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GOE 565 AIRFOIL (goe565-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 565 AIRFOIL (goe565-il)
Reynolds number: 100,000
Max Cl/Cd: 55.04 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe565-il-100000-n5.txt
Download as CSV file: xf-goe565-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 565 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4405   0.08904   0.08390  -0.0342   1.0000   0.0333
  -8.750  -0.4462   0.08500   0.07995  -0.0354   1.0000   0.0333
  -8.500  -0.4547   0.08105   0.07610  -0.0363   1.0000   0.0334
  -8.250  -0.4662   0.07741   0.07258  -0.0368   1.0000   0.0333
  -8.000  -0.4773   0.07294   0.06820  -0.0387   1.0000   0.0333
  -7.750  -0.4866   0.06757   0.06287  -0.0419   1.0000   0.0333
  -7.500  -0.4957   0.06101   0.05628  -0.0455   1.0000   0.0334
  -7.250  -0.5044   0.05365   0.04874  -0.0486   1.0000   0.0338
  -7.000  -0.5119   0.04547   0.04004  -0.0509   1.0000   0.0351
  -6.750  -0.5083   0.04038   0.03448  -0.0511   1.0000   0.0368
  -6.500  -0.4949   0.03899   0.03302  -0.0501   1.0000   0.0383
  -6.250  -0.4820   0.03622   0.02993  -0.0494   1.0000   0.0401
  -6.000  -0.4672   0.03313   0.02629  -0.0489   1.0000   0.0438
  -5.750  -0.4506   0.03008   0.02256  -0.0482   1.0000   0.0472
  -5.500  -0.4324   0.02861   0.02096  -0.0474   1.0000   0.0496
  -5.250  -0.4043   0.02738   0.01944  -0.0483   0.9974   0.0544
  -5.000  -0.3719   0.02552   0.01694  -0.0496   0.9939   0.0583
  -4.750  -0.3413   0.02415   0.01543  -0.0509   0.9900   0.0624
  -4.500  -0.3083   0.02302   0.01404  -0.0523   0.9866   0.0653
  -4.250  -0.2769   0.02193   0.01271  -0.0532   0.9824   0.0678
  -4.000  -0.2438   0.02114   0.01164  -0.0543   0.9785   0.0715
  -3.750  -0.2123   0.02033   0.01080  -0.0554   0.9744   0.0746
  -3.500  -0.1803   0.01966   0.01008  -0.0564   0.9698   0.0771
  -3.250  -0.1471   0.01907   0.00943  -0.0576   0.9658   0.0802
  -3.000  -0.1162   0.01858   0.00883  -0.0583   0.9602   0.0834
  -2.750  -0.0807   0.01809   0.00836  -0.0600   0.9562   0.0885
  -2.500  -0.0496   0.01774   0.00795  -0.0607   0.9487   0.0963
  -2.250  -0.0141   0.01725   0.00746  -0.0623   0.9432   0.1052
  -2.000   0.0179   0.01679   0.00703  -0.0631   0.9360   0.1192
  -1.750   0.0533   0.01620   0.00664  -0.0648   0.9313   0.1567
  -1.500   0.0821   0.01555   0.00656  -0.0654   0.9241   0.2984
  -1.250   0.1181   0.01504   0.00645  -0.0671   0.9199   0.4121
  -1.000   0.1443   0.01456   0.00649  -0.0667   0.9121   0.5515
  -0.750   0.1755   0.01395   0.00643  -0.0667   0.9071   0.7172
  -0.500   0.2407   0.01343   0.00628  -0.0736   0.9063   1.0000
  -0.250   0.2698   0.01344   0.00617  -0.0738   0.8969   1.0000
   0.000   0.3081   0.01334   0.00595  -0.0756   0.8900   1.0000
   0.250   0.3369   0.01328   0.00581  -0.0754   0.8778   1.0000
   0.500   0.3667   0.01323   0.00568  -0.0755   0.8661   1.0000
   0.750   0.3975   0.01317   0.00557  -0.0757   0.8556   1.0000
   1.000   0.4298   0.01309   0.00544  -0.0762   0.8455   1.0000
   1.250   0.4575   0.01305   0.00537  -0.0757   0.8316   1.0000
   1.500   0.4858   0.01300   0.00528  -0.0754   0.8167   1.0000
   1.750   0.5150   0.01293   0.00518  -0.0751   0.8005   1.0000
   2.000   0.5422   0.01291   0.00513  -0.0745   0.7819   1.0000
   2.250   0.5701   0.01290   0.00510  -0.0740   0.7628   1.0000
   2.500   0.5987   0.01290   0.00507  -0.0736   0.7431   1.0000
   2.750   0.6255   0.01295   0.00508  -0.0729   0.7196   1.0000
   3.000   0.6522   0.01303   0.00511  -0.0721   0.6936   1.0000
   3.250   0.6776   0.01317   0.00522  -0.0712   0.6662   1.0000
   3.500   0.7023   0.01334   0.00535  -0.0703   0.6370   1.0000
   3.750   0.7270   0.01354   0.00550  -0.0693   0.6058   1.0000
   4.000   0.7513   0.01379   0.00568  -0.0683   0.5729   1.0000
   4.250   0.7748   0.01410   0.00590  -0.0672   0.5391   1.0000
   4.500   0.7976   0.01449   0.00616  -0.0659   0.5039   1.0000
   4.750   0.8189   0.01496   0.00648  -0.0645   0.4624   1.0000
   5.000   0.8391   0.01550   0.00686  -0.0630   0.4157   1.0000
   5.250   0.8584   0.01611   0.00725  -0.0614   0.3677   1.0000
   5.500   0.8781   0.01675   0.00771  -0.0600   0.3264   1.0000
   5.750   0.8981   0.01738   0.00822  -0.0586   0.2905   1.0000
   6.000   0.9181   0.01803   0.00878  -0.0574   0.2539   1.0000
   6.250   0.9376   0.01874   0.00934  -0.0561   0.2188   1.0000
   6.500   0.9567   0.01950   0.00997  -0.0548   0.1893   1.0000
   6.750   0.9764   0.02024   0.01068  -0.0536   0.1676   1.0000
   7.000   0.9958   0.02102   0.01146  -0.0523   0.1422   1.0000
   7.250   1.0148   0.02189   0.01228  -0.0509   0.1026   1.0000
   7.500   1.0299   0.02315   0.01329  -0.0492   0.0774   1.0000
   7.750   1.0459   0.02431   0.01447  -0.0474   0.0654   1.0000
   8.000   1.0615   0.02547   0.01566  -0.0457   0.0575   1.0000
   8.250   1.0766   0.02664   0.01689  -0.0439   0.0514   1.0000
   8.500   1.0905   0.02792   0.01826  -0.0419   0.0473   1.0000
   8.750   1.1045   0.02915   0.01961  -0.0401   0.0429   1.0000
   9.000   1.1149   0.03076   0.02129  -0.0379   0.0399   1.0000
   9.250   1.1277   0.03234   0.02302  -0.0359   0.0373   1.0000
   9.500   1.1407   0.03383   0.02469  -0.0340   0.0344   1.0000
   9.750   1.1519   0.03550   0.02647  -0.0320   0.0322   1.0000
  10.000   1.1628   0.03751   0.02854  -0.0302   0.0305   1.0000
  10.250   1.1747   0.03995   0.03114  -0.0286   0.0287   1.0000
  10.500   1.1838   0.04176   0.03326  -0.0265   0.0272   1.0000
  10.750   1.1913   0.04390   0.03568  -0.0244   0.0258   1.0000
  11.000   1.1961   0.04637   0.03842  -0.0222   0.0248   1.0000
  11.250   1.1982   0.04893   0.04124  -0.0201   0.0241   1.0000
  11.500   1.1969   0.05157   0.04417  -0.0180   0.0234   1.0000
  11.750   1.1934   0.05428   0.04709  -0.0162   0.0227   1.0000
  12.000   1.1887   0.05709   0.05008  -0.0147   0.0221   1.0000
  12.250   1.1818   0.06035   0.05351  -0.0137   0.0217   1.0000
  12.500   1.1729   0.06411   0.05742  -0.0131   0.0212   1.0000
  13.000   1.1427   0.07342   0.06718  -0.0141   0.0208   1.0000
  13.250   1.1252   0.07877   0.07278  -0.0159   0.0207   1.0000
  13.500   1.1065   0.08491   0.07914  -0.0188   0.0207   1.0000
  13.750   1.0877   0.09169   0.08611  -0.0224   0.0208   1.0000
  14.000   1.0678   0.09926   0.09386  -0.0271   0.0209   1.0000
  14.250   0.9677   0.13195   0.12711  -0.0503   0.0247   1.0000
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