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GOE 615 AIRFOIL (goe615-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 615 AIRFOIL (goe615-il)
Reynolds number: 200,000
Max Cl/Cd: 74.63 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe615-il-200000.txt
Download as CSV file: xf-goe615-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 615 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.2423   0.13644   0.13266  -0.0414   1.0000   0.0486
 -12.250  -0.2483   0.13416   0.13043  -0.0428   1.0000   0.0500
 -12.000  -0.2720   0.13259   0.12893  -0.0459   1.0000   0.0505
 -11.750  -0.2569   0.12869   0.12507  -0.0431   1.0000   0.0510
 -11.500  -0.2499   0.12637   0.12278  -0.0410   1.0000   0.0516
 -11.250  -0.2492   0.12473   0.12120  -0.0389   1.0000   0.0524
 -11.000  -0.2547   0.12348   0.12000  -0.0365   1.0000   0.0532
 -10.750  -0.2638   0.12246   0.11905  -0.0339   1.0000   0.0540
 -10.500  -0.2595   0.11968   0.11630  -0.0354   0.9985   0.0554
 -10.250  -0.2657   0.11444   0.11106  -0.0489   0.9930   0.0580
 -10.000  -0.2451   0.10950   0.10612  -0.0502   0.9900   0.0586
  -9.750  -0.2176   0.10616   0.10277  -0.0507   0.9872   0.0597
  -9.500  -0.1954   0.10275   0.09935  -0.0539   0.9841   0.0615
  -9.250  -0.1798   0.09894   0.09553  -0.0587   0.9794   0.0644
  -9.000  -0.1883   0.09204   0.08866  -0.0745   0.9704   0.0671
  -8.750  -0.1572   0.08900   0.08560  -0.0724   0.9692   0.0681
  -8.500  -0.1371   0.08629   0.08288  -0.0733   0.9627   0.0693
  -8.250  -0.1149   0.08288   0.07947  -0.0773   0.9585   0.0717
  -8.000   0.0057   0.06352   0.06020  -0.0934   0.9411   0.0807
  -7.750  -0.0969   0.07196   0.06854  -0.0953   0.9424   0.0782
  -7.500  -0.0626   0.06968   0.06624  -0.0963   0.9409   0.0805
  -7.250  -0.0491   0.06638   0.06293  -0.1002   0.9301   0.0835
  -7.000  -0.0485   0.05741   0.05377  -0.1162   0.9155   0.0895
  -6.750  -0.0188   0.05573   0.05211  -0.1162   0.9112   0.0911
  -6.500  -0.0203   0.05167   0.04739  -0.1242   0.8954   0.1010
  -6.250   0.0076   0.04704   0.04301  -0.1251   0.8916   0.1029
  -6.000   0.0244   0.04600   0.04204  -0.1230   0.8810   0.1048
  -5.750   0.0494   0.04397   0.03990  -0.1244   0.8742   0.1103
  -5.500   0.0544   0.04052   0.03618  -0.1248   0.8614   0.1182
  -5.250   0.0756   0.03905   0.03470  -0.1242   0.8526   0.1213
  -5.000   0.0727   0.02747   0.02114  -0.1229   0.8417   0.0772
  -4.750   0.0937   0.02561   0.01915  -0.1218   0.8316   0.0758
  -4.500   0.1192   0.02356   0.01682  -0.1214   0.8236   0.0748
  -4.250   0.1402   0.02204   0.01505  -0.1200   0.8126   0.0737
  -4.000   0.1686   0.02062   0.01331  -0.1197   0.8050   0.0731
  -3.750   0.1909   0.01965   0.01214  -0.1183   0.7934   0.0732
  -3.500   0.2180   0.01884   0.01111  -0.1178   0.7844   0.0743
  -3.250   0.2440   0.01824   0.01032  -0.1170   0.7740   0.0757
  -3.000   0.2699   0.01771   0.00961  -0.1162   0.7637   0.0766
  -2.750   0.2974   0.01675   0.00857  -0.1158   0.7546   0.0780
  -2.500   0.3216   0.01618   0.00802  -0.1149   0.7437   0.0799
  -2.250   0.3497   0.01575   0.00753  -0.1146   0.7354   0.0827
  -2.000   0.3736   0.01546   0.00720  -0.1135   0.7243   0.0862
  -1.750   0.3992   0.01505   0.00674  -0.1128   0.7148   0.0895
  -1.500   0.4239   0.01465   0.00635  -0.1119   0.7047   0.0940
  -1.250   0.4486   0.01445   0.00611  -0.1110   0.6950   0.1001
  -1.000   0.4742   0.01412   0.00576  -0.1103   0.6864   0.1110
  -0.750   0.4973   0.01377   0.00555  -0.1092   0.6767   0.1363
  -0.500   0.5190   0.01299   0.00551  -0.1081   0.6693   0.3452
  -0.250   0.5382   0.01253   0.00559  -0.1064   0.6614   0.5020
   0.000   0.6454   0.01149   0.00555  -0.1218   0.6525   1.0000
   0.250   0.6677   0.01162   0.00556  -0.1206   0.6448   1.0000
   0.500   0.6913   0.01174   0.00554  -0.1196   0.6375   1.0000
   0.750   0.7152   0.01189   0.00556  -0.1187   0.6306   1.0000
   1.000   0.7379   0.01203   0.00561  -0.1175   0.6230   1.0000
   1.250   0.7635   0.01218   0.00560  -0.1169   0.6166   1.0000
   1.500   0.7849   0.01233   0.00572  -0.1156   0.6087   1.0000
   1.750   0.8097   0.01248   0.00574  -0.1148   0.6018   1.0000
   2.000   0.8321   0.01265   0.00587  -0.1136   0.5942   1.0000
   2.250   0.8557   0.01280   0.00593  -0.1126   0.5867   1.0000
   2.500   0.8792   0.01298   0.00605  -0.1116   0.5792   1.0000
   2.750   0.9018   0.01314   0.00615  -0.1104   0.5710   1.0000
   3.000   0.9257   0.01334   0.00626  -0.1095   0.5632   1.0000
   3.250   0.9475   0.01350   0.00640  -0.1082   0.5543   1.0000
   3.500   0.9709   0.01371   0.00652  -0.1072   0.5459   1.0000
   3.750   0.9923   0.01388   0.00667  -0.1059   0.5364   1.0000
   4.000   1.0142   0.01408   0.00682  -0.1046   0.5267   1.0000
   4.250   1.0362   0.01426   0.00691  -0.1034   0.5161   1.0000
   4.500   1.0545   0.01441   0.00708  -0.1014   0.5038   1.0000
   4.750   1.0743   0.01460   0.00722  -0.0998   0.4918   1.0000
   5.000   1.0941   0.01478   0.00732  -0.0981   0.4796   1.0000
   5.250   1.1108   0.01494   0.00747  -0.0959   0.4653   1.0000
   5.500   1.1275   0.01512   0.00765  -0.0937   0.4505   1.0000
   5.750   1.1434   0.01532   0.00781  -0.0914   0.4346   1.0000
   6.000   1.1583   0.01557   0.00800  -0.0890   0.4181   1.0000
   6.250   1.1728   0.01587   0.00822  -0.0865   0.4024   1.0000
   6.500   1.1867   0.01622   0.00850  -0.0840   0.3876   1.0000
   6.750   1.1995   0.01662   0.00882  -0.0813   0.3746   1.0000
   7.000   1.2119   0.01707   0.00918  -0.0786   0.3632   1.0000
   7.250   1.2246   0.01757   0.00958  -0.0760   0.3523   1.0000
   7.500   1.2390   0.01805   0.01005  -0.0739   0.3425   1.0000
   8.000   1.2687   0.01912   0.01104  -0.0698   0.3256   1.0000
   8.250   1.2844   0.01974   0.01156  -0.0681   0.3182   1.0000
   8.500   1.2989   0.02024   0.01212  -0.0661   0.3105   1.0000
   8.750   1.3139   0.02085   0.01267  -0.0643   0.3035   1.0000
   9.000   1.3275   0.02143   0.01328  -0.0624   0.2961   1.0000
   9.250   1.3407   0.02203   0.01390  -0.0605   0.2891   1.0000
   9.500   1.3557   0.02269   0.01453  -0.0589   0.2832   1.0000
   9.750   1.3688   0.02328   0.01522  -0.0570   0.2772   1.0000
  10.000   1.3824   0.02395   0.01589  -0.0554   0.2718   1.0000
  10.250   1.3968   0.02465   0.01661  -0.0538   0.2668   1.0000
  10.500   1.4088   0.02534   0.01741  -0.0521   0.2614   1.0000
  10.750   1.4205   0.02611   0.01819  -0.0504   0.2562   1.0000
  11.000   1.4327   0.02691   0.01901  -0.0488   0.2512   1.0000
  11.250   1.4419   0.02777   0.02000  -0.0470   0.2452   1.0000
  11.500   1.4520   0.02867   0.02093  -0.0453   0.2403   1.0000
  11.750   1.4624   0.02963   0.02192  -0.0438   0.2355   1.0000
  12.000   1.4710   0.03065   0.02309  -0.0422   0.2300   1.0000
  12.250   1.4764   0.03188   0.02432  -0.0405   0.2237   1.0000
  12.500   1.4841   0.03308   0.02562  -0.0391   0.2181   1.0000
  12.750   1.4886   0.03450   0.02713  -0.0376   0.2110   1.0000
  13.000   1.4927   0.03603   0.02870  -0.0363   0.2047   1.0000
  13.250   1.4968   0.03766   0.03044  -0.0351   0.1970   1.0000
  13.500   1.4984   0.03956   0.03239  -0.0339   0.1892   1.0000
  13.750   1.5000   0.04157   0.03447  -0.0329   0.1809   1.0000
  14.000   1.5006   0.04377   0.03674  -0.0320   0.1716   1.0000
  14.250   1.4977   0.04641   0.03940  -0.0312   0.1620   1.0000
  14.500   1.4932   0.04935   0.04236  -0.0306   0.1509   1.0000
  14.750   1.4882   0.05247   0.04549  -0.0302   0.1390   1.0000
  15.000   1.4813   0.05592   0.04896  -0.0299   0.1278   1.0000
  15.250   1.4742   0.05951   0.05256  -0.0298   0.1187   1.0000
  15.500   1.4642   0.06353   0.05659  -0.0299   0.1113   1.0000
  15.750   1.4574   0.06728   0.06037  -0.0300   0.1055   1.0000
  16.250   1.4440   0.07497   0.06816  -0.0308   0.0981   1.0000
  16.500   1.4389   0.07871   0.07197  -0.0313   0.0956   1.0000
  16.750   1.4325   0.08267   0.07598  -0.0319   0.0933   1.0000
  17.000   1.4254   0.08678   0.08013  -0.0326   0.0913   1.0000
  17.250   1.4225   0.09035   0.08378  -0.0333   0.0895   1.0000
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