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GOE 534 AIRFOIL (goe534-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 534 AIRFOIL (goe534-il)
Reynolds number: 200,000
Max Cl/Cd: 65.44 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe534-il-200000.txt
Download as CSV file: xf-goe534-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 534 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2355   0.09247   0.08898  -0.0302   1.0000   0.0885
  -8.500  -0.2367   0.09005   0.08663  -0.0302   1.0000   0.0903
  -8.250  -0.4164   0.03298   0.02826  -0.0920   0.9703   0.0665
  -8.000  -0.3850   0.02823   0.02275  -0.0975   0.9600   0.0691
  -7.750  -0.3436   0.02759   0.02222  -0.1001   0.9538   0.0711
  -7.500  -0.3081   0.02555   0.01983  -0.1027   0.9441   0.0742
  -7.250  -0.2702   0.02358   0.01754  -0.1055   0.9361   0.0776
  -7.000  -0.2357   0.02278   0.01671  -0.1067   0.9237   0.0812
  -6.750  -0.2011   0.02143   0.01512  -0.1082   0.9119   0.0865
  -6.500  -0.1653   0.02074   0.01426  -0.1095   0.8999   0.0926
  -6.250  -0.1359   0.01982   0.01331  -0.1097   0.8842   0.0978
  -6.000  -0.1067   0.01941   0.01264  -0.1095   0.8682   0.1037
  -5.750  -0.0792   0.01865   0.01189  -0.1092   0.8527   0.1082
  -5.500  -0.0515   0.01838   0.01147  -0.1087   0.8372   0.1131
  -5.250  -0.0248   0.01786   0.01070  -0.1080   0.8218   0.1170
  -5.000   0.0008   0.01742   0.01028  -0.1071   0.8053   0.1205
  -4.750   0.0269   0.01715   0.00989  -0.1063   0.7892   0.1241
  -4.500   0.0533   0.01698   0.00951  -0.1055   0.7733   0.1277
  -4.250   0.0790   0.01648   0.00895  -0.1047   0.7578   0.1319
  -4.000   0.1052   0.01631   0.00871  -0.1038   0.7416   0.1363
  -3.750   0.1313   0.01606   0.00833  -0.1030   0.7246   0.1394
  -3.500   0.1577   0.01582   0.00793  -0.1021   0.7079   0.1416
  -3.250   0.1839   0.01536   0.00739  -0.1013   0.6919   0.1439
  -3.000   0.2101   0.01502   0.00699  -0.1005   0.6762   0.1461
  -2.750   0.2365   0.01477   0.00666  -0.0997   0.6606   0.1484
  -2.500   0.2629   0.01453   0.00638  -0.0989   0.6442   0.1512
  -2.250   0.2895   0.01434   0.00610  -0.0981   0.6286   0.1544
  -2.000   0.3160   0.01414   0.00582  -0.0973   0.6138   0.1583
  -1.750   0.3423   0.01396   0.00561  -0.0966   0.6001   0.1640
  -1.500   0.3689   0.01384   0.00543  -0.0959   0.5861   0.1714
  -1.250   0.3954   0.01368   0.00531  -0.0952   0.5734   0.1831
  -1.000   0.4220   0.01355   0.00520  -0.0945   0.5622   0.2094
  -0.750   0.4483   0.01340   0.00527  -0.0939   0.5503   0.2689
  -0.500   0.4751   0.01352   0.00540  -0.0933   0.5400   0.3107
  -0.250   0.5019   0.01368   0.00550  -0.0927   0.5293   0.3383
   0.000   0.5288   0.01386   0.00563  -0.0920   0.5193   0.3596
   0.250   0.5554   0.01401   0.00576  -0.0914   0.5093   0.3776
   0.500   0.5821   0.01417   0.00592  -0.0908   0.5000   0.3937
   0.750   0.6087   0.01430   0.00603  -0.0901   0.4905   0.4088
   1.000   0.6353   0.01449   0.00618  -0.0895   0.4815   0.4256
   1.250   0.6616   0.01461   0.00630  -0.0888   0.4718   0.4423
   1.500   0.6881   0.01481   0.00643  -0.0882   0.4631   0.4592
   1.750   0.7141   0.01489   0.00656  -0.0875   0.4537   0.4754
   2.000   0.7404   0.01505   0.00668  -0.0868   0.4453   0.4914
   2.250   0.7660   0.01510   0.00680  -0.0860   0.4355   0.5084
   2.500   0.7919   0.01525   0.00689  -0.0854   0.4269   0.5264
   2.750   0.8171   0.01527   0.00702  -0.0846   0.4171   0.5457
   3.000   0.8430   0.01542   0.00711  -0.0839   0.4087   0.5677
   3.250   0.8680   0.01541   0.00725  -0.0831   0.3987   0.5916
   3.500   0.8932   0.01548   0.00733  -0.0824   0.3901   0.6208
   3.750   0.9186   0.01534   0.00746  -0.0817   0.3801   0.6744
   4.000   0.9639   0.01515   0.00760  -0.0850   0.3695   1.0000
   4.250   0.9894   0.01538   0.00777  -0.0844   0.3599   1.0000
   4.500   1.0146   0.01572   0.00798  -0.0837   0.3514   1.0000
   4.750   1.0393   0.01598   0.00820  -0.0830   0.3425   1.0000
   5.000   1.0641   0.01637   0.00845  -0.0822   0.3348   1.0000
   5.250   1.0882   0.01664   0.00873  -0.0814   0.3262   1.0000
   5.750   1.1364   0.01737   0.00933  -0.0798   0.3114   1.0000
   6.000   1.1602   0.01773   0.00961  -0.0789   0.3046   1.0000
   6.250   1.1839   0.01817   0.01001  -0.0781   0.2981   1.0000
   6.500   1.2071   0.01851   0.01037  -0.0772   0.2913   1.0000
   6.750   1.2308   0.01900   0.01072  -0.0764   0.2856   1.0000
   7.000   1.2534   0.01942   0.01120  -0.0755   0.2797   1.0000
   7.250   1.2758   0.01981   0.01159  -0.0745   0.2738   1.0000
   7.500   1.2992   0.02037   0.01201  -0.0737   0.2684   1.0000
   7.750   1.3204   0.02080   0.01254  -0.0726   0.2631   1.0000
   8.000   1.3418   0.02124   0.01300  -0.0715   0.2577   1.0000
   8.250   1.3641   0.02178   0.01344  -0.0707   0.2527   1.0000
   8.500   1.3846   0.02233   0.01405  -0.0695   0.2477   1.0000
   8.750   1.4042   0.02280   0.01458  -0.0682   0.2426   1.0000
   9.000   1.4246   0.02332   0.01505  -0.0671   0.2379   1.0000
   9.250   1.4452   0.02401   0.01572  -0.0661   0.2332   1.0000
   9.500   1.4618   0.02452   0.01634  -0.0644   0.2283   1.0000
   9.750   1.4795   0.02504   0.01686  -0.0629   0.2237   1.0000
  10.000   1.5015   0.02584   0.01752  -0.0623   0.2189   1.0000
  10.250   1.5132   0.02639   0.01825  -0.0599   0.2148   1.0000
  10.500   1.5263   0.02696   0.01890  -0.0579   0.2104   1.0000
  10.750   1.5400   0.02756   0.01947  -0.0559   0.2063   1.0000
  11.000   1.5564   0.02842   0.02029  -0.0545   0.2023   1.0000
  11.250   1.5622   0.02913   0.02117  -0.0516   0.1985   1.0000
  11.500   1.5713   0.02987   0.02196  -0.0493   0.1946   1.0000
  11.750   1.5833   0.03064   0.02271  -0.0475   0.1910   1.0000
  12.000   1.5967   0.03165   0.02371  -0.0461   0.1873   1.0000
  12.250   1.5993   0.03272   0.02496  -0.0436   0.1838   1.0000
  12.500   1.6053   0.03377   0.02609  -0.0416   0.1802   1.0000
  12.750   1.6141   0.03480   0.02712  -0.0401   0.1770   1.0000
  13.000   1.6276   0.03594   0.02821  -0.0390   0.1734   1.0000
  13.250   1.6262   0.03757   0.03005  -0.0371   0.1706   1.0000
  13.500   1.6287   0.03915   0.03174  -0.0357   0.1673   1.0000
  13.750   1.6344   0.04059   0.03322  -0.0346   0.1643   1.0000
  14.000   1.6466   0.04180   0.03435  -0.0338   0.1613   1.0000
  14.250   1.6464   0.04390   0.03660  -0.0328   0.1585   1.0000
  14.500   1.6427   0.04628   0.03916  -0.0320   0.1557   1.0000
  14.750   1.6431   0.04842   0.04140  -0.0314   0.1529   1.0000
  15.000   1.6476   0.05026   0.04325  -0.0309   0.1502   1.0000
  15.250   1.6627   0.05141   0.04429  -0.0302   0.1472   1.0000
  15.500   1.6498   0.05499   0.04812  -0.0301   0.1451   1.0000
  15.750   1.6416   0.05834   0.05166  -0.0303   0.1427   1.0000
  16.000   1.6385   0.06128   0.05469  -0.0304   0.1402   1.0000
  16.250   1.6420   0.06354   0.05698  -0.0305   0.1380   1.0000
  16.500   1.6584   0.06444   0.05777  -0.0298   0.1354   1.0000
  16.750   1.6446   0.06889   0.06243  -0.0307   0.1336   1.0000
  17.000   1.6258   0.07418   0.06797  -0.0323   0.1318   1.0000
  17.250   1.6113   0.07917   0.07314  -0.0339   0.1298   1.0000
  17.500   1.6044   0.08325   0.07733  -0.0351   0.1278   1.0000
  17.750   1.6093   0.08565   0.07974  -0.0356   0.1259   1.0000
  18.000   1.6302   0.08575   0.07973  -0.0346   0.1239   1.0000
  18.250   1.6071   0.09235   0.08655  -0.0373   0.1224   1.0000
  18.500   1.5564   0.10367   0.09824  -0.0429   0.1210   1.0000
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