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GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il)
Reynolds number: 200,000
Max Cl/Cd: 88.3 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe198-il-200000.txt
Download as CSV file: xf-goe198-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 198 (L.F.G. 5294) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2835   0.12056   0.11706  -0.0302   1.0000   0.0307
  -9.500  -0.2915   0.11956   0.11611  -0.0273   1.0000   0.0309
  -9.250  -0.2986   0.11844   0.11504  -0.0249   1.0000   0.0312
  -9.000  -0.3023   0.11694   0.11357  -0.0235   0.9997   0.0316
  -8.750  -0.2863   0.11337   0.10998  -0.0272   0.9970   0.0324
  -8.500  -0.2694   0.10980   0.10640  -0.0314   0.9943   0.0333
  -8.250  -0.2542   0.10672   0.10332  -0.0360   0.9901   0.0346
  -8.000  -0.2425   0.10542   0.10201  -0.0448   0.9837   0.0352
  -7.750  -0.2248   0.10231   0.09891  -0.0534   0.9764   0.0353
  -7.500  -0.2089   0.09671   0.09330  -0.0503   0.9756   0.0357
  -7.250  -0.1877   0.09257   0.08915  -0.0530   0.9730   0.0363
  -7.000  -0.1624   0.08871   0.08527  -0.0582   0.9706   0.0372
  -6.750  -0.1456   0.08572   0.08227  -0.0616   0.9642   0.0380
  -6.500  -0.1187   0.08207   0.07860  -0.0679   0.9602   0.0394
  -6.250  -0.0536   0.07882   0.07516  -0.0924   0.9563   0.0417
  -6.000  -0.0463   0.07499   0.07138  -0.0905   0.9503   0.0420
  -5.750  -0.0304   0.07122   0.06762  -0.0899   0.9471   0.0425
  -5.500  -0.0045   0.06783   0.06421  -0.0931   0.9442   0.0434
  -5.250   0.0278   0.06449   0.06083  -0.0985   0.9417   0.0448
  -5.000   0.0497   0.06203   0.05834  -0.1017   0.9347   0.0464
  -4.750   0.1200   0.05898   0.05497  -0.1197   0.9298   0.0493
  -4.500   0.1333   0.05505   0.05112  -0.1184   0.9269   0.0500
  -4.250   0.1501   0.05269   0.04878  -0.1182   0.9208   0.0510
  -4.000   0.1771   0.05026   0.04630  -0.1206   0.9148   0.0527
  -3.750   0.2150   0.04752   0.04344  -0.1254   0.9106   0.0555
  -3.500   0.2679   0.04500   0.04057  -0.1338   0.9028   0.0584
  -3.250   0.2869   0.04214   0.03776  -0.1336   0.8969   0.0592
  -3.000   0.3104   0.04008   0.03567  -0.1342   0.8910   0.0607
  -2.750   0.3384   0.03822   0.03374  -0.1356   0.8837   0.0633
  -2.500   0.3894   0.03628   0.03132  -0.1407   0.8791   0.0687
  -2.250   0.4082   0.03395   0.02910  -0.1405   0.8708   0.0700
  -2.000   0.4346   0.03224   0.02735  -0.1410   0.8646   0.0727
  -1.750   0.4785   0.03194   0.02648  -0.1432   0.8577   0.0798
  -1.500   0.5018   0.02882   0.02349  -0.1439   0.8504   0.0813
  -1.250   0.5287   0.02724   0.02188  -0.1441   0.8438   0.0839
  -0.750   0.5910   0.02438   0.01864  -0.1453   0.8289   0.0955
  -0.500   0.6192   0.02331   0.01750  -0.1455   0.8187   0.1019
  -0.250   0.6494   0.02196   0.01597  -0.1458   0.8105   0.1109
   0.000   0.6781   0.02094   0.01485  -0.1460   0.8009   0.1260
   0.750   0.7753   0.01692   0.00985  -0.1453   0.7711   0.0739
   1.000   0.8052   0.01628   0.00885  -0.1446   0.7596   0.0679
   1.250   0.8338   0.01549   0.00793  -0.1443   0.7478   0.0678
   1.500   0.8618   0.01475   0.00715  -0.1441   0.7350   0.0713
   1.750   0.8894   0.01433   0.00667  -0.1436   0.7194   0.0746
   2.000   0.9167   0.01396   0.00623  -0.1431   0.7012   0.0775
   2.250   0.9440   0.01355   0.00580  -0.1427   0.6816   0.0828
   2.500   0.9712   0.01327   0.00550  -0.1424   0.6619   0.0961
   2.750   0.9987   0.01297   0.00524  -0.1422   0.6432   0.1458
   3.000   1.0177   0.01162   0.00522  -0.1401   0.6261   1.0000
   3.250   1.0440   0.01186   0.00525  -0.1396   0.6080   1.0000
   3.500   1.0700   0.01212   0.00535  -0.1391   0.5898   1.0000
   3.750   1.0958   0.01241   0.00549  -0.1387   0.5720   1.0000
   4.000   1.1213   0.01272   0.00568  -0.1382   0.5544   1.0000
   4.250   1.1463   0.01307   0.00590  -0.1376   0.5350   1.0000
   4.500   1.1708   0.01344   0.00614  -0.1370   0.5151   1.0000
   4.750   1.1951   0.01381   0.00640  -0.1363   0.4952   1.0000
   5.000   1.2193   0.01413   0.00668  -0.1357   0.4732   1.0000
   5.250   1.2429   0.01449   0.00695  -0.1350   0.4503   1.0000
   5.500   1.2662   0.01485   0.00722  -0.1342   0.4269   1.0000
   5.750   1.2890   0.01526   0.00753  -0.1334   0.4048   1.0000
   6.000   1.3114   0.01571   0.00789  -0.1325   0.3871   1.0000
   6.250   1.3338   0.01618   0.00829  -0.1317   0.3725   1.0000
   6.500   1.3563   0.01665   0.00872  -0.1308   0.3599   1.0000
   6.750   1.3780   0.01717   0.00918  -0.1299   0.3468   1.0000
   7.000   1.3995   0.01770   0.00968  -0.1290   0.3364   1.0000
   7.250   1.4217   0.01816   0.01017  -0.1281   0.3263   1.0000
   7.500   1.4434   0.01864   0.01068  -0.1272   0.3170   1.0000
   8.000   1.4846   0.01963   0.01174  -0.1250   0.2941   1.0000
   8.250   1.5041   0.02011   0.01227  -0.1237   0.2795   1.0000
   8.500   1.5223   0.02063   0.01281  -0.1222   0.2618   1.0000
   8.750   1.5386   0.02122   0.01339  -0.1204   0.2352   1.0000
   9.000   1.5453   0.02237   0.01426  -0.1173   0.1827   1.0000
   9.250   1.5428   0.02409   0.01563  -0.1129   0.1362   1.0000
   9.500   1.5445   0.02571   0.01707  -0.1093   0.1088   1.0000
   9.750   1.5504   0.02712   0.01842  -0.1065   0.0973   1.0000
  10.000   1.5567   0.02853   0.01983  -0.1039   0.0908   1.0000
  10.250   1.5644   0.02988   0.02125  -0.1016   0.0864   1.0000
  10.500   1.5688   0.03152   0.02295  -0.0992   0.0825   1.0000
  10.750   1.5728   0.03324   0.02474  -0.0968   0.0793   1.0000
  11.000   1.5782   0.03490   0.02652  -0.0947   0.0765   1.0000
  11.250   1.5806   0.03687   0.02857  -0.0926   0.0737   1.0000
  11.500   1.5782   0.03931   0.03105  -0.0901   0.0710   1.0000
  11.750   1.5769   0.04174   0.03357  -0.0880   0.0686   1.0000
  12.000   1.5792   0.04393   0.03590  -0.0862   0.0659   1.0000
  12.250   1.5776   0.04653   0.03861  -0.0844   0.0630   1.0000
  12.500   1.5705   0.04974   0.04181  -0.0822   0.0600   1.0000
  12.750   1.5690   0.05252   0.04473  -0.0805   0.0564   1.0000
  13.000   1.5667   0.05543   0.04772  -0.0790   0.0524   1.0000
  13.250   1.5642   0.05839   0.05062  -0.0768   0.0484   1.0000
  13.500   1.5634   0.06129   0.05372  -0.0760   0.0450   1.0000
  13.750   1.5643   0.06400   0.05647  -0.0750   0.0424   1.0000
  14.000   1.5686   0.06635   0.05881  -0.0733   0.0400   1.0000
  14.250   1.5692   0.06929   0.06198  -0.0728   0.0382   1.0000
  14.500   1.5701   0.07221   0.06505  -0.0722   0.0364   1.0000
  14.750   1.5712   0.07511   0.06803  -0.0719   0.0351   1.0000
  15.000   1.5733   0.07785   0.07078  -0.0715   0.0339   1.0000
  15.250   1.5745   0.08084   0.07391  -0.0709   0.0327   1.0000
  15.500   1.5736   0.08425   0.07755  -0.0709   0.0316   1.0000
  15.750   1.5727   0.08766   0.08114  -0.0709   0.0305   1.0000
  16.000   1.5723   0.09102   0.08464  -0.0710   0.0297   1.0000
  16.250   1.5715   0.09444   0.08819  -0.0714   0.0291   1.0000
  16.500   1.5715   0.09776   0.09159  -0.0718   0.0285   1.0000
  16.750   1.5730   0.10079   0.09467  -0.0720   0.0279   1.0000
  17.000   1.5723   0.10421   0.09823  -0.0718   0.0274   1.0000
  17.250   1.5653   0.10894   0.10322  -0.0729   0.0270   1.0000
  17.500   1.5566   0.11406   0.10861  -0.0743   0.0267   1.0000
  17.750   1.5461   0.11965   0.11445  -0.0764   0.0264   1.0000
  18.000   1.5342   0.12564   0.12070  -0.0790   0.0261   1.0000
  18.250   1.5208   0.13214   0.12744  -0.0822   0.0259   1.0000
  18.500   1.5056   0.13923   0.13476  -0.0861   0.0258   1.0000
  18.750   1.4885   0.14706   0.14283  -0.0909   0.0257   1.0000
  19.000   1.4685   0.15602   0.15204  -0.0967   0.0257   1.0000
  19.250   1.4454   0.16632   0.16258  -0.1039   0.0259   1.0000
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