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GOE 342 AIRFOIL (goe342-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 342 AIRFOIL (goe342-il)
Reynolds number: 500,000
Max Cl/Cd: 109.52 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe342-il-500000.txt
Download as CSV file: xf-goe342-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.1856   0.08755   0.08548  -0.0433   0.9909   0.0161
  -8.250  -0.1713   0.08327   0.08119  -0.0449   0.9885   0.0164
  -7.750  -0.2616   0.09475   0.09260  -0.0387   0.9917   0.0160
  -7.500  -0.2453   0.09046   0.08830  -0.0396   0.9895   0.0163
  -7.250  -0.2232   0.08687   0.08470  -0.0440   0.9859   0.0168
  -7.000  -0.1972   0.08307   0.08089  -0.0501   0.9829   0.0174
  -6.750  -0.1737   0.07943   0.07725  -0.0556   0.9753   0.0181
  -6.500  -0.1439   0.07548   0.07327  -0.0630   0.9692   0.0192
  -6.250  -0.1046   0.07156   0.06930  -0.0757   0.9571   0.0196
  -6.000  -0.0707   0.06749   0.06516  -0.0851   0.9446   0.0196
  -5.750  -0.0587   0.06350   0.06115  -0.0851   0.9338   0.0199
  -5.500  -0.0465   0.06080   0.05841  -0.0843   0.9234   0.0202
  -5.250  -0.0259   0.05811   0.05566  -0.0866   0.9121   0.0206
  -5.000  -0.0003   0.05520   0.05269  -0.0905   0.9006   0.0213
  -4.750   0.0293   0.05209   0.04951  -0.0954   0.8907   0.0224
  -4.500   0.0881   0.04813   0.04532  -0.1078   0.8822   0.0240
  -4.250   0.1297   0.04451   0.04152  -0.1143   0.8733   0.0241
  -4.000   0.1471   0.04063   0.03760  -0.1156   0.8658   0.0246
  -3.750   0.1713   0.03839   0.03532  -0.1171   0.8576   0.0250
  -3.500   0.2007   0.03614   0.03295  -0.1197   0.8512   0.0258
  -3.250   0.2341   0.03372   0.03043  -0.1229   0.8441   0.0270
  -3.000   0.2833   0.03132   0.02770  -0.1276   0.8386   0.0296
  -2.750   0.3206   0.02888   0.02501  -0.1303   0.8326   0.0298
  -2.500   0.3488   0.02518   0.02122  -0.1330   0.8263   0.0306
  -2.250   0.3766   0.02370   0.01965  -0.1341   0.8208   0.0313
  -2.000   0.4067   0.02223   0.01808  -0.1354   0.8145   0.0324
  -1.750   0.4384   0.02072   0.01638  -0.1366   0.8089   0.0340
  -1.500   0.4741   0.02021   0.01549  -0.1368   0.8020   0.0370
  -1.250   0.5057   0.01721   0.01225  -0.1386   0.7943   0.0382
  -1.000   0.5341   0.01616   0.01115  -0.1392   0.7864   0.0393
  -0.750   0.5633   0.01532   0.01019  -0.1397   0.7801   0.0413
  -0.500   0.5933   0.01556   0.01017  -0.1393   0.7746   0.0460
  -0.250   0.6241   0.01348   0.00796  -0.1406   0.7689   0.0489
   0.000   0.6527   0.01295   0.00734  -0.1408   0.7634   0.0522
   0.250   0.6820   0.01234   0.00660  -0.1411   0.7576   0.0603
   0.500   0.7102   0.01210   0.00632  -0.1412   0.7511   0.0674
   0.750   0.7385   0.01160   0.00577  -0.1415   0.7444   0.0782
   1.500   0.8260   0.00975   0.00346  -0.1406   0.7171   0.0486
   1.750   0.8539   0.00972   0.00343  -0.1403   0.7070   0.0466
   2.000   0.8817   0.00946   0.00316  -0.1402   0.6954   0.0459
   2.250   0.9095   0.00921   0.00290  -0.1401   0.6806   0.0468
   2.500   0.9368   0.00911   0.00278  -0.1398   0.6599   0.0461
   2.750   0.9635   0.00902   0.00262  -0.1395   0.6235   0.0459
   3.000   0.9858   0.00946   0.00262  -0.1384   0.5311   0.0462
   3.250   1.0083   0.01004   0.00281  -0.1375   0.4593   0.0478
   3.500   1.0325   0.01047   0.00301  -0.1369   0.4166   0.0510
   4.000   1.0810   0.00987   0.00370  -0.1362   0.3727   0.8693
   4.750   1.1563   0.01058   0.00426  -0.1345   0.3360   1.0000
   5.000   1.1816   0.01088   0.00452  -0.1341   0.3275   1.0000
   5.250   1.2077   0.01109   0.00475  -0.1338   0.3195   1.0000
   5.500   1.2330   0.01136   0.00500  -0.1334   0.3102   1.0000
   5.750   1.2582   0.01164   0.00527  -0.1330   0.2987   1.0000
   6.000   1.2836   0.01188   0.00550  -0.1326   0.2855   1.0000
   6.250   1.3083   0.01218   0.00576  -0.1321   0.2680   1.0000
   6.500   1.3325   0.01254   0.00602  -0.1316   0.2396   1.0000
   6.750   1.3513   0.01348   0.00656  -0.1303   0.1644   1.0000
   7.000   1.3693   0.01454   0.00733  -0.1289   0.1225   1.0000
   7.250   1.3904   0.01522   0.00794  -0.1279   0.1062   1.0000
   7.500   1.4124   0.01576   0.00847  -0.1271   0.0942   1.0000
   7.750   1.4343   0.01631   0.00898  -0.1262   0.0833   1.0000
   8.000   1.4558   0.01686   0.00951  -0.1252   0.0724   1.0000
   8.250   1.4766   0.01747   0.01007  -0.1242   0.0619   1.0000
   8.500   1.4969   0.01809   0.01066  -0.1231   0.0518   1.0000
   8.750   1.5158   0.01885   0.01137  -0.1218   0.0375   1.0000
   9.000   1.5320   0.01985   0.01229  -0.1200   0.0264   1.0000
   9.250   1.5485   0.02076   0.01325  -0.1183   0.0224   1.0000
   9.500   1.5642   0.02167   0.01419  -0.1164   0.0200   1.0000
   9.750   1.5757   0.02289   0.01549  -0.1139   0.0182   1.0000
  10.000   1.5892   0.02379   0.01649  -0.1117   0.0173   1.0000
  10.250   1.5989   0.02477   0.01757  -0.1089   0.0165   1.0000
  10.500   1.6069   0.02587   0.01878  -0.1059   0.0157   1.0000
  10.750   1.6128   0.02717   0.02017  -0.1029   0.0151   1.0000
  11.000   1.6146   0.02884   0.02193  -0.0995   0.0145   1.0000
  11.250   1.6100   0.03113   0.02437  -0.0956   0.0140   1.0000
  11.500   1.6128   0.03294   0.02630  -0.0929   0.0136   1.0000
  11.750   1.6199   0.03441   0.02789  -0.0908   0.0133   1.0000
  12.000   1.6248   0.03613   0.02974  -0.0887   0.0128   1.0000
  12.250   1.6283   0.03805   0.03179  -0.0867   0.0124   1.0000
  12.500   1.6304   0.04018   0.03405  -0.0847   0.0121   1.0000
  12.750   1.6315   0.04249   0.03647  -0.0828   0.0118   1.0000
  13.000   1.6318   0.04493   0.03903  -0.0811   0.0115   1.0000
  13.250   1.6309   0.04757   0.04179  -0.0795   0.0113   1.0000
  13.500   1.6288   0.05043   0.04476  -0.0781   0.0110   1.0000
  13.750   1.6247   0.05358   0.04803  -0.0767   0.0108   1.0000
  14.000   1.6188   0.05704   0.05162  -0.0754   0.0107   1.0000
  14.250   1.6102   0.06096   0.05569  -0.0741   0.0105   1.0000
  14.500   1.5991   0.06533   0.06024  -0.0729   0.0103   1.0000
  15.000   1.5776   0.07445   0.06976  -0.0721   0.0102   1.0000
  15.250   1.5685   0.07906   0.07454  -0.0727   0.0101   1.0000
  15.500   1.5585   0.08405   0.07973  -0.0737   0.0101   1.0000
  15.750   1.5473   0.08949   0.08535  -0.0752   0.0100   1.0000
  16.000   1.5348   0.09540   0.09144  -0.0772   0.0100   1.0000
  16.250   1.5217   0.10170   0.09793  -0.0797   0.0099   1.0000
  16.500   1.5077   0.10844   0.10486  -0.0827   0.0099   1.0000
  16.750   1.4932   0.11556   0.11215  -0.0863   0.0099   1.0000
  17.000   1.4777   0.12309   0.11986  -0.0903   0.0099   1.0000
  17.250   1.4623   0.13088   0.12782  -0.0947   0.0098   1.0000
  17.500   1.4461   0.13907   0.13619  -0.0996   0.0099   1.0000
  17.750   1.4300   0.14759   0.14486  -0.1049   0.0099   1.0000
  18.000   1.4131   0.15663   0.15405  -0.1108   0.0099   1.0000
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