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GOE 342 AIRFOIL (goe342-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 342 AIRFOIL (goe342-il)
Reynolds number: 100,000
Max Cl/Cd: 71.31 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe342-il-100000.txt
Download as CSV file: xf-goe342-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 342 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3122   0.10124   0.09669  -0.0209   1.0000   0.0425
  -7.000  -0.3234   0.10050   0.09603  -0.0182   1.0000   0.0431
  -6.750  -0.3329   0.09967   0.09529  -0.0162   1.0000   0.0438
  -6.500  -0.3403   0.09882   0.09451  -0.0152   1.0000   0.0445
  -6.250  -0.3438   0.09815   0.09389  -0.0160   1.0000   0.0453
  -6.000  -0.3392   0.09789   0.09365  -0.0206   1.0000   0.0458
  -5.750  -0.3222   0.09728   0.09300  -0.0289   1.0000   0.0462
  -5.500  -0.3244   0.09256   0.08835  -0.0254   1.0000   0.0466
  -5.250  -0.3276   0.08857   0.08441  -0.0208   1.0000   0.0474
  -5.000  -0.3240   0.08558   0.08145  -0.0194   1.0000   0.0484
  -4.750  -0.3156   0.08287   0.07874  -0.0201   1.0000   0.0498
  -4.500  -0.3025   0.08016   0.07602  -0.0223   1.0000   0.0517
  -4.250  -0.2204   0.07784   0.07340  -0.0460   0.9965   0.0574
  -4.000  -0.2200   0.07250   0.06816  -0.0418   0.9943   0.0587
  -3.750  -0.2000   0.06899   0.06463  -0.0434   0.9911   0.0613
  -3.500  -0.1089   0.06726   0.06244  -0.0648   0.9867   0.0698
  -3.250  -0.1033   0.06173   0.05708  -0.0626   0.9845   0.0714
  -3.000  -0.0797   0.05871   0.05405  -0.0644   0.9813   0.0762
  -2.750  -0.0273   0.05560   0.05072  -0.0740   0.9774   0.0849
  -2.500   0.0045   0.05281   0.04790  -0.0774   0.9740   0.0914
  -2.250   0.0592   0.04964   0.04453  -0.0861   0.9707   0.1003
  -2.000   0.1072   0.04731   0.04195  -0.0928   0.9648   0.1119
  -1.750   0.1552   0.04451   0.03903  -0.0990   0.9588   0.1269
  -1.500   0.2008   0.04204   0.03647  -0.1042   0.9520   0.1444
  -1.250   0.2539   0.03981   0.03403  -0.1108   0.9445   0.1715
  -1.000   0.3000   0.03760   0.03175  -0.1156   0.9375   0.2025
  -0.250   0.4200   0.03104   0.02535  -0.1246   0.9159   0.4107
   0.000   0.4694   0.02893   0.02326  -0.1286   0.9122   0.4710
   0.250   0.5089   0.02796   0.02213  -0.1313   0.9043   0.4821
   0.500   0.6036   0.02762   0.01997  -0.1408   0.8992   0.1467
   0.750   0.6501   0.02638   0.01832  -0.1430   0.8936   0.1181
   1.000   0.6901   0.02544   0.01716  -0.1446   0.8860   0.1133
   1.250   0.7416   0.02416   0.01573  -0.1478   0.8819   0.1075
   1.500   0.7697   0.02363   0.01519  -0.1473   0.8714   0.1053
   1.750   0.8121   0.02258   0.01415  -0.1489   0.8655   0.1048
   2.000   0.8429   0.02199   0.01358  -0.1485   0.8550   0.1063
   2.250   0.8745   0.02140   0.01299  -0.1481   0.8444   0.1114
   2.500   0.9139   0.02040   0.01203  -0.1488   0.8365   0.1274
   2.750   0.9434   0.01981   0.01163  -0.1480   0.8236   0.1665
   3.000   0.9672   0.01825   0.01129  -0.1459   0.8104   1.0000
   3.250   0.9957   0.01789   0.01081  -0.1446   0.7957   1.0000
   3.500   1.0243   0.01745   0.01029  -0.1432   0.7793   1.0000
   3.750   1.0506   0.01707   0.00985  -0.1414   0.7583   1.0000
   4.000   1.0771   0.01666   0.00941  -0.1396   0.7336   1.0000
   4.250   1.1019   0.01639   0.00905  -0.1377   0.7027   1.0000
   4.500   1.1246   0.01627   0.00887  -0.1357   0.6624   1.0000
   4.750   1.1479   0.01626   0.00872  -0.1339   0.6186   1.0000
   5.000   1.1716   0.01643   0.00869  -0.1324   0.5795   1.0000
   5.250   1.1954   0.01685   0.00888  -0.1312   0.5477   1.0000
   5.500   1.2189   0.01743   0.00923  -0.1301   0.5212   1.0000
   5.750   1.2418   0.01807   0.00971  -0.1290   0.4960   1.0000
   6.000   1.2641   0.01873   0.01029  -0.1279   0.4714   1.0000
   6.250   1.2867   0.01940   0.01086  -0.1268   0.4503   1.0000
   6.500   1.3094   0.02005   0.01150  -0.1259   0.4315   1.0000
   6.750   1.3311   0.02067   0.01218  -0.1248   0.4116   1.0000
   7.000   1.3521   0.02133   0.01287  -0.1235   0.3909   1.0000
   7.250   1.3718   0.02198   0.01359  -0.1220   0.3683   1.0000
   7.500   1.3890   0.02266   0.01430  -0.1201   0.3401   1.0000
   7.750   1.4020   0.02339   0.01506  -0.1176   0.3006   1.0000
   8.000   1.4111   0.02431   0.01588  -0.1145   0.2424   1.0000
   8.250   1.4197   0.02569   0.01692  -0.1115   0.1924   1.0000
   8.500   1.4285   0.02735   0.01828  -0.1089   0.1611   1.0000
   8.750   1.4359   0.02927   0.01993  -0.1061   0.1407   1.0000
   9.000   1.4455   0.03119   0.02181  -0.1036   0.1241   1.0000
   9.250   1.4551   0.03327   0.02387  -0.1011   0.1081   1.0000
   9.500   1.4645   0.03548   0.02607  -0.0986   0.0922   1.0000
   9.750   1.4759   0.03777   0.02841  -0.0963   0.0791   1.0000
  10.000   1.4885   0.03998   0.03064  -0.0943   0.0698   1.0000
  10.250   1.5036   0.04209   0.03272  -0.0927   0.0631   1.0000
  10.500   1.5265   0.04534   0.03623  -0.0919   0.0583   1.0000
  10.750   1.5391   0.04767   0.03881  -0.0899   0.0545   1.0000
  11.000   1.5584   0.05124   0.04233  -0.0896   0.0505   1.0000
  11.250   1.5632   0.05443   0.04600  -0.0868   0.0492   1.0000
  11.500   1.5631   0.05768   0.04969  -0.0835   0.0484   1.0000
  11.750   1.5572   0.06105   0.05347  -0.0797   0.0478   1.0000
  12.000   1.5471   0.06460   0.05739  -0.0760   0.0475   1.0000
  12.250   1.5332   0.06838   0.06153  -0.0726   0.0474   1.0000
  12.500   1.5166   0.07241   0.06589  -0.0697   0.0473   1.0000
  12.750   1.4975   0.07678   0.07057  -0.0675   0.0473   1.0000
  13.000   1.4766   0.08155   0.07563  -0.0660   0.0474   1.0000
  13.250   1.4540   0.08679   0.08114  -0.0655   0.0476   1.0000
  13.500   1.4301   0.09257   0.08717  -0.0659   0.0478   1.0000
  13.750   1.4054   0.09890   0.09372  -0.0673   0.0481   1.0000
  14.000   1.3807   0.10583   0.10085  -0.0697   0.0486   1.0000
  14.250   1.3559   0.11343   0.10862  -0.0733   0.0490   1.0000
  14.500   1.3327   0.12162   0.11696  -0.0777   0.0495   1.0000
  14.750   1.3121   0.13027   0.12568  -0.0825   0.0500   1.0000
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