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GOE 298 AIRFOIL (goe298-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 298 AIRFOIL (goe298-il)
Reynolds number: 100,000
Max Cl/Cd: 52.84 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe298-il-100000.txt
Download as CSV file: xf-goe298-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 298 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2534   0.09828   0.09333  -0.0284   1.0000   0.1303
  -7.500  -0.2766   0.09857   0.09377  -0.0238   1.0000   0.1313
  -7.250  -0.3060   0.09934   0.09466  -0.0185   1.0000   0.1319
  -7.000  -0.3042   0.09483   0.09009  -0.0427   0.9808   0.1383
  -6.750  -0.2739   0.09035   0.08565  -0.0382   0.9779   0.1396
  -6.500  -0.2424   0.08677   0.08206  -0.0388   0.9724   0.1424
  -6.250  -0.2108   0.08285   0.07811  -0.0466   0.9650   0.1493
  -6.000  -0.1858   0.07748   0.07267  -0.0594   0.9541   0.1553
  -5.750  -0.1553   0.07444   0.06964  -0.0598   0.9475   0.1591
  -5.500  -0.1238   0.06945   0.06444  -0.0767   0.9361   0.1709
  -5.250  -0.1027   0.06678   0.06185  -0.0737   0.9266   0.1734
  -5.000  -0.0722   0.06416   0.05920  -0.0761   0.9195   0.1814
  -4.750  -0.0526   0.06073   0.05565  -0.0822   0.9063   0.1906
  -4.500  -0.0295   0.05859   0.05352  -0.0818   0.8978   0.1960
  -4.000   0.0106   0.05410   0.04892  -0.0852   0.8753   0.2152
  -3.750   0.0349   0.05158   0.04626  -0.0883   0.8659   0.2295
  -3.500   0.0575   0.05001   0.04452  -0.0909   0.8534   0.2465
  -3.250   0.0763   0.04780   0.04238  -0.0883   0.8456   0.2520
  -3.000   0.0962   0.04619   0.04070  -0.0889   0.8329   0.2696
  -2.750   0.1203   0.04441   0.03882  -0.0891   0.8259   0.2888
  -2.500   0.1408   0.04310   0.03749  -0.0892   0.8146   0.3083
  -2.250   0.2126   0.03383   0.02640  -0.1037   0.8088   0.1863
  -2.000   0.2395   0.03218   0.02456  -0.1041   0.7998   0.1856
  -1.750   0.2680   0.03057   0.02272  -0.1043   0.7920   0.1847
  -1.500   0.2983   0.02938   0.02118  -0.1042   0.7862   0.1862
  -1.250   0.3259   0.02867   0.02024  -0.1044   0.7765   0.1875
  -1.000   0.3541   0.02728   0.01874  -0.1042   0.7700   0.1900
  -0.750   0.3807   0.02673   0.01821  -0.1039   0.7620   0.1938
  -0.500   0.4087   0.02616   0.01754  -0.1037   0.7541   0.1970
  -0.250   0.4384   0.02544   0.01660  -0.1030   0.7482   0.2005
   0.000   0.4651   0.02522   0.01626  -0.1027   0.7377   0.2043
   0.250   0.4940   0.02454   0.01546  -0.1022   0.7308   0.2075
   0.500   0.5211   0.02416   0.01513  -0.1018   0.7233   0.2121
   0.750   0.5483   0.02392   0.01488  -0.1013   0.7145   0.2175
   1.000   0.5778   0.02344   0.01428  -0.1005   0.7081   0.2226
   1.250   0.6034   0.02331   0.01423  -0.1000   0.6975   0.2274
   1.500   0.6317   0.02283   0.01379  -0.0992   0.6899   0.2351
   1.750   0.6580   0.02276   0.01375  -0.0986   0.6799   0.2428
   2.000   0.6853   0.02227   0.01334  -0.0976   0.6708   0.2514
   2.250   0.7112   0.02210   0.01323  -0.0966   0.6597   0.2644
   2.500   0.7393   0.02158   0.01276  -0.0956   0.6497   0.2844
   2.750   0.7654   0.02124   0.01268  -0.0948   0.6364   0.3231
   3.000   0.7868   0.01922   0.01209  -0.0918   0.6264   1.0000
   3.250   0.8142   0.01912   0.01177  -0.0908   0.6117   1.0000
   3.500   0.8410   0.01907   0.01157  -0.0898   0.5953   1.0000
   3.750   0.8679   0.01900   0.01134  -0.0888   0.5779   1.0000
   4.000   0.8948   0.01896   0.01113  -0.0878   0.5589   1.0000
   4.250   0.9213   0.01897   0.01094  -0.0868   0.5384   1.0000
   4.500   0.9472   0.01908   0.01084  -0.0858   0.5173   1.0000
   4.750   0.9726   0.01928   0.01088  -0.0849   0.4968   1.0000
   5.000   0.9977   0.01955   0.01103  -0.0841   0.4776   1.0000
   5.250   1.0226   0.01987   0.01126  -0.0834   0.4600   1.0000
   5.500   1.0474   0.02019   0.01153  -0.0826   0.4435   1.0000
   5.750   1.0721   0.02052   0.01179  -0.0819   0.4282   1.0000
   6.000   1.0968   0.02087   0.01204  -0.0812   0.4140   1.0000
   6.250   1.1213   0.02124   0.01229  -0.0805   0.4007   1.0000
   6.500   1.1456   0.02168   0.01260  -0.0797   0.3875   1.0000
   6.750   1.1691   0.02226   0.01311  -0.0790   0.3742   1.0000
   7.000   1.1928   0.02292   0.01366  -0.0782   0.3615   1.0000
   7.250   1.2170   0.02369   0.01423  -0.0776   0.3491   1.0000
   7.500   1.2401   0.02450   0.01495  -0.0769   0.3360   1.0000
   7.750   1.2623   0.02544   0.01587  -0.0760   0.3229   1.0000
   8.000   1.2858   0.02648   0.01678  -0.0755   0.3107   1.0000
   8.250   1.3092   0.02748   0.01767  -0.0748   0.2985   1.0000
   8.500   1.3287   0.02856   0.01885  -0.0737   0.2865   1.0000
   8.750   1.3534   0.02968   0.01978  -0.0733   0.2763   1.0000
   9.000   1.3710   0.03063   0.02088  -0.0720   0.2660   1.0000
   9.250   1.3947   0.03171   0.02184  -0.0715   0.2580   1.0000
   9.500   1.4112   0.03274   0.02308  -0.0700   0.2499   1.0000
   9.750   1.4364   0.03369   0.02389  -0.0697   0.2439   1.0000
  10.000   1.4534   0.03501   0.02539  -0.0685   0.2382   1.0000
  10.250   1.4708   0.03617   0.02670  -0.0672   0.2328   1.0000
  10.500   1.4943   0.03713   0.02759  -0.0667   0.2283   1.0000
  10.750   1.5154   0.03849   0.02898  -0.0661   0.2243   1.0000
  11.000   1.5263   0.03999   0.03077  -0.0642   0.2201   1.0000
  11.250   1.5412   0.04128   0.03221  -0.0629   0.2163   1.0000
  11.500   1.5622   0.04228   0.03320  -0.0621   0.2128   1.0000
  11.750   1.5860   0.04355   0.03439  -0.0619   0.2093   1.0000
  12.000   1.5869   0.04542   0.03663  -0.0591   0.2062   1.0000
  12.250   1.5916   0.04705   0.03848  -0.0569   0.2027   1.0000
  12.500   1.6033   0.04812   0.03961  -0.0552   0.1991   1.0000
  12.750   1.6390   0.04847   0.03970  -0.0561   0.1949   1.0000
  13.000   1.6286   0.05075   0.04234  -0.0525   0.1927   1.0000
  13.250   1.6138   0.05318   0.04507  -0.0486   0.1907   1.0000
  13.500   1.6021   0.05579   0.04792  -0.0457   0.1886   1.0000
  13.750   1.5942   0.05834   0.05065  -0.0435   0.1863   1.0000
  14.000   1.6045   0.05957   0.05191  -0.0424   0.1833   1.0000
  14.250   1.6398   0.05960   0.05176  -0.0425   0.1794   1.0000
  14.500   1.6029   0.06428   0.05682  -0.0398   0.1784   1.0000
  14.750   1.5560   0.07078   0.06369  -0.0385   0.1776   1.0000
  15.000   1.4787   0.08208   0.07541  -0.0398   0.1781   1.0000
  15.750   1.5524   0.08114   0.07433  -0.0368   0.1659   1.0000
  16.000   0.7084   0.18155   0.17614  -0.0750   0.2169   1.0000
  16.250   0.7333   0.18442   0.17903  -0.0739   0.2114   1.0000
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