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GOE 711 AIRFOIL (goe711-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 711 AIRFOIL (goe711-il)
Reynolds number: 200,000
Max Cl/Cd: 64.61 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe711-il-200000.txt
Download as CSV file: xf-goe711-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 711 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1699   0.09961   0.09642  -0.0662   0.9664   0.0435
  -7.750  -0.1714   0.09489   0.09170  -0.0785   0.9574   0.0447
  -7.500  -0.1654   0.08894   0.08564  -0.0906   0.9452   0.0450
  -7.250  -0.1462   0.08446   0.08125  -0.0874   0.9443   0.0458
  -7.000  -0.1205   0.08092   0.07770  -0.0889   0.9426   0.0468
  -6.750  -0.1112   0.07788   0.07465  -0.0900   0.9330   0.0479
  -6.500  -0.0848   0.07321   0.06991  -0.0969   0.9292   0.0505
  -6.250  -0.0643   0.06760   0.06368  -0.1103   0.9168   0.0541
  -6.000  -0.0411   0.06150   0.05781  -0.1122   0.9149   0.0552
  -5.750  -0.0089   0.05801   0.05432  -0.1155   0.9133   0.0567
  -5.500   0.0268   0.05418   0.05037  -0.1204   0.9116   0.0596
  -5.250   0.0480   0.05044   0.04597  -0.1233   0.8999   0.0658
  -5.000   0.0784   0.04625   0.04194  -0.1260   0.8978   0.0676
  -4.750   0.0969   0.04410   0.03976  -0.1256   0.8883   0.0699
  -4.250   0.1592   0.03795   0.03303  -0.1298   0.8778   0.0811
  -4.000   0.1866   0.03581   0.03085  -0.1306   0.8710   0.0850
  -3.750   0.2224   0.03325   0.02793  -0.1329   0.8673   0.0962
  -3.500   0.2448   0.03163   0.02630  -0.1324   0.8565   0.1015
  -3.250   0.2770   0.02954   0.02395  -0.1338   0.8501   0.1135
  -3.000   0.3048   0.02812   0.02230  -0.1342   0.8399   0.1284
  -2.750   0.3323   0.02671   0.02075  -0.1345   0.8292   0.1450
  -2.500   0.3620   0.02506   0.01906  -0.1354   0.8197   0.1637
  -1.750   0.4661   0.02044   0.01273  -0.1337   0.7816   0.0784
  -1.500   0.4949   0.01859   0.01074  -0.1337   0.7675   0.0749
  -1.250   0.5238   0.01787   0.00983  -0.1336   0.7523   0.0751
  -1.000   0.5520   0.01718   0.00896  -0.1333   0.7364   0.0745
  -0.750   0.5797   0.01660   0.00823  -0.1329   0.7198   0.0739
  -0.500   0.6067   0.01615   0.00766  -0.1325   0.7028   0.0742
  -0.250   0.6333   0.01581   0.00721  -0.1321   0.6857   0.0751
   0.000   0.6595   0.01560   0.00688  -0.1316   0.6684   0.0771
   0.250   0.6852   0.01530   0.00650  -0.1312   0.6509   0.0803
   0.500   0.7107   0.01512   0.00623  -0.1308   0.6334   0.0839
   0.750   0.7361   0.01507   0.00607  -0.1303   0.6156   0.0887
   1.000   0.7614   0.01506   0.00593  -0.1298   0.5982   0.0969
   1.250   0.7860   0.01465   0.00591  -0.1295   0.5815   0.2532
   1.500   0.8068   0.01313   0.00599  -0.1274   0.5659   1.0000
   1.750   0.8309   0.01341   0.00603  -0.1268   0.5498   1.0000
   2.000   0.8549   0.01371   0.00613  -0.1261   0.5346   1.0000
   2.250   0.8790   0.01402   0.00624  -0.1255   0.5206   1.0000
   2.500   0.9030   0.01432   0.00640  -0.1250   0.5070   1.0000
   2.750   0.9270   0.01462   0.00658  -0.1244   0.4942   1.0000
   3.000   0.9511   0.01495   0.00678  -0.1239   0.4826   1.0000
   3.250   0.9754   0.01531   0.00697  -0.1235   0.4721   1.0000
   3.500   0.9993   0.01561   0.00721  -0.1229   0.4615   1.0000
   3.750   1.0238   0.01597   0.00746  -0.1225   0.4524   1.0000
   4.000   1.0481   0.01631   0.00770  -0.1221   0.4439   1.0000
   4.250   1.0727   0.01667   0.00800  -0.1218   0.4360   1.0000
   4.500   1.0970   0.01702   0.00827  -0.1214   0.4284   1.0000
   4.750   1.1217   0.01739   0.00858  -0.1212   0.4214   1.0000
   5.000   1.1455   0.01773   0.00890  -0.1207   0.4144   1.0000
   5.250   1.1714   0.01817   0.00921  -0.1207   0.4085   1.0000
   5.500   1.1946   0.01850   0.00959  -0.1202   0.4023   1.0000
   5.750   1.2193   0.01888   0.00993  -0.1199   0.3969   1.0000
   6.000   1.2454   0.01933   0.01032  -0.1200   0.3919   1.0000
   6.250   1.2682   0.01969   0.01073  -0.1195   0.3865   1.0000
   6.500   1.2919   0.02007   0.01108  -0.1191   0.3813   1.0000
   6.750   1.3159   0.02052   0.01149  -0.1188   0.3758   1.0000
   7.000   1.3354   0.02085   0.01189  -0.1176   0.3697   1.0000
   7.250   1.3581   0.02124   0.01223  -0.1170   0.3645   1.0000
   7.500   1.3807   0.02170   0.01271  -0.1166   0.3596   1.0000
   7.750   1.4007   0.02209   0.01319  -0.1155   0.3549   1.0000
   8.000   1.4231   0.02251   0.01362  -0.1150   0.3508   1.0000
   8.250   1.4511   0.02304   0.01408  -0.1156   0.3470   1.0000
   8.500   1.4678   0.02347   0.01466  -0.1139   0.3428   1.0000
   8.750   1.4842   0.02387   0.01513  -0.1123   0.3379   1.0000
   9.000   1.5021   0.02426   0.01548  -0.1109   0.3328   1.0000
   9.250   1.5135   0.02473   0.01604  -0.1083   0.3274   1.0000
   9.500   1.5231   0.02516   0.01656  -0.1055   0.3218   1.0000
   9.750   1.5399   0.02563   0.01698  -0.1041   0.3166   1.0000
  10.000   1.5487   0.02620   0.01769  -0.1013   0.3113   1.0000
  10.250   1.5576   0.02675   0.01834  -0.0986   0.3055   1.0000
  10.500   1.5727   0.02733   0.01885  -0.0971   0.3001   1.0000
  10.750   1.5791   0.02804   0.01977  -0.0942   0.2948   1.0000
  11.000   1.5887   0.02874   0.02055  -0.0920   0.2894   1.0000
  11.250   1.6014   0.02947   0.02125  -0.0903   0.2845   1.0000
  11.500   1.6090   0.03033   0.02234  -0.0880   0.2792   1.0000
  11.750   1.6152   0.03128   0.02334  -0.0856   0.2726   1.0000
  12.000   1.6214   0.03234   0.02451  -0.0834   0.2658   1.0000
  12.250   1.6263   0.03353   0.02578  -0.0812   0.2582   1.0000
  12.500   1.6320   0.03481   0.02718  -0.0793   0.2503   1.0000
  12.750   1.6349   0.03633   0.02876  -0.0772   0.2420   1.0000
  13.000   1.6378   0.03801   0.03055  -0.0754   0.2305   1.0000
  13.250   1.6378   0.04004   0.03263  -0.0735   0.2170   1.0000
  13.500   1.6316   0.04279   0.03536  -0.0715   0.1984   1.0000
  13.750   1.6186   0.04641   0.03889  -0.0694   0.1717   1.0000
  14.000   1.5958   0.05130   0.04363  -0.0674   0.1425   1.0000
  14.250   1.5700   0.05688   0.04911  -0.0657   0.1201   1.0000
  14.500   1.5434   0.06291   0.05511  -0.0647   0.0967   1.0000
  14.750   1.5138   0.06968   0.06184  -0.0642   0.0645   1.0000
  15.000   1.4868   0.07648   0.06868  -0.0643   0.0583   1.0000
  15.250   1.4635   0.08304   0.07538  -0.0647   0.0528   1.0000
  15.500   1.4411   0.08970   0.08219  -0.0655   0.0492   1.0000
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