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GOE 7K AIRFOIL (goe07k-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 7K AIRFOIL (goe07k-il)
Reynolds number: 500,000
Max Cl/Cd: 116.48 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe07k-il-500000-n5.txt
Download as CSV file: xf-goe07k-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 7K 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.1277   0.08429   0.08167  -0.1249   0.9455   0.0069
  -9.500  -0.1312   0.08072   0.07812  -0.1253   0.9399   0.0071
  -9.250  -0.1315   0.07593   0.07335  -0.1280   0.9364   0.0072
  -9.000  -0.1252   0.07197   0.06938  -0.1313   0.9341   0.0071
  -8.750  -0.1177   0.06753   0.06494  -0.1361   0.9323   0.0069
  -8.500  -0.1204   0.06302   0.06044  -0.1401   0.9274   0.0068
  -8.250  -0.1276   0.05826   0.05566  -0.1433   0.9211   0.0067
  -8.000  -0.1240   0.04948   0.04674  -0.1518   0.9175   0.0069
  -7.750  -0.1266   0.04466   0.04178  -0.1523   0.9120   0.0066
  -7.250  -0.2024   0.01967   0.01489  -0.1389   0.8963   0.0067
  -7.000  -0.1899   0.01777   0.01259  -0.1363   0.8928   0.0069
  -6.750  -0.1676   0.01634   0.01078  -0.1356   0.8907   0.0074
  -6.500  -0.1416   0.01507   0.00925  -0.1358   0.8892   0.0077
  -6.250  -0.1096   0.01464   0.00875  -0.1373   0.8880   0.0084
  -6.000  -0.0871   0.01398   0.00795  -0.1365   0.8858   0.0089
  -5.750  -0.0809   0.01356   0.00742  -0.1318   0.8810   0.0094
  -5.500  -0.0593   0.01297   0.00668  -0.1307   0.8783   0.0098
  -5.250  -0.0335   0.01235   0.00596  -0.1306   0.8761   0.0107
  -5.000  -0.0028   0.01194   0.00549  -0.1315   0.8745   0.0119
  -4.750   0.0296   0.01149   0.00493  -0.1329   0.8732   0.0135
  -4.500   0.0377   0.01126   0.00467  -0.1286   0.8689   0.0146
  -4.250   0.0544   0.01101   0.00436  -0.1263   0.8653   0.0158
  -4.000   0.0784   0.01071   0.00401  -0.1256   0.8628   0.0186
  -3.750   0.1064   0.01043   0.00372  -0.1259   0.8609   0.0229
  -3.500   0.1385   0.01020   0.00347  -0.1271   0.8594   0.0304
  -3.250   0.1637   0.01010   0.00336  -0.1268   0.8570   0.0375
  -3.000   0.1724   0.01008   0.00335  -0.1225   0.8521   0.0420
  -2.750   0.1964   0.01004   0.00325  -0.1218   0.8491   0.0470
  -2.500   0.2234   0.00986   0.00305  -0.1219   0.8469   0.0510
  -2.250   0.2548   0.00971   0.00286  -0.1230   0.8452   0.0560
  -2.000   0.2819   0.00961   0.00272  -0.1230   0.8430   0.0591
  -1.750   0.2910   0.00961   0.00270  -0.1189   0.8383   0.0603
  -1.500   0.3123   0.00950   0.00257  -0.1176   0.8351   0.0636
  -1.250   0.3389   0.00939   0.00244  -0.1175   0.8327   0.0661
  -1.000   0.3699   0.00927   0.00230  -0.1185   0.8308   0.0694
  -0.750   0.3938   0.00923   0.00224  -0.1178   0.8280   0.0722
  -0.500   0.4060   0.00922   0.00228  -0.1144   0.8233   0.0842
  -0.250   0.4237   0.00886   0.00230  -0.1125   0.8200   0.2176
   0.000   0.4468   0.00847   0.00230  -0.1119   0.8176   0.3624
   0.250   0.4645   0.00772   0.00234  -0.1101   0.8154   0.6325
   0.500   0.4646   0.00737   0.00255  -0.1038   0.8104   0.7944
   1.000   0.7617   0.00781   0.00337  -0.1609   0.8194   0.9948
   1.250   0.8030   0.00779   0.00333  -0.1643   0.8162   0.9967
   1.500   0.8332   0.00779   0.00335  -0.1651   0.8096   1.0000
   1.750   0.8509   0.00779   0.00334  -0.1630   0.8032   1.0000
   2.000   0.8595   0.00781   0.00334  -0.1587   0.7934   1.0000
   2.500   0.8914   0.00788   0.00340  -0.1537   0.7783   1.0000
   2.750   0.9104   0.00792   0.00342  -0.1518   0.7697   1.0000
   3.000   0.9236   0.00798   0.00346  -0.1486   0.7577   1.0000
   3.250   0.9365   0.00807   0.00355  -0.1454   0.7471   1.0000
   3.500   0.9502   0.00817   0.00363  -0.1423   0.7334   1.0000
   3.750   0.9656   0.00829   0.00374  -0.1397   0.7222   1.0000
   4.000   0.9797   0.00842   0.00387  -0.1368   0.7091   1.0000
   4.250   0.9895   0.00861   0.00402  -0.1328   0.6888   1.0000
   4.500   0.9888   0.00895   0.00422  -0.1266   0.6502   1.0000
   4.750   0.9647   0.00981   0.00466  -0.1153   0.5663   1.0000
   5.000   0.9476   0.01086   0.00532  -0.1060   0.4981   1.0000
   5.500   0.9332   0.01298   0.00675  -0.0926   0.3558   1.0000
   5.750   0.9323   0.01403   0.00746  -0.0874   0.2827   1.0000
   6.000   0.9303   0.01525   0.00827  -0.0823   0.2031   1.0000
   6.250   0.9343   0.01628   0.00897  -0.0784   0.1363   1.0000
   6.500   0.9406   0.01726   0.00967  -0.0749   0.0812   1.0000
   6.750   0.9542   0.01788   0.01023  -0.0727   0.0632   1.0000
   7.000   0.9680   0.01849   0.01079  -0.0706   0.0452   1.0000
   7.250   0.9800   0.01924   0.01142  -0.0682   0.0241   1.0000
   7.500   0.9937   0.01991   0.01209  -0.0661   0.0174   1.0000
   7.750   1.0077   0.02057   0.01276  -0.0641   0.0143   1.0000
   8.000   1.0231   0.02115   0.01341  -0.0623   0.0124   1.0000
   8.250   1.0372   0.02183   0.01412  -0.0603   0.0111   1.0000
   8.500   1.0508   0.02255   0.01490  -0.0584   0.0099   1.0000
   8.750   1.0654   0.02321   0.01561  -0.0566   0.0090   1.0000
   9.000   1.0778   0.02404   0.01647  -0.0545   0.0081   1.0000
   9.250   1.0906   0.02486   0.01738  -0.0525   0.0077   1.0000
   9.500   1.1033   0.02569   0.01828  -0.0505   0.0072   1.0000
   9.750   1.1158   0.02654   0.01918  -0.0486   0.0066   1.0000
  10.000   1.1261   0.02756   0.02027  -0.0464   0.0064   1.0000
  10.250   1.1359   0.02865   0.02144  -0.0442   0.0060   1.0000
  10.500   1.1474   0.02963   0.02251  -0.0422   0.0057   1.0000
  10.750   1.1569   0.03079   0.02379  -0.0400   0.0054   1.0000
  11.000   1.1700   0.03165   0.02471  -0.0385   0.0050   1.0000
  11.250   1.1785   0.03294   0.02609  -0.0363   0.0048   1.0000
  11.500   1.1887   0.03407   0.02728  -0.0345   0.0046   1.0000
  11.750   1.1957   0.03554   0.02884  -0.0323   0.0045   1.0000
  12.000   1.2049   0.03687   0.03032  -0.0303   0.0043   1.0000
  12.250   1.2129   0.03836   0.03195  -0.0283   0.0043   1.0000
  12.500   1.2207   0.03995   0.03369  -0.0263   0.0042   1.0000
  12.750   1.2277   0.04168   0.03563  -0.0243   0.0040   1.0000
  13.000   1.2343   0.04340   0.03753  -0.0224   0.0039   1.0000
  13.250   1.2386   0.04543   0.03975  -0.0202   0.0037   1.0000
  13.500   1.2429   0.04726   0.04174  -0.0184   0.0035   1.0000
  13.750   1.2469   0.04903   0.04363  -0.0168   0.0034   1.0000
  14.000   1.2484   0.05121   0.04597  -0.0150   0.0034   1.0000
  14.250   1.2452   0.05404   0.04901  -0.0129   0.0033   1.0000
  14.500   1.2483   0.05577   0.05077  -0.0119   0.0032   1.0000
  14.750   1.2393   0.05944   0.05470  -0.0099   0.0032   1.0000
  15.000   1.2346   0.06239   0.05778  -0.0087   0.0031   1.0000
  15.250   1.2245   0.06633   0.06199  -0.0073   0.0031   1.0000
  15.500   1.2075   0.07135   0.06731  -0.0062   0.0030   1.0000
  15.750   1.1889   0.07683   0.07306  -0.0057   0.0030   1.0000
  16.000   1.1719   0.08236   0.07881  -0.0060   0.0030   1.0000
  16.250   1.1474   0.08953   0.08627  -0.0072   0.0029   1.0000
  16.500   1.1290   0.09609   0.09299  -0.0092   0.0030   1.0000
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