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GOE 548 AIRFOIL (goe548-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 548 AIRFOIL (goe548-il)
Reynolds number: 200,000
Max Cl/Cd: 74.23 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe548-il-200000.txt
Download as CSV file: xf-goe548-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 548 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4874   0.08737   0.08412  -0.0448   1.0000   0.0591
  -9.250  -0.5048   0.08321   0.08002  -0.0451   1.0000   0.0590
  -9.000  -0.5256   0.07876   0.07564  -0.0457   1.0000   0.0581
  -8.750  -0.5613   0.07337   0.07030  -0.0475   1.0000   0.0569
  -8.500  -0.5978   0.07033   0.06724  -0.0445   1.0000   0.0558
  -8.250  -0.6225   0.06671   0.06357  -0.0423   1.0000   0.0560
  -8.000  -0.6415   0.06312   0.05987  -0.0399   1.0000   0.0564
  -7.750  -0.6573   0.05939   0.05600  -0.0374   1.0000   0.0576
  -7.500  -0.6991   0.04540   0.04091  -0.0327   0.9993   0.0357
  -7.250  -0.6800   0.04042   0.03538  -0.0342   0.9947   0.0356
  -7.000  -0.6594   0.03643   0.03083  -0.0346   0.9894   0.0360
  -6.750  -0.6345   0.03256   0.02640  -0.0353   0.9852   0.0358
  -6.500  -0.6083   0.02987   0.02321  -0.0356   0.9803   0.0366
  -6.250  -0.5775   0.02849   0.02137  -0.0363   0.9752   0.0379
  -6.000  -0.5487   0.02544   0.01814  -0.0376   0.9726   0.0417
  -5.750  -0.5201   0.02422   0.01676  -0.0380   0.9675   0.0451
  -5.500  -0.4875   0.02326   0.01553  -0.0389   0.9626   0.0489
  -5.250  -0.4543   0.02141   0.01365  -0.0404   0.9598   0.0552
  -5.000  -0.4251   0.02056   0.01270  -0.0408   0.9543   0.0610
  -4.750  -0.3962   0.01945   0.01159  -0.0414   0.9492   0.0686
  -4.500  -0.3602   0.01876   0.01084  -0.0432   0.9460   0.0767
  -4.250  -0.3351   0.01816   0.01027  -0.0430   0.9391   0.0855
  -4.000  -0.3032   0.01756   0.00968  -0.0441   0.9344   0.0970
  -3.750  -0.2668   0.01682   0.00904  -0.0460   0.9316   0.1220
  -3.500  -0.2507   0.01565   0.00867  -0.0443   0.9228   0.2751
  -3.250  -0.2182   0.01489   0.00842  -0.0456   0.9189   0.4074
  -3.000  -0.1908   0.01452   0.00826  -0.0455   0.9128   0.4780
  -2.750  -0.1627   0.01418   0.00813  -0.0455   0.9068   0.5456
  -2.500  -0.1273   0.01380   0.00794  -0.0468   0.9040   0.6116
  -2.250  -0.1049   0.01362   0.00791  -0.0455   0.8969   0.6632
  -2.000  -0.0739   0.01334   0.00779  -0.0457   0.8924   0.7185
  -1.750  -0.0368   0.01303   0.00765  -0.0470   0.8901   0.7777
  -1.500   0.0056   0.01280   0.00754  -0.0493   0.8888   0.8331
  -1.250   0.0354   0.01285   0.00765  -0.0492   0.8820   0.8756
  -1.000   0.0901   0.01282   0.00761  -0.0544   0.8804   0.9069
  -0.750   0.1454   0.01279   0.00750  -0.0598   0.8788   0.9264
  -0.500   0.2015   0.01274   0.00739  -0.0654   0.8773   0.9405
  -0.250   0.2647   0.01271   0.00731  -0.0725   0.8764   0.9498
   0.000   0.3258   0.01266   0.00721  -0.0791   0.8751   0.9597
   0.250   0.3748   0.01262   0.00715  -0.0835   0.8706   0.9702
   0.500   0.4262   0.01252   0.00704  -0.0885   0.8651   0.9777
   0.750   0.4790   0.01222   0.00672  -0.0936   0.8605   0.9843
   1.000   0.5269   0.01196   0.00646  -0.0979   0.8509   0.9921
   1.250   0.5777   0.01154   0.00603  -0.1026   0.8414   0.9985
   1.500   0.6076   0.01124   0.00572  -0.1031   0.8306   1.0000
   1.750   0.6242   0.01108   0.00555  -0.1009   0.8172   1.0000
   2.000   0.6422   0.01096   0.00542  -0.0990   0.8045   1.0000
   2.250   0.6630   0.01081   0.00525  -0.0975   0.7910   1.0000
   2.500   0.6852   0.01071   0.00514  -0.0963   0.7776   1.0000
   2.750   0.7090   0.01062   0.00501  -0.0953   0.7626   1.0000
   3.000   0.7335   0.01060   0.00491  -0.0945   0.7458   1.0000
   3.250   0.7531   0.01067   0.00496  -0.0927   0.7275   1.0000
   3.500   0.7731   0.01079   0.00505  -0.0910   0.7106   1.0000
   3.750   0.7918   0.01091   0.00514  -0.0890   0.6919   1.0000
   4.000   0.8093   0.01104   0.00523  -0.0867   0.6714   1.0000
   4.250   0.8223   0.01114   0.00529  -0.0834   0.6442   1.0000
   4.500   0.8343   0.01124   0.00537  -0.0800   0.6137   1.0000
   4.750   0.8456   0.01141   0.00543  -0.0764   0.5755   1.0000
   5.000   0.8573   0.01169   0.00555  -0.0729   0.5382   1.0000
   5.250   0.8660   0.01211   0.00575  -0.0690   0.4936   1.0000
   5.500   0.8720   0.01264   0.00602  -0.0646   0.4407   1.0000
   5.750   0.8743   0.01330   0.00636  -0.0596   0.3703   1.0000
   6.000   0.8713   0.01424   0.00681  -0.0538   0.2794   1.0000
   6.250   0.8699   0.01531   0.00743  -0.0485   0.2086   1.0000
   6.500   0.8740   0.01614   0.00799  -0.0443   0.1639   1.0000
   6.750   0.8775   0.01703   0.00854  -0.0399   0.1057   1.0000
   7.000   0.8821   0.01796   0.00921  -0.0359   0.0679   1.0000
   7.250   0.8887   0.01889   0.00992  -0.0322   0.0403   1.0000
   7.500   0.8990   0.01969   0.01073  -0.0292   0.0357   1.0000
   7.750   0.9088   0.02056   0.01170  -0.0261   0.0331   1.0000
   8.000   0.9193   0.02138   0.01264  -0.0233   0.0319   1.0000
   8.250   0.9290   0.02228   0.01365  -0.0204   0.0302   1.0000
   8.500   0.9374   0.02330   0.01475  -0.0175   0.0287   1.0000
   8.750   0.9450   0.02444   0.01596  -0.0147   0.0279   1.0000
   9.000   0.9534   0.02565   0.01724  -0.0120   0.0273   1.0000
   9.250   0.9620   0.02706   0.01870  -0.0094   0.0265   1.0000
   9.500   0.9751   0.02844   0.02015  -0.0075   0.0263   1.0000
   9.750   0.9926   0.02991   0.02167  -0.0061   0.0261   1.0000
  10.000   1.0162   0.03153   0.02337  -0.0055   0.0260   1.0000
  10.250   1.0493   0.03393   0.02585  -0.0063   0.0254   1.0000
  10.500   1.0903   0.03800   0.03018  -0.0089   0.0247   1.0000
  10.750   1.1052   0.03962   0.03200  -0.0071   0.0250   1.0000
  11.000   1.1143   0.04111   0.03377  -0.0044   0.0254   1.0000
  11.250   1.1169   0.04296   0.03608  -0.0007   0.0270   1.0000
  11.500   1.1124   0.04735   0.04108   0.0032   0.0298   1.0000
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