3.250   0.4514   0.04208   0.03320  -0.0579   0.6199   1.0000
   3.500   0.4765   0.04243   0.03350  -0.0581   0.6176   1.0000
   3.750   0.5046   0.04262   0.03364  -0.0586   0.6159   1.0000
   4.000   0.5347   0.04272   0.03371  -0.0592   0.6146   1.0000
   4.250   0.5289   0.04465   0.03564  -0.0568   0.6051   1.0000
   4.500   0.5556   0.04490   0.03587  -0.0572   0.6029   1.0000
   4.750   0.5850   0.04501   0.03596  -0.0577   0.6013   1.0000
   5.250   0.6092   0.04708   0.03806  -0.0560   0.5896   1.0000
   5.500   0.6381   0.04717   0.03815  -0.0565   0.5878   1.0000
   5.750   0.6687   0.04717   0.03816  -0.0571   0.5864   1.0000
   6.000   0.6642   0.04921   0.04025  -0.0549   0.5760   1.0000
   6.250   0.6924   0.04930   0.04037  -0.0553   0.5739   1.0000
   6.500   0.7231   0.04921   0.04031  -0.0558   0.5724   1.0000
   6.750   0.7201   0.05124   0.04238  -0.0539   0.5619   1.0000
   7.000   0.7490   0.05121   0.04242  -0.0543   0.5597   1.0000
   7.250   0.7793   0.05106   0.04233  -0.0547   0.5581   1.0000
   7.500   0.7776   0.05305   0.04438  -0.0530   0.5472   1.0000
   7.750   0.8067   0.05292   0.04434  -0.0533   0.5450   1.0000
   8.250   0.8361   0.05465   0.04622  -0.0521   0.5320   1.0000
   8.500   0.8669   0.05428   0.04593  -0.0524   0.5300   1.0000
   8.750   0.8675   0.05621   0.04795  -0.0510   0.5189   1.0000
   9.000   0.8976   0.05580   0.04766  -0.0512   0.5165   1.0000
   9.500   0.9345   0.05642   0.04849  -0.0501   0.5024   1.0000
  10.000   0.9781   0.05595   0.04826  -0.0490   0.4874   1.0000
  10.500   0.9978   0.05814   0.05067  -0.0471   0.4653   1.0000
  10.750   1.0246   0.05752   0.05019  -0.0468   0.4598   1.0000
  11.250   1.0523   0.05911   0.05206  -0.0455   0.4379   1.0000
  11.500   1.0779   0.05853   0.05160  -0.0450   0.4277   1.0000
  11.750   1.0999   0.05836   0.05154  -0.0445   0.4147   1.0000
  12.000   1.1140   0.05913   0.05240  -0.0438   0.3967   1.0000
  12.250   1.1410   0.05818   0.05143  -0.0431   0.3714   1.0000
  12.500   1.1592   0.05839   0.05158  -0.0424   0.3437   1.0000
  12.750   1.1725   0.05921   0.05233  -0.0415   0.3149   1.0000
  13.000   1.1803   0.06066   0.05366  -0.0405   0.2835   1.0000
  13.250   1.1829   0.06281   0.05568  -0.0395   0.2515   1.0000
  13.500   1.1823   0.06541   0.05813  -0.0386   0.2194   1.0000
  13.750   1.1787   0.06846   0.06102  -0.0377   0.1872   1.0000
  14.000   1.1739   0.07176   0.06419  -0.0371   0.1562   1.0000
  14.250   1.1688   0.07523   0.06750  -0.0365   0.1273   1.0000
  14.500   1.1642   0.07873   0.07087  -0.0361   0.1048   1.0000
  14.750   1.1622   0.08199   0.07407  -0.0359   0.0899   1.0000
  15.250   1.1612   0.08836   0.08042  -0.0357   0.0700   1.0000
  15.500   1.1619   0.09147   0.08355  -0.0359   0.0617   1.0000
  15.750   1.1609   0.09485   0.08691  -0.0362   0.0543   1.0000
  16.000   1.1611   0.09812   0.09022  -0.0366   0.0467   1.0000
  16.250   1.1626   0.10127   0.09346  -0.0371   0.0413   1.0000
  16.500   1.1615   0.10482   0.09706  -0.0377   0.0370   1.0000
  16.750   1.1618   0.10821   0.10060  -0.0383   0.0333   1.0000
  17.000   1.1616   0.11171   0.10422  -0.0390   0.0296   1.0000
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