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GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il)
Reynolds number: 200,000
Max Cl/Cd: 80.37 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe198-il-200000-n5.txt
Download as CSV file: xf-goe198-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1451   0.09222   0.08847  -0.0614   0.9338   0.0300
  -7.750  -0.1348   0.08959   0.08582  -0.0631   0.9276   0.0307
  -7.500  -0.1263   0.08718   0.08341  -0.0648   0.9205   0.0319
  -7.250  -0.1134   0.08492   0.08111  -0.0703   0.9138   0.0330
  -7.000  -0.0963   0.08227   0.07843  -0.0769   0.9066   0.0331
  -6.750  -0.0754   0.07924   0.07533  -0.0836   0.9007   0.0332
  -6.500  -0.0647   0.07576   0.07184  -0.0823   0.8968   0.0335
  -6.250  -0.0523   0.07284   0.06893  -0.0819   0.8914   0.0338
  -6.000  -0.0364   0.07017   0.06624  -0.0833   0.8860   0.0343
  -5.750  -0.0178   0.06754   0.06357  -0.0857   0.8812   0.0350
  -5.500   0.0031   0.06493   0.06094  -0.0888   0.8752   0.0362
  -5.250   0.0317   0.06208   0.05802  -0.0946   0.8703   0.0386
  -5.000   0.0796   0.05865   0.05435  -0.1066   0.8662   0.0394
  -4.750   0.1035   0.05535   0.05103  -0.1095   0.8609   0.0396
  -4.500   0.1195   0.05270   0.04840  -0.1092   0.8561   0.0400
  -4.250   0.1412   0.05031   0.04596  -0.1104   0.8518   0.0407
  -4.000   0.1673   0.04798   0.04359  -0.1127   0.8457   0.0417
  -3.750   0.1972   0.04556   0.04108  -0.1158   0.8397   0.0432
  -3.500   0.2505   0.04226   0.03743  -0.1243   0.8349   0.0465
  -3.250   0.2711   0.03998   0.03518  -0.1248   0.8276   0.0471
  -3.000   0.2975   0.03796   0.03309  -0.1261   0.8218   0.0480
  -2.750   0.3274   0.03599   0.03104  -0.1280   0.8150   0.0493
  -2.500   0.3610   0.03395   0.02886  -0.1304   0.8078   0.0515
  -2.250   0.4101   0.03168   0.02603  -0.1347   0.8022   0.0537
  -1.500   0.5082   0.02326   0.01697  -0.1396   0.7797   0.0392
  -1.250   0.5381   0.02185   0.01540  -0.1404   0.7713   0.0385
  -1.000   0.5693   0.02038   0.01372  -0.1412   0.7610   0.0378
  -0.750   0.6010   0.01892   0.01198  -0.1419   0.7518   0.0373
  -0.500   0.6321   0.01760   0.01036  -0.1423   0.7412   0.0371
  -0.250   0.6625   0.01648   0.00896  -0.1426   0.7289   0.0372
   0.000   0.6920   0.01559   0.00779  -0.1426   0.7153   0.0378
   0.250   0.7207   0.01496   0.00688  -0.1425   0.6990   0.0393
   0.500   0.7487   0.01444   0.00622  -0.1424   0.6811   0.0402
   0.750   0.7765   0.01406   0.00572  -0.1422   0.6639   0.0408
   1.000   0.8041   0.01379   0.00535  -0.1420   0.6467   0.0416
   1.250   0.8312   0.01361   0.00506  -0.1417   0.6268   0.0427
   1.500   0.8581   0.01351   0.00484  -0.1414   0.6046   0.0441
   1.750   0.8847   0.01349   0.00469  -0.1411   0.5838   0.0458
   2.000   0.9110   0.01359   0.00472  -0.1408   0.5649   0.0495
   2.250   0.9375   0.01370   0.00474  -0.1406   0.5485   0.0542
   2.500   0.9638   0.01384   0.00480  -0.1402   0.5313   0.0611
   2.750   0.9897   0.01399   0.00489  -0.1399   0.5134   0.0756
   3.000   1.0157   0.01414   0.00498  -0.1396   0.4963   0.0950
   3.250   1.0417   0.01425   0.00515  -0.1393   0.4786   0.1356
   4.250   1.1340   0.01411   0.00592  -0.1358   0.3878   1.0000
   4.500   1.1571   0.01458   0.00620  -0.1351   0.3661   1.0000
   5.000   1.2043   0.01542   0.00686  -0.1338   0.3385   1.0000
   5.250   1.2275   0.01587   0.00722  -0.1331   0.3256   1.0000
   5.500   1.2501   0.01635   0.00761  -0.1324   0.3125   1.0000
   5.750   1.2724   0.01684   0.00802  -0.1315   0.3000   1.0000
   6.000   1.2955   0.01724   0.00841  -0.1309   0.2871   1.0000
   6.250   1.3185   0.01764   0.00880  -0.1301   0.2753   1.0000
   6.500   1.3410   0.01806   0.00920  -0.1294   0.2642   1.0000
   6.750   1.3632   0.01848   0.00963  -0.1285   0.2520   1.0000
   7.000   1.3853   0.01890   0.01005  -0.1277   0.2383   1.0000
   7.250   1.4047   0.01949   0.01055  -0.1265   0.2118   1.0000
   7.500   1.4201   0.02037   0.01121  -0.1247   0.1764   1.0000
   7.750   1.4337   0.02138   0.01205  -0.1227   0.1459   1.0000
   8.250   1.4495   0.02402   0.01425  -0.1170   0.0773   1.0000
   8.500   1.4620   0.02484   0.01510  -0.1147   0.0734   1.0000
   8.750   1.4750   0.02567   0.01598  -0.1126   0.0713   1.0000
   9.000   1.4871   0.02660   0.01699  -0.1105   0.0691   1.0000
   9.250   1.4978   0.02765   0.01811  -0.1083   0.0668   1.0000
   9.500   1.5071   0.02885   0.01937  -0.1061   0.0646   1.0000
   9.750   1.5172   0.03001   0.02063  -0.1041   0.0630   1.0000
  10.000   1.5275   0.03118   0.02191  -0.1022   0.0613   1.0000
  10.250   1.5362   0.03252   0.02337  -0.1003   0.0596   1.0000
  10.500   1.5429   0.03404   0.02500  -0.0983   0.0578   1.0000
  10.750   1.5474   0.03579   0.02684  -0.0963   0.0564   1.0000
  11.000   1.5496   0.03780   0.02894  -0.0942   0.0551   1.0000
  11.250   1.5512   0.03991   0.03114  -0.0922   0.0540   1.0000
  11.500   1.5601   0.04141   0.03279  -0.0908   0.0528   1.0000
  11.750   1.5672   0.04313   0.03466  -0.0895   0.0509   1.0000
  12.000   1.5718   0.04512   0.03676  -0.0881   0.0491   1.0000
  12.250   1.5739   0.04741   0.03916  -0.0867   0.0474   1.0000
  12.500   1.5714   0.05025   0.04208  -0.0853   0.0460   1.0000
  12.750   1.5777   0.05225   0.04423  -0.0844   0.0442   1.0000
  13.000   1.5847   0.05421   0.04638  -0.0836   0.0418   1.0000
  13.250   1.5891   0.05652   0.04881  -0.0830   0.0394   1.0000
  13.500   1.5950   0.05874   0.05118  -0.0824   0.0365   1.0000
  13.750   1.6025   0.06082   0.05339  -0.0820   0.0326   1.0000
  14.000   1.6074   0.06327   0.05597  -0.0816   0.0283   1.0000
  14.250   1.6093   0.06616   0.05894  -0.0814   0.0252   1.0000
  14.500   1.6091   0.06943   0.06225  -0.0814   0.0231   1.0000
  14.750   1.6056   0.07323   0.06613  -0.0815   0.0218   1.0000
  15.000   1.6003   0.07738   0.07037  -0.0818   0.0208   1.0000
  15.250   1.5935   0.08182   0.07491  -0.0823   0.0200   1.0000
  15.500   1.5856   0.08651   0.07969  -0.0829   0.0193   1.0000
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