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GOE 430 AIRFOIL (goe430-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 430 AIRFOIL (goe430-il)
Reynolds number: 500,000
Max Cl/Cd: 96.6 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe430-il-500000-n5.txt
Download as CSV file: xf-goe430-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 430 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
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.7859   0.07370   0.07058  -0.0755   1.0000   0.0347
 -14.750  -0.8224   0.06452   0.06126  -0.0820   1.0000   0.0349
 -14.500  -0.8492   0.05734   0.05394  -0.0872   1.0000   0.0351
 -14.250  -0.8717   0.05127   0.04776  -0.0914   1.0000   0.0352
 -14.000  -0.8965   0.04625   0.04266  -0.0934   1.0000   0.0353
 -13.750  -0.8965   0.04097   0.03730  -0.1004   0.9935   0.0358
 -13.500  -0.8819   0.03637   0.03260  -0.1085   0.9847   0.0363
 -13.250  -0.8594   0.03266   0.02878  -0.1163   0.9772   0.0369
 -13.000  -0.8297   0.02967   0.02566  -0.1240   0.9718   0.0376
 -12.750  -0.8009   0.02740   0.02325  -0.1299   0.9650   0.0383
 -12.500  -0.7718   0.02588   0.02159  -0.1337   0.9602   0.0391
 -12.250  -0.7441   0.02469   0.02027  -0.1363   0.9553   0.0398
 -12.000  -0.7174   0.02369   0.01913  -0.1381   0.9496   0.0406
 -11.750  -0.6889   0.02297   0.01826  -0.1397   0.9451   0.0413
 -11.500  -0.6630   0.02194   0.01713  -0.1412   0.9400   0.0422
 -11.250  -0.6372   0.02111   0.01625  -0.1422   0.9338   0.0431
 -11.000  -0.6102   0.02039   0.01544  -0.1431   0.9282   0.0437
 -10.750  -0.5841   0.01966   0.01463  -0.1437   0.9219   0.0441
 -10.500  -0.5576   0.01898   0.01384  -0.1443   0.9157   0.0446
 -10.250  -0.5304   0.01836   0.01312  -0.1449   0.9111   0.0451
 -10.000  -0.5031   0.01779   0.01247  -0.1454   0.9066   0.0457
  -9.750  -0.4756   0.01722   0.01181  -0.1460   0.9024   0.0463
  -9.500  -0.4479   0.01666   0.01115  -0.1465   0.8983   0.0468
  -9.250  -0.4199   0.01614   0.01053  -0.1469   0.8946   0.0473
  -9.000  -0.3919   0.01565   0.00996  -0.1474   0.8905   0.0478
  -8.750  -0.3637   0.01520   0.00942  -0.1478   0.8861   0.0482
  -8.500  -0.3355   0.01479   0.00892  -0.1481   0.8812   0.0486
  -8.250  -0.3071   0.01441   0.00845  -0.1485   0.8765   0.0489
  -8.000  -0.2788   0.01399   0.00796  -0.1488   0.8707   0.0493
  -7.750  -0.2504   0.01341   0.00732  -0.1493   0.8657   0.0503
  -7.500  -0.2217   0.01297   0.00682  -0.1497   0.8613   0.0513
  -7.250  -0.1928   0.01260   0.00642  -0.1501   0.8558   0.0521
  -7.000  -0.1640   0.01227   0.00604  -0.1505   0.8501   0.0529
  -6.750  -0.1349   0.01198   0.00568  -0.1508   0.8453   0.0537
  -6.500  -0.1058   0.01170   0.00536  -0.1511   0.8398   0.0545
  -6.250  -0.0767   0.01144   0.00504  -0.1514   0.8335   0.0554
  -6.000  -0.0477   0.01121   0.00474  -0.1516   0.8273   0.0563
  -5.750  -0.0186   0.01098   0.00447  -0.1518   0.8196   0.0572
  -5.500   0.0104   0.01080   0.00420  -0.1520   0.8119   0.0580
  -5.250   0.0397   0.01057   0.00394  -0.1523   0.8036   0.0593
  -5.000   0.0689   0.01035   0.00367  -0.1525   0.7961   0.0615
  -4.750   0.0982   0.01014   0.00345  -0.1528   0.7881   0.0640
  -4.500   0.1273   0.00999   0.00324  -0.1530   0.7800   0.0668
  -4.250   0.1566   0.00983   0.00306  -0.1532   0.7708   0.0707
  -4.000   0.1858   0.00965   0.00288  -0.1534   0.7614   0.0789
  -3.750   0.2148   0.00945   0.00274  -0.1537   0.7503   0.0999
  -3.500   0.2438   0.00936   0.00266  -0.1538   0.7385   0.1151
  -3.250   0.2725   0.00931   0.00258  -0.1539   0.7259   0.1241
  -3.000   0.3010   0.00931   0.00250  -0.1539   0.7127   0.1309
  -2.500   0.3581   0.00928   0.00238  -0.1540   0.6862   0.1432
  -2.250   0.3864   0.00932   0.00233  -0.1539   0.6715   0.1475
  -2.000   0.4146   0.00933   0.00228  -0.1539   0.6561   0.1526
  -1.750   0.4427   0.00936   0.00225  -0.1538   0.6409   0.1578
  -1.500   0.4708   0.00940   0.00223  -0.1538   0.6277   0.1625
  -1.250   0.4990   0.00943   0.00221  -0.1538   0.6157   0.1686
  -1.000   0.5274   0.00944   0.00220  -0.1538   0.6035   0.1769
  -0.750   0.5558   0.00944   0.00221  -0.1539   0.5917   0.1908
  -0.500   0.5842   0.00943   0.00224  -0.1540   0.5804   0.2148
  -0.250   0.6125   0.00943   0.00229  -0.1541   0.5692   0.2459
   0.000   0.6408   0.00946   0.00234  -0.1541   0.5579   0.2713
   0.250   0.6688   0.00952   0.00240  -0.1541   0.5456   0.2907
   0.500   0.6965   0.00960   0.00246  -0.1540   0.5309   0.3058
   0.750   0.7239   0.00971   0.00253  -0.1538   0.5141   0.3185
   1.000   0.7509   0.00985   0.00261  -0.1536   0.4953   0.3308
   1.250   0.7777   0.01000   0.00271  -0.1534   0.4773   0.3456
   1.500   0.8047   0.01013   0.00283  -0.1532   0.4630   0.3661
   1.750   0.8318   0.01025   0.00296  -0.1531   0.4519   0.3913
   2.000   0.8593   0.01035   0.00310  -0.1530   0.4422   0.4199
   2.250   0.8865   0.01047   0.00325  -0.1528   0.4344   0.4503
   2.500   0.9141   0.01056   0.00339  -0.1527   0.4275   0.4746
   3.000   0.9684   0.01082   0.00369  -0.1524   0.4127   0.5130
   3.250   0.9952   0.01096   0.00386  -0.1521   0.4052   0.5295
   3.500   1.0222   0.01108   0.00402  -0.1519   0.3985   0.5483
   3.750   1.0493   0.01120   0.00420  -0.1517   0.3915   0.5709
   4.000   1.0757   0.01136   0.00440  -0.1514   0.3844   0.5944
   4.250   1.1024   0.01149   0.00459  -0.1511   0.3748   0.6165
   4.500   1.1283   0.01168   0.00479  -0.1507   0.3625   0.6379
   4.750   1.1532   0.01194   0.00502  -0.1502   0.3417   0.6592
   5.000   1.1696   0.01286   0.00553  -0.1484   0.2611   0.6763
   5.250   1.1899   0.01348   0.00601  -0.1472   0.2321   0.6907
   5.500   1.2130   0.01386   0.00637  -0.1463   0.2200   0.7061
   5.750   1.2363   0.01417   0.00671  -0.1456   0.2120   0.7267
   6.000   1.2600   0.01439   0.00703  -0.1448   0.2064   0.7566
   6.250   1.2767   0.01431   0.00728  -0.1424   0.2015   1.0000
   6.500   1.3000   0.01465   0.00762  -0.1417   0.1969   1.0000
   6.750   1.3235   0.01497   0.00794  -0.1409   0.1907   1.0000
   7.000   1.3445   0.01544   0.00835  -0.1398   0.1810   1.0000
   7.250   1.3669   0.01578   0.00868  -0.1389   0.1722   1.0000
   7.500   1.3877   0.01621   0.00908  -0.1378   0.1637   1.0000
   7.750   1.4071   0.01666   0.00948  -0.1364   0.1523   1.0000
   8.000   1.4235   0.01720   0.00995  -0.1345   0.1371   1.0000
   8.250   1.4379   0.01790   0.01053  -0.1324   0.1170   1.0000
   8.750   1.4648   0.01944   0.01192  -0.1280   0.0925   1.0000
   9.000   1.4788   0.02019   0.01265  -0.1261   0.0865   1.0000
   9.250   1.4949   0.02082   0.01330  -0.1244   0.0836   1.0000
   9.500   1.5097   0.02154   0.01405  -0.1227   0.0804   1.0000
   9.750   1.5225   0.02241   0.01492  -0.1207   0.0764   1.0000
  10.000   1.5372   0.02318   0.01573  -0.1191   0.0735   1.0000
  10.250   1.5526   0.02391   0.01651  -0.1176   0.0705   1.0000
  10.500   1.5652   0.02484   0.01746  -0.1158   0.0659   1.0000
  10.750   1.5774   0.02584   0.01847  -0.1141   0.0603   1.0000
  11.000   1.5729   0.02810   0.02049  -0.1108   0.0305   1.0000
  11.250   1.5740   0.03004   0.02242  -0.1082   0.0223   1.0000
  11.500   1.5801   0.03164   0.02406  -0.1062   0.0193   1.0000
  11.750   1.5880   0.03313   0.02560  -0.1045   0.0177   1.0000
  12.000   1.5951   0.03473   0.02726  -0.1029   0.0165   1.0000
  12.250   1.6011   0.03647   0.02906  -0.1013   0.0155   1.0000
  12.500   1.6082   0.03815   0.03082  -0.0998   0.0149   1.0000
  12.750   1.6147   0.03993   0.03268  -0.0984   0.0143   1.0000
  13.000   1.6200   0.04186   0.03468  -0.0971   0.0138   1.0000
  13.250   1.6242   0.04396   0.03685  -0.0959   0.0133   1.0000
  13.500   1.6272   0.04624   0.03922  -0.0947   0.0129   1.0000
  13.750   1.6283   0.04881   0.04186  -0.0936   0.0124   1.0000
  14.000   1.6304   0.05137   0.04450  -0.0927   0.0121   1.0000
  14.250   1.6333   0.05389   0.04712  -0.0920   0.0118   1.0000
  14.500   1.6351   0.05659   0.04992  -0.0913   0.0115   1.0000
  14.750   1.6360   0.05946   0.05289  -0.0908   0.0112   1.0000
  15.000   1.6360   0.06252   0.05604  -0.0903   0.0109   1.0000
  15.250   1.6351   0.06575   0.05936  -0.0900   0.0107   1.0000
  15.500   1.6331   0.06915   0.06285  -0.0898   0.0105   1.0000
  15.750   1.6301   0.07275   0.06655  -0.0898   0.0103   1.0000
  16.000   1.6258   0.07659   0.07049  -0.0899   0.0101   1.0000
  16.250   1.6202   0.08069   0.07470  -0.0901   0.0099   1.0000
  16.500   1.6130   0.08508   0.07919  -0.0905   0.0098   1.0000
  16.750   1.6043   0.08975   0.08398  -0.0912   0.0096   1.0000
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