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GOE 284 AIRFOIL (goe284-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 284 AIRFOIL (goe284-il)
Reynolds number: 200,000
Max Cl/Cd: 69.48 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe284-il-200000-n5.txt
Download as CSV file: xf-goe284-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 284 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.6436   0.07044   0.06591  -0.0692   1.0000   0.0440
 -13.000  -0.7941   0.03666   0.03112  -0.1007   0.9592   0.0435
 -12.750  -0.7928   0.03444   0.02869  -0.1005   0.9415   0.0439
 -12.500  -0.7864   0.03264   0.02669  -0.0998   0.9259   0.0444
 -12.250  -0.7766   0.03127   0.02521  -0.0987   0.9107   0.0450
 -12.000  -0.7641   0.03009   0.02394  -0.0976   0.8957   0.0456
 -11.750  -0.7499   0.02898   0.02271  -0.0964   0.8807   0.0464
 -11.500  -0.7345   0.02793   0.02151  -0.0952   0.8650   0.0472
 -11.250  -0.7176   0.02692   0.02034  -0.0941   0.8479   0.0481
 -11.000  -0.6996   0.02596   0.01919  -0.0931   0.8301   0.0492
 -10.750  -0.6802   0.02518   0.01831  -0.0921   0.8115   0.0502
 -10.500  -0.6596   0.02448   0.01747  -0.0912   0.7924   0.0515
 -10.250  -0.6381   0.02378   0.01661  -0.0904   0.7735   0.0532
 -10.000  -0.6156   0.02319   0.01587  -0.0898   0.7555   0.0552
  -9.750  -0.5919   0.02273   0.01530  -0.0892   0.7386   0.0575
  -9.500  -0.5677   0.02229   0.01470  -0.0887   0.7228   0.0606
  -9.250  -0.5423   0.02200   0.01429  -0.0883   0.7079   0.0641
  -9.000  -0.5163   0.02179   0.01397  -0.0880   0.6944   0.0678
  -8.750  -0.4904   0.02148   0.01346  -0.0877   0.6825   0.0723
  -8.500  -0.4633   0.02147   0.01337  -0.0875   0.6710   0.0754
  -8.250  -0.4368   0.02119   0.01285  -0.0873   0.6612   0.0794
  -8.000  -0.4095   0.02120   0.01280  -0.0871   0.6514   0.0818
  -7.750  -0.3827   0.02104   0.01245  -0.0869   0.6432   0.0849
  -7.500  -0.3556   0.02079   0.01202  -0.0868   0.6352   0.0875
  -7.250  -0.3283   0.02074   0.01191  -0.0867   0.6282   0.0895
  -7.000  -0.3009   0.02061   0.01166  -0.0866   0.6224   0.0919
  -6.750  -0.2733   0.02038   0.01124  -0.0865   0.6166   0.0946
  -6.500  -0.2459   0.02016   0.01094  -0.0865   0.6112   0.0966
  -6.250  -0.2184   0.02007   0.01081  -0.0864   0.6066   0.0987
  -6.000  -0.1905   0.01996   0.01062  -0.0864   0.6023   0.1013
  -5.750  -0.1624   0.01976   0.01029  -0.0864   0.5979   0.1038
  -5.500  -0.1345   0.01952   0.00992  -0.0864   0.5938   0.1058
  -5.250  -0.1067   0.01928   0.00969  -0.0864   0.5899   0.1079
  -5.000  -0.0788   0.01916   0.00952  -0.0864   0.5863   0.1103
  -4.750  -0.0506   0.01900   0.00928  -0.0865   0.5828   0.1128
  -4.500  -0.0221   0.01879   0.00899  -0.0865   0.5792   0.1149
  -4.250   0.0064   0.01858   0.00869  -0.0866   0.5760   0.1164
  -4.000   0.0345   0.01822   0.00832  -0.0866   0.5729   0.1177
  -3.750   0.0626   0.01794   0.00803  -0.0867   0.5701   0.1191
  -3.500   0.0908   0.01774   0.00780  -0.0867   0.5675   0.1206
  -3.250   0.1192   0.01758   0.00759  -0.0867   0.5652   0.1222
  -3.000   0.1477   0.01739   0.00739  -0.0868   0.5627   0.1238
  -2.750   0.1762   0.01721   0.00721  -0.0869   0.5599   0.1253
  -2.500   0.2047   0.01705   0.00704  -0.0869   0.5569   0.1269
  -2.250   0.2332   0.01692   0.00688  -0.0870   0.5543   0.1285
  -2.000   0.2615   0.01676   0.00673  -0.0871   0.5519   0.1303
  -1.750   0.2897   0.01661   0.00660  -0.0871   0.5497   0.1327
  -1.500   0.3181   0.01652   0.00650  -0.0872   0.5475   0.1352
  -1.250   0.3467   0.01648   0.00642  -0.0873   0.5452   0.1378
  -1.000   0.3751   0.01641   0.00637  -0.0874   0.5424   0.1406
  -0.750   0.4034   0.01634   0.00632  -0.0874   0.5388   0.1434
  -0.500   0.4314   0.01621   0.00624  -0.0875   0.5345   0.1474
  -0.250   0.4594   0.01612   0.00616  -0.0875   0.5300   0.1527
   0.250   0.5158   0.01602   0.00608  -0.0876   0.5225   0.1680
   0.500   0.5438   0.01594   0.00611  -0.0876   0.5189   0.1819
   1.000   0.5991   0.01568   0.00619  -0.0877   0.5117   0.2646
   1.250   0.6266   0.01553   0.00621  -0.0877   0.5083   0.3261
   1.500   0.6535   0.01532   0.00625  -0.0877   0.5052   0.4143
   1.750   0.6779   0.01492   0.00642  -0.0872   0.5017   0.5639
   2.000   0.6991   0.01449   0.00662  -0.0855   0.4981   0.7411
   2.250   0.7279   0.01430   0.00678  -0.0849   0.4942   0.9014
   2.500   0.7737   0.01436   0.00682  -0.0884   0.4902   0.9809
   2.750   0.8093   0.01449   0.00684  -0.0900   0.4867   1.0000
   3.000   0.8345   0.01462   0.00698  -0.0896   0.4825   1.0000
   3.250   0.8599   0.01475   0.00711  -0.0892   0.4781   1.0000
   3.500   0.8857   0.01488   0.00721  -0.0888   0.4739   1.0000
   3.750   0.9117   0.01501   0.00727  -0.0885   0.4700   1.0000
   4.000   0.9375   0.01516   0.00739  -0.0882   0.4659   1.0000
   4.250   0.9629   0.01532   0.00759  -0.0878   0.4607   1.0000
   4.500   0.9884   0.01546   0.00771  -0.0875   0.4555   1.0000
   4.750   1.0140   0.01560   0.00779  -0.0871   0.4509   1.0000
   5.000   1.0390   0.01578   0.00801  -0.0867   0.4448   1.0000
   5.250   1.0637   0.01594   0.00818  -0.0862   0.4382   1.0000
   5.500   1.0882   0.01611   0.00830  -0.0857   0.4319   1.0000
   5.750   1.1121   0.01631   0.00854  -0.0852   0.4237   1.0000
   6.000   1.1354   0.01650   0.00868  -0.0845   0.4161   1.0000
   6.250   1.1584   0.01673   0.00893  -0.0838   0.4062   1.0000
   6.500   1.1802   0.01699   0.00916  -0.0829   0.3962   1.0000
   6.750   1.2006   0.01728   0.00940  -0.0818   0.3853   1.0000
   7.000   1.2202   0.01763   0.00971  -0.0807   0.3740   1.0000
   7.250   1.2381   0.01805   0.01006  -0.0793   0.3637   1.0000
   7.500   1.2543   0.01852   0.01047  -0.0776   0.3541   1.0000
   7.750   1.2700   0.01901   0.01094  -0.0759   0.3457   1.0000
   8.000   1.2818   0.01959   0.01147  -0.0736   0.3382   1.0000
   8.250   1.2953   0.02019   0.01205  -0.0717   0.3313   1.0000
   8.500   1.3083   0.02086   0.01271  -0.0699   0.3249   1.0000
   8.750   1.3205   0.02162   0.01343  -0.0680   0.3194   1.0000
   9.000   1.3356   0.02231   0.01415  -0.0667   0.3144   1.0000
   9.250   1.3493   0.02309   0.01493  -0.0653   0.3096   1.0000
   9.500   1.3617   0.02396   0.01579  -0.0638   0.3053   1.0000
   9.750   1.3755   0.02481   0.01666  -0.0625   0.3015   1.0000
  10.000   1.3898   0.02566   0.01756  -0.0614   0.2975   1.0000
  10.250   1.4028   0.02660   0.01854  -0.0602   0.2937   1.0000
  10.500   1.4151   0.02762   0.01957  -0.0591   0.2902   1.0000
  10.750   1.4270   0.02868   0.02062  -0.0579   0.2872   1.0000
  11.000   1.4406   0.02969   0.02170  -0.0570   0.2842   1.0000
  11.250   1.4534   0.03077   0.02286  -0.0561   0.2810   1.0000
  11.500   1.4648   0.03195   0.02410  -0.0552   0.2777   1.0000
  11.750   1.4753   0.03322   0.02541  -0.0543   0.2744   1.0000
  12.000   1.4855   0.03453   0.02672  -0.0534   0.2714   1.0000
  12.250   1.4962   0.03584   0.02809  -0.0526   0.2685   1.0000
  12.500   1.5055   0.03732   0.02968  -0.0519   0.2651   1.0000
  12.750   1.5137   0.03890   0.03135  -0.0512   0.2616   1.0000
  13.000   1.5211   0.04055   0.03305  -0.0504   0.2581   1.0000
  13.250   1.5284   0.04220   0.03471  -0.0497   0.2548   1.0000
  13.500   1.5356   0.04393   0.03650  -0.0491   0.2517   1.0000
  13.750   1.5419   0.04584   0.03855  -0.0486   0.2484   1.0000
  14.000   1.5473   0.04785   0.04066  -0.0482   0.2448   1.0000
  14.250   1.5512   0.05001   0.04286  -0.0478   0.2408   1.0000
  14.500   1.5558   0.05205   0.04490  -0.0473   0.2372   1.0000
  14.750   1.5588   0.05448   0.04749  -0.0471   0.2334   1.0000
  15.000   1.5600   0.05711   0.05024  -0.0469   0.2288   1.0000
  15.250   1.5611   0.05974   0.05291  -0.0467   0.2243   1.0000
  15.500   1.5632   0.06223   0.05545  -0.0465   0.2205   1.0000
  15.750   1.5629   0.06519   0.05856  -0.0466   0.2159   1.0000
  16.000   1.5603   0.06840   0.06185  -0.0466   0.2103   1.0000
  16.250   1.5585   0.07151   0.06501  -0.0467   0.2053   1.0000
  16.500   1.5542   0.07507   0.06871  -0.0470   0.1989   1.0000
  16.750   1.5481   0.07881   0.07248  -0.0473   0.1921   1.0000
  17.000   1.5415   0.08276   0.07656  -0.0477   0.1835   1.0000
  17.250   1.5311   0.08723   0.08109  -0.0483   0.1725   1.0000
  17.500   1.5160   0.09237   0.08625  -0.0491   0.1569   1.0000
  17.750   1.4930   0.09864   0.09244  -0.0502   0.1410   1.0000
  18.000   1.4682   0.10529   0.09904  -0.0515   0.1312   1.0000
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