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GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il)
Reynolds number: 100,000
Max Cl/Cd: 58.78 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe167-il-100000-n5.txt
Download as CSV file: xf-goe167-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 167 (V.KARMAN PROP.2) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3378   0.09517   0.09067  -0.0245   1.0000   0.0495
  -7.750  -0.3366   0.09220   0.08777  -0.0265   1.0000   0.0512
  -7.500  -0.3358   0.08925   0.08491  -0.0320   1.0000   0.0533
  -7.250  -0.3298   0.08584   0.08151  -0.0410   1.0000   0.0543
  -7.000  -0.3131   0.08155   0.07712  -0.0492   0.9898   0.0546
  -6.750  -0.3016   0.07633   0.07205  -0.0451   0.9761   0.0566
  -6.500  -0.2797   0.07273   0.06841  -0.0473   0.9544   0.0600
  -6.250  -0.2545   0.06831   0.06387  -0.0537   0.9270   0.0638
  -6.000  -0.2159   0.06326   0.05824  -0.0677   0.8949   0.0681
  -5.750  -0.2028   0.05871   0.05381  -0.0664   0.8669   0.0696
  -5.500  -0.1864   0.05615   0.05117  -0.0657   0.8387   0.0735
  -5.250  -0.1542   0.05252   0.04690  -0.0720   0.8145   0.0823
  -5.000  -0.1371   0.04911   0.04344  -0.0717   0.7915   0.0838
  -4.500  -0.0831   0.04138   0.03490  -0.0747   0.7533   0.0638
  -4.000  -0.0221   0.03451   0.02683  -0.0771   0.7215   0.0534
  -3.750   0.0050   0.03215   0.02412  -0.0777   0.7075   0.0526
  -3.500   0.0332   0.03007   0.02164  -0.0781   0.6951   0.0520
  -3.250   0.0626   0.02843   0.01952  -0.0785   0.6834   0.0531
  -3.000   0.0918   0.02706   0.01772  -0.0787   0.6729   0.0539
  -2.750   0.1203   0.02557   0.01587  -0.0789   0.6639   0.0536
  -2.500   0.1493   0.02429   0.01428  -0.0792   0.6545   0.0533
  -2.250   0.1781   0.02320   0.01287  -0.0792   0.6472   0.0532
  -2.000   0.2071   0.02224   0.01167  -0.0794   0.6396   0.0533
  -1.750   0.2356   0.02144   0.01061  -0.0793   0.6335   0.0536
  -1.500   0.2643   0.02072   0.00974  -0.0794   0.6265   0.0540
  -1.250   0.2924   0.02004   0.00893  -0.0794   0.6207   0.0557
  -1.000   0.3204   0.01951   0.00839  -0.0796   0.6149   0.0585
  -0.750   0.3484   0.01906   0.00791  -0.0796   0.6093   0.0601
  -0.500   0.3762   0.01867   0.00745  -0.0795   0.6049   0.0611
  -0.250   0.4042   0.01836   0.00710  -0.0796   0.6002   0.0625
   0.000   0.4324   0.01814   0.00681  -0.0797   0.5953   0.0643
   0.250   0.4605   0.01801   0.00656  -0.0797   0.5910   0.0667
   0.500   0.4888   0.01791   0.00639  -0.0798   0.5870   0.0706
   0.750   0.5175   0.01787   0.00633  -0.0800   0.5824   0.0783
   1.000   0.5464   0.01777   0.00629  -0.0803   0.5786   0.1103
   1.250   0.5699   0.01560   0.00623  -0.0793   0.5754   1.0000
   1.500   0.5983   0.01585   0.00629  -0.0794   0.5720   1.0000
   1.750   0.6267   0.01608   0.00644  -0.0796   0.5675   1.0000
   2.000   0.6548   0.01632   0.00658  -0.0798   0.5629   1.0000
   2.250   0.6828   0.01656   0.00669  -0.0798   0.5589   1.0000
   2.500   0.7107   0.01681   0.00692  -0.0800   0.5538   1.0000
   2.750   0.7386   0.01705   0.00714  -0.0802   0.5486   1.0000
   3.000   0.7664   0.01729   0.00729  -0.0802   0.5442   1.0000
   3.250   0.7940   0.01756   0.00758  -0.0803   0.5392   1.0000
   3.500   0.8216   0.01783   0.00789  -0.0805   0.5342   1.0000
   3.750   0.8493   0.01809   0.00813  -0.0805   0.5300   1.0000
   4.000   0.8768   0.01836   0.00842  -0.0806   0.5254   1.0000
   4.250   0.9039   0.01864   0.00880  -0.0807   0.5195   1.0000
   4.500   0.9312   0.01885   0.00900  -0.0806   0.5139   1.0000
   4.750   0.9577   0.01908   0.00931  -0.0806   0.5060   1.0000
   5.000   0.9845   0.01916   0.00938  -0.0803   0.4974   1.0000
   5.250   1.0103   0.01931   0.00966  -0.0801   0.4866   1.0000
   5.500   1.0365   0.01945   0.00986  -0.0798   0.4769   1.0000
   5.750   1.0628   0.01962   0.01012  -0.0796   0.4689   1.0000
   6.000   1.0889   0.01988   0.01056  -0.0795   0.4616   1.0000
   6.250   1.1149   0.02010   0.01089  -0.0793   0.4540   1.0000
   6.500   1.1404   0.02033   0.01130  -0.0791   0.4443   1.0000
   6.750   1.1657   0.02051   0.01163  -0.0788   0.4337   1.0000
   7.000   1.1909   0.02072   0.01200  -0.0784   0.4230   1.0000
   7.250   1.2155   0.02098   0.01246  -0.0781   0.4098   1.0000
   7.500   1.2387   0.02117   0.01278  -0.0774   0.3863   1.0000
   7.750   1.2596   0.02143   0.01300  -0.0764   0.3427   1.0000
   8.000   1.2757   0.02218   0.01341  -0.0749   0.2866   1.0000
   8.500   1.3010   0.02477   0.01562  -0.0716   0.2189   1.0000
   8.750   1.3119   0.02619   0.01696  -0.0698   0.1793   1.0000
   9.000   1.3068   0.02876   0.01896  -0.0666   0.0977   1.0000
   9.250   1.3073   0.03070   0.02084  -0.0637   0.0813   1.0000
   9.500   1.3058   0.03253   0.02269  -0.0606   0.0719   1.0000
   9.750   1.3038   0.03456   0.02479  -0.0578   0.0624   1.0000
  10.000   1.3045   0.03663   0.02698  -0.0559   0.0535   1.0000
  10.500   1.3051   0.04148   0.03211  -0.0534   0.0390   1.0000
  10.750   1.3048   0.04425   0.03500  -0.0527   0.0339   1.0000
  11.000   1.3037   0.04724   0.03806  -0.0523   0.0303   1.0000
  11.250   1.3018   0.05043   0.04135  -0.0520   0.0279   1.0000
  11.500   1.2995   0.05375   0.04477  -0.0520   0.0260   1.0000
  11.750   1.2954   0.05733   0.04842  -0.0521   0.0245   1.0000
  12.000   1.2901   0.06114   0.05235  -0.0522   0.0236   1.0000
  12.250   1.2850   0.06492   0.05629  -0.0523   0.0229   1.0000
  12.500   1.2799   0.06874   0.06026  -0.0525   0.0224   1.0000
  12.750   1.2749   0.07253   0.06419  -0.0526   0.0219   1.0000
  13.000   1.2704   0.07623   0.06803  -0.0527   0.0214   1.0000
  13.250   1.2671   0.07983   0.07175  -0.0528   0.0209   1.0000
  13.500   1.2652   0.08325   0.07529  -0.0528   0.0205   1.0000
  13.750   1.2643   0.08654   0.07868  -0.0528   0.0199   1.0000
  14.000   1.2641   0.08971   0.08193  -0.0527   0.0193   1.0000
  14.250   1.2649   0.09267   0.08494  -0.0525   0.0186   1.0000
  14.500   1.2683   0.09509   0.08741  -0.0515   0.0179   1.0000
  14.750   1.2719   0.09787   0.09037  -0.0513   0.0174   1.0000
  15.000   1.2751   0.10077   0.09350  -0.0510   0.0171   1.0000
  15.250   1.2775   0.10388   0.09680  -0.0509   0.0168   1.0000
  15.500   1.2781   0.10742   0.10055  -0.0511   0.0166   1.0000
  15.750   1.2764   0.11148   0.10483  -0.0519   0.0164   1.0000
  16.000   1.2724   0.11606   0.10962  -0.0531   0.0163   1.0000
  16.250   1.2661   0.12122   0.11502  -0.0550   0.0162   1.0000
  16.500   1.2575   0.12703   0.12106  -0.0575   0.0161   1.0000
  16.750   1.2470   0.13348   0.12774  -0.0607   0.0161   1.0000
  17.000   1.2349   0.14059   0.13509  -0.0646   0.0161   1.0000
  17.250   1.2210   0.14852   0.14324  -0.0694   0.0162   1.0000
  17.500   1.2052   0.15744   0.15237  -0.0751   0.0163   1.0000
  17.750   1.1876   0.16763   0.16275  -0.0818   0.0164   1.0000
  18.000   1.1673   0.17967   0.17497  -0.0898   0.0167   1.0000
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