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GOE 358 AIRFOIL (goe358-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 358 AIRFOIL (goe358-il)
Reynolds number: 200,000
Max Cl/Cd: 79.01 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe358-il-200000.txt
Download as CSV file: xf-goe358-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 358 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  -0.3353   0.09284   0.08933  -0.0312   1.0000   0.0753
  -7.750  -0.3488   0.09111   0.08768  -0.0294   1.0000   0.0776
  -7.250  -0.4084   0.08522   0.08203  -0.0362   1.0000   0.0807
  -7.000  -0.4076   0.08282   0.07967  -0.0292   1.0000   0.0819
  -6.750  -0.3789   0.04783   0.04421  -0.0806   0.9949   0.0696
  -6.500  -0.3221   0.03485   0.03033  -0.1014   0.9927   0.0666
  -6.250  -0.2708   0.02859   0.02308  -0.1122   0.9899   0.0695
  -6.000  -0.2301   0.02624   0.02061  -0.1163   0.9866   0.0723
  -5.750  -0.1864   0.02472   0.01886  -0.1205   0.9838   0.0760
  -5.500  -0.1446   0.02302   0.01674  -0.1240   0.9794   0.0787
  -5.250  -0.1023   0.02161   0.01494  -0.1275   0.9751   0.0813
  -5.000  -0.0602   0.01992   0.01315  -0.1309   0.9724   0.0842
  -4.750  -0.0192   0.01910   0.01224  -0.1337   0.9683   0.0877
  -4.500   0.0202   0.01826   0.01126  -0.1360   0.9619   0.0905
  -4.250   0.0665   0.01745   0.01029  -0.1394   0.9579   0.0933
  -4.000   0.1074   0.01634   0.00920  -0.1418   0.9509   0.0970
  -3.750   0.1515   0.01555   0.00842  -0.1448   0.9453   0.1009
  -3.500   0.1969   0.01488   0.00772  -0.1480   0.9422   0.1058
  -3.250   0.2306   0.01430   0.00719  -0.1489   0.9335   0.1115
  -3.000   0.2702   0.01375   0.00664  -0.1509   0.9283   0.1198
  -2.750   0.3044   0.01321   0.00617  -0.1519   0.9199   0.1340
  -2.500   0.3412   0.01227   0.00570  -0.1538   0.9129   0.2321
  -2.250   0.3720   0.01233   0.00585  -0.1537   0.9023   0.3027
  -2.000   0.4054   0.01235   0.00578  -0.1541   0.8938   0.3264
  -1.750   0.4344   0.01240   0.00576  -0.1536   0.8809   0.3418
  -1.500   0.4630   0.01246   0.00583  -0.1531   0.8675   0.3552
  -1.250   0.4917   0.01251   0.00588  -0.1526   0.8541   0.3669
  -1.000   0.5204   0.01253   0.00584  -0.1522   0.8401   0.3783
  -0.750   0.5489   0.01256   0.00579  -0.1518   0.8254   0.3883
  -0.500   0.5767   0.01257   0.00578  -0.1512   0.8099   0.3971
  -0.250   0.6047   0.01264   0.00572  -0.1507   0.7937   0.4075
   0.000   0.6317   0.01269   0.00578  -0.1500   0.7767   0.4161
   0.250   0.6590   0.01276   0.00574  -0.1495   0.7592   0.4256
   0.500   0.6859   0.01284   0.00577  -0.1489   0.7413   0.4334
   0.750   0.7131   0.01291   0.00573  -0.1483   0.7231   0.4412
   1.000   0.7398   0.01297   0.00573  -0.1478   0.7047   0.4471
   1.250   0.7668   0.01306   0.00570  -0.1473   0.6857   0.4531
   1.500   0.7934   0.01311   0.00567  -0.1467   0.6655   0.4580
   1.750   0.8197   0.01317   0.00569  -0.1462   0.6434   0.4631
   2.000   0.8459   0.01328   0.00567  -0.1456   0.6205   0.4686
   2.250   0.8718   0.01337   0.00567  -0.1449   0.5960   0.4734
   2.500   0.8973   0.01353   0.00572  -0.1443   0.5726   0.4788
   2.750   0.9232   0.01376   0.00581  -0.1437   0.5514   0.4856
   3.000   0.9490   0.01394   0.00595  -0.1431   0.5327   0.4914
   3.250   0.9750   0.01418   0.00611  -0.1427   0.5168   0.4981
   3.500   1.0013   0.01444   0.00630  -0.1423   0.5037   0.5047
   3.750   1.0275   0.01465   0.00652  -0.1418   0.4913   0.5121
   4.000   1.0539   0.01487   0.00675  -0.1415   0.4799   0.5206
   4.250   1.0802   0.01513   0.00699  -0.1411   0.4702   0.5302
   4.500   1.1065   0.01530   0.00724  -0.1407   0.4603   0.5400
   4.750   1.1329   0.01554   0.00751  -0.1404   0.4517   0.5513
   5.000   1.1589   0.01574   0.00776  -0.1399   0.4426   0.5647
   5.250   1.1847   0.01592   0.00805  -0.1395   0.4335   0.5815
   5.500   1.2102   0.01609   0.00831  -0.1389   0.4253   0.6056
   5.750   1.2352   0.01612   0.00863  -0.1383   0.4173   0.6693
   6.000   1.2574   0.01598   0.00881  -0.1369   0.4091   1.0000
   6.250   1.2828   0.01627   0.00913  -0.1364   0.3997   1.0000
   6.500   1.3077   0.01664   0.00942  -0.1358   0.3905   1.0000
   6.750   1.3315   0.01687   0.00973  -0.1349   0.3788   1.0000
   7.000   1.3550   0.01715   0.01006  -0.1341   0.3666   1.0000
   7.250   1.3779   0.01746   0.01038  -0.1331   0.3539   1.0000
   7.500   1.4001   0.01778   0.01072  -0.1320   0.3400   1.0000
   7.750   1.4216   0.01810   0.01109  -0.1308   0.3238   1.0000
   8.000   1.4424   0.01842   0.01147  -0.1294   0.3031   1.0000
   8.250   1.4615   0.01883   0.01187  -0.1279   0.2722   1.0000
   8.500   1.4711   0.01995   0.01254  -0.1251   0.1920   1.0000
   8.750   1.4742   0.02188   0.01407  -0.1216   0.1481   1.0000
   9.000   1.4828   0.02333   0.01537  -0.1187   0.1138   1.0000
   9.250   1.4895   0.02476   0.01662  -0.1156   0.0945   1.0000
   9.500   1.4938   0.02610   0.01792  -0.1120   0.0843   1.0000
   9.750   1.4975   0.02753   0.01938  -0.1085   0.0771   1.0000
  10.000   1.4973   0.02928   0.02111  -0.1048   0.0716   1.0000
  10.250   1.5005   0.03091   0.02284  -0.1017   0.0670   1.0000
  10.500   1.5034   0.03262   0.02461  -0.0988   0.0630   1.0000
  10.750   1.4986   0.03509   0.02704  -0.0955   0.0599   1.0000
  11.000   1.5045   0.03677   0.02887  -0.0933   0.0571   1.0000
  11.250   1.5088   0.03864   0.03082  -0.0912   0.0542   1.0000
  11.500   1.5109   0.04079   0.03298  -0.0892   0.0518   1.0000
  11.750   1.5125   0.04326   0.03546  -0.0869   0.0496   1.0000
  12.000   1.5190   0.04516   0.03752  -0.0853   0.0478   1.0000
  12.250   1.5245   0.04719   0.03965  -0.0837   0.0459   1.0000
  12.500   1.5297   0.04928   0.04179  -0.0823   0.0442   1.0000
  12.750   1.5359   0.05143   0.04390  -0.0808   0.0425   1.0000
  13.000   1.5423   0.05372   0.04630  -0.0792   0.0410   1.0000
  13.250   1.5467   0.05604   0.04880  -0.0780   0.0398   1.0000
  13.500   1.5514   0.05840   0.05132  -0.0767   0.0386   1.0000
  13.750   1.5554   0.06086   0.05390  -0.0757   0.0376   1.0000
  14.000   1.5591   0.06330   0.05642  -0.0747   0.0366   1.0000
  14.250   1.5663   0.06552   0.05864  -0.0736   0.0355   1.0000
  14.500   1.5723   0.06837   0.06160  -0.0722   0.0345   1.0000
  14.750   1.5662   0.07190   0.06538  -0.0718   0.0339   1.0000
  15.000   1.5605   0.07560   0.06932  -0.0715   0.0333   1.0000
  15.250   1.5546   0.07947   0.07342  -0.0714   0.0327   1.0000
  15.500   1.5479   0.08359   0.07776  -0.0715   0.0323   1.0000
  15.750   1.5400   0.08795   0.08234  -0.0719   0.0319   1.0000
  16.000   1.5310   0.09259   0.08717  -0.0727   0.0315   1.0000
  16.250   1.5207   0.09756   0.09235  -0.0739   0.0312   1.0000
  16.500   1.5091   0.10288   0.09788  -0.0755   0.0310   1.0000
  16.750   1.4967   0.10849   0.10369  -0.0776   0.0307   1.0000
  17.000   1.4824   0.11464   0.11004  -0.0804   0.0306   1.0000
  17.250   1.4629   0.12209   0.11772  -0.0843   0.0306   1.0000
  17.500   1.4346   0.13185   0.12779  -0.0903   0.0308   1.0000
  17.750   1.3917   0.14594   0.14226  -0.1001   0.0314   1.0000
  18.000   1.3408   0.16381   0.16047  -0.1133   0.0325   1.0000
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