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GOE 298 AIRFOIL (goe298-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 298 AIRFOIL (goe298-il)
Reynolds number: 50,000
Max Cl/Cd: 27.64 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe298-il-50000.txt
Download as CSV file: xf-goe298-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 298 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2694   0.12047   0.11293  -0.0203   1.0000   0.1999
  -9.000  -0.2846   0.12120   0.11377  -0.0231   1.0000   0.2050
  -8.750  -0.2779   0.11737   0.11002  -0.0239   1.0000   0.2074
  -8.500  -0.2515   0.11220   0.10487  -0.0227   1.0000   0.2133
  -8.250  -0.2496   0.11041   0.10317  -0.0234   1.0000   0.2208
  -8.000  -0.2842   0.11301   0.10598  -0.0251   1.0000   0.2247
  -7.750  -0.2465   0.10555   0.09852  -0.0237   1.0000   0.2298
  -7.500  -0.2416   0.10335   0.09641  -0.0224   1.0000   0.2360
  -7.250  -0.2629   0.10365   0.09689  -0.0197   1.0000   0.2411
  -7.000  -0.3041   0.10573   0.09917  -0.0148   1.0000   0.2430
  -6.750  -0.3485   0.10786   0.10148  -0.0104   1.0000   0.2439
  -6.500  -0.3484   0.10455   0.09826  -0.0076   1.0000   0.2465
  -6.250  -0.3315   0.10113   0.09488  -0.0049   1.0000   0.2526
  -6.000  -0.3502   0.10075   0.09460  -0.0016   1.0000   0.2574
  -5.750  -0.3837   0.10155   0.09552  -0.0009   1.0000   0.2627
  -5.500  -0.3988   0.09985   0.09391  -0.0005   1.0000   0.2662
  -5.250  -0.3884   0.09697   0.09109   0.0040   1.0000   0.2726
  -5.000  -0.4050   0.09648   0.09065   0.0032   1.0000   0.2823
  -4.750  -0.4102   0.09400   0.08824   0.0040   1.0000   0.2878
  -4.250  -0.3756   0.08818   0.08243   0.0009   0.9898   0.3131
  -4.000  -0.3575   0.08529   0.07953  -0.0032   0.9828   0.3302
  -3.750  -0.3401   0.08266   0.07691  -0.0054   0.9760   0.3498
  -3.500  -0.3211   0.08007   0.07433  -0.0064   0.9694   0.3716
  -3.250  -0.3054   0.07778   0.07205  -0.0068   0.9631   0.3953
  -3.000  -0.2953   0.07577   0.07006  -0.0080   0.9572   0.4261
  -2.750  -0.2790   0.07341   0.06775  -0.0054   0.9528   0.4533
  -2.500  -0.2755   0.07168   0.06608  -0.0017   0.9486   0.4906
  -2.250  -0.2728   0.07005   0.06453   0.0043   0.9439   0.5343
  -1.500  -0.0521   0.05969   0.05415   0.0042   0.9247   0.8461
  -1.250  -0.0754   0.05910   0.05361   0.0080   0.9170   0.8315
  -1.000   0.0671   0.05196   0.04398  -0.0792   0.8955   0.2891
  -0.750   0.1315   0.04984   0.04140  -0.0867   0.8813   0.2788
  -0.500   0.1714   0.04856   0.03984  -0.0898   0.8678   0.2765
  -0.250   0.2074   0.04779   0.03881  -0.0922   0.8566   0.2769
   0.000   0.2619   0.04676   0.03746  -0.0969   0.8461   0.2789
   0.250   0.2844   0.04671   0.03720  -0.0970   0.8342   0.2818
   0.500   0.3319   0.04609   0.03633  -0.1001   0.8232   0.2853
   0.750   0.3632   0.04574   0.03601  -0.1008   0.8102   0.2918
   1.000   0.3922   0.04575   0.03593  -0.1012   0.7964   0.2977
   1.250   0.4389   0.04531   0.03529  -0.1033   0.7837   0.3056
   1.500   0.4809   0.04478   0.03478  -0.1046   0.7695   0.3170
   1.750   0.5093   0.04492   0.03480  -0.1042   0.7529   0.3256
   2.000   0.5423   0.04475   0.03470  -0.1041   0.7365   0.3394
   2.250   0.5821   0.04422   0.03423  -0.1043   0.7210   0.3598
   2.500   0.6322   0.04265   0.03287  -0.1048   0.7087   0.3943
   2.750   0.6579   0.04214   0.03284  -0.1035   0.6905   0.4546
   3.000   0.6758   0.04110   0.03279  -0.0999   0.6729   1.0000
   3.250   0.7032   0.04150   0.03281  -0.0985   0.6552   1.0000
   3.500   0.7309   0.04179   0.03290  -0.0972   0.6388   1.0000
   3.750   0.7783   0.04041   0.03129  -0.0964   0.6292   1.0000
   4.000   0.7975   0.04130   0.03210  -0.0949   0.6118   1.0000
   4.250   0.8159   0.04232   0.03305  -0.0935   0.5952   1.0000
   4.500   0.8352   0.04333   0.03401  -0.0922   0.5803   1.0000
   4.750   0.8856   0.04128   0.03180  -0.0912   0.5724   1.0000
   5.000   0.8980   0.04285   0.03337  -0.0897   0.5562   1.0000
   5.250   0.9122   0.04428   0.03478  -0.0882   0.5411   1.0000
   5.500   0.9740   0.04073   0.03101  -0.0872   0.5332   1.0000
   5.750   0.9871   0.04205   0.03236  -0.0855   0.5168   1.0000
   6.000   1.0010   0.04334   0.03366  -0.0839   0.5014   1.0000
   6.250   1.0288   0.04323   0.03350  -0.0825   0.4880   1.0000
   6.500   1.0770   0.04109   0.03116  -0.0816   0.4763   1.0000
   6.750   1.0857   0.04287   0.03305  -0.0798   0.4611   1.0000
   7.000   1.1004   0.04412   0.03434  -0.0782   0.4472   1.0000
   7.250   1.1323   0.04368   0.03382  -0.0771   0.4344   1.0000
   7.500   1.1731   0.04244   0.03240  -0.0764   0.4216   1.0000
   7.750   1.1804   0.04437   0.03445  -0.0745   0.4076   1.0000
   8.000   1.1948   0.04572   0.03584  -0.0728   0.3946   1.0000
   8.250   1.2258   0.04571   0.03573  -0.0719   0.3823   1.0000
   8.500   1.2606   0.04560   0.03546  -0.0714   0.3704   1.0000
   8.750   1.2508   0.04944   0.03957  -0.0689   0.3598   1.0000
   9.000   1.2905   0.04937   0.03928  -0.0688   0.3496   1.0000
   9.250   1.2565   0.05519   0.04551  -0.0654   0.3416   1.0000
   9.500   1.3153   0.05395   0.04399  -0.0662   0.3323   1.0000
   9.750   1.1767   0.06916   0.05981  -0.0611   0.3304   1.0000
  10.000   0.8113   0.13236   0.12335  -0.0924   0.3934   1.0000
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