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GOE 802 A AIRFOIL (goe802a-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 802 A AIRFOIL (goe802a-il)
Reynolds number: 200,000
Max Cl/Cd: 73.91 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe802a-il-200000.txt
Download as CSV file: xf-goe802a-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 802 A 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3050   0.09445   0.09101  -0.0264   1.0000   0.0371
  -8.000  -0.3030   0.09188   0.08849  -0.0276   1.0000   0.0380
  -7.750  -0.3111   0.09026   0.08696  -0.0272   1.0000   0.0387
  -7.500  -0.2836   0.08314   0.08020  -0.0278   0.9954   0.0396
  -7.250  -0.2638   0.07807   0.07513  -0.0282   0.9935   0.0402
  -7.000  -0.2479   0.07367   0.07072  -0.0320   0.9878   0.0410
  -6.750  -0.3204   0.08090   0.07775  -0.0316   0.9944   0.0399
  -6.500  -0.2973   0.07678   0.07362  -0.0352   0.9901   0.0407
  -6.250  -0.2685   0.07261   0.06940  -0.0413   0.9848   0.0418
  -6.000  -0.2322   0.06804   0.06475  -0.0495   0.9809   0.0437
  -5.750  -0.1847   0.06322   0.05962  -0.0621   0.9720   0.0457
  -5.500  -0.1599   0.05897   0.05543  -0.0644   0.9687   0.0464
  -5.250  -0.1254   0.05527   0.05166  -0.0694   0.9655   0.0480
  -5.000  -0.0761   0.05273   0.04858  -0.0775   0.9567   0.0519
  -4.750  -0.0496   0.04812   0.04411  -0.0800   0.9527   0.0524
  -4.500  -0.0216   0.04505   0.04100  -0.0824   0.9458   0.0536
  -4.250   0.0095   0.04237   0.03818  -0.0847   0.9374   0.0559
  -4.000   0.0466   0.04032   0.03569  -0.0870   0.9286   0.0584
  -3.750   0.0685   0.03733   0.03272  -0.0874   0.9187   0.0593
  -3.500   0.0921   0.03529   0.03057  -0.0874   0.9079   0.0613
  -3.250   0.1229   0.03432   0.02916  -0.0872   0.8985   0.0645
  -3.000   0.1425   0.03167   0.02655  -0.0868   0.8867   0.0658
  -2.750   0.1685   0.03049   0.02511  -0.0861   0.8765   0.0692
  -2.500   0.1939   0.02910   0.02346  -0.0853   0.8644   0.0702
  -2.250   0.2172   0.02718   0.02146  -0.0848   0.8520   0.0717
  -2.000   0.2438   0.02637   0.02037  -0.0839   0.8408   0.0741
  -1.750   0.2715   0.02615   0.01976  -0.0829   0.8277   0.0749
  -1.500   0.2956   0.02376   0.01736  -0.0826   0.8144   0.0757
  -1.250   0.3218   0.02254   0.01596  -0.0820   0.8013   0.0771
  -1.000   0.3494   0.02231   0.01541  -0.0811   0.7875   0.0790
  -0.750   0.3766   0.02175   0.01458  -0.0804   0.7723   0.0796
  -0.500   0.4027   0.02020   0.01293  -0.0800   0.7559   0.0803
  -0.250   0.4295   0.01933   0.01190  -0.0795   0.7392   0.0810
   0.000   0.3916   0.00804   0.00188  -0.0689   0.7176   0.0740
   0.250   0.4839   0.01813   0.01032  -0.0784   0.7048   0.0815
   0.500   0.5111   0.01765   0.00965  -0.0779   0.6872   0.0812
   0.750   0.5384   0.01728   0.00909  -0.0773   0.6697   0.0805
   1.000   0.5660   0.01753   0.00907  -0.0767   0.6527   0.0793
   1.250   0.5930   0.01705   0.00846  -0.0763   0.6364   0.0793
   1.500   0.6199   0.01675   0.00802  -0.0759   0.6205   0.0838
   1.750   0.6469   0.01652   0.00765  -0.0755   0.6052   0.0839
   2.000   0.6736   0.01615   0.00716  -0.0751   0.5905   0.0884
   2.250   0.6999   0.01535   0.00633  -0.0748   0.5760   0.1000
   2.500   0.7244   0.01377   0.00508  -0.0745   0.5621   0.1276
   2.750   0.7501   0.01319   0.00469  -0.0742   0.5482   0.2117
   3.000   0.7782   0.01170   0.00483  -0.0742   0.5329   1.0000
   3.250   0.8040   0.01196   0.00493  -0.0738   0.5181   1.0000
   3.500   0.8299   0.01222   0.00504  -0.0734   0.5044   1.0000
   3.750   0.8559   0.01244   0.00522  -0.0730   0.4906   1.0000
   4.000   0.8818   0.01269   0.00540  -0.0727   0.4784   1.0000
   4.250   0.9077   0.01299   0.00557  -0.0724   0.4680   1.0000
   4.500   0.9337   0.01321   0.00579  -0.0721   0.4566   1.0000
   4.750   0.9595   0.01350   0.00602  -0.0718   0.4465   1.0000
   5.000   0.9853   0.01374   0.00623  -0.0715   0.4359   1.0000
   5.250   1.0110   0.01402   0.00649  -0.0712   0.4261   1.0000
   5.500   1.0365   0.01431   0.00674  -0.0709   0.4168   1.0000
   5.750   1.0618   0.01457   0.00702  -0.0705   0.4063   1.0000
   6.000   1.0868   0.01489   0.00725  -0.0701   0.3962   1.0000
   6.250   1.1115   0.01512   0.00753  -0.0697   0.3844   1.0000
   6.500   1.1359   0.01541   0.00783  -0.0692   0.3728   1.0000
   6.750   1.1598   0.01575   0.00809  -0.0687   0.3609   1.0000
   7.000   1.1834   0.01602   0.00839  -0.0681   0.3475   1.0000
   7.250   1.2070   0.01633   0.00873  -0.0675   0.3343   1.0000
   7.500   1.2300   0.01669   0.00910  -0.0669   0.3215   1.0000
   7.750   1.2522   0.01709   0.00947  -0.0661   0.3075   1.0000
   8.000   1.2739   0.01751   0.00987  -0.0653   0.2925   1.0000
   8.250   1.2951   0.01794   0.01032  -0.0644   0.2761   1.0000
   8.500   1.3155   0.01841   0.01080  -0.0634   0.2578   1.0000
   8.750   1.3351   0.01894   0.01130  -0.0624   0.2391   1.0000
   9.000   1.3538   0.01954   0.01186  -0.0613   0.2214   1.0000
   9.250   1.3713   0.02024   0.01250  -0.0600   0.2065   1.0000
   9.750   1.4041   0.02176   0.01399  -0.0572   0.1821   1.0000
  10.000   1.4194   0.02257   0.01480  -0.0557   0.1720   1.0000
  10.250   1.4315   0.02352   0.01571  -0.0538   0.1630   1.0000
  10.500   1.4457   0.02424   0.01653  -0.0521   0.1545   1.0000
  10.750   1.4539   0.02527   0.01753  -0.0496   0.1471   1.0000
  11.000   1.4671   0.02605   0.01844  -0.0480   0.1396   1.0000
  11.250   1.4761   0.02711   0.01951  -0.0460   0.1331   1.0000
  11.500   1.4867   0.02814   0.02063  -0.0443   0.1272   1.0000
  11.750   1.4975   0.02916   0.02175  -0.0428   0.1212   1.0000
  12.000   1.5039   0.03054   0.02313  -0.0411   0.1154   1.0000
  12.250   1.5166   0.03151   0.02428  -0.0400   0.1091   1.0000
  12.500   1.5233   0.03298   0.02577  -0.0387   0.1033   1.0000
  12.750   1.5332   0.03427   0.02719  -0.0376   0.0973   1.0000
  13.000   1.5401   0.03586   0.02885  -0.0366   0.0909   1.0000
  13.250   1.5467   0.03757   0.03065  -0.0357   0.0837   1.0000
  13.500   1.5485   0.03980   0.03291  -0.0349   0.0769   1.0000
  13.750   1.5503   0.04214   0.03532  -0.0342   0.0694   1.0000
  14.000   1.5470   0.04513   0.03836  -0.0336   0.0629   1.0000
  14.250   1.5421   0.04843   0.04172  -0.0333   0.0561   1.0000
  14.500   1.5368   0.05192   0.04532  -0.0332   0.0493   1.0000
  14.750   1.5277   0.05602   0.04948  -0.0335   0.0440   1.0000
  15.000   1.5199   0.06011   0.05366  -0.0340   0.0387   1.0000
  15.250   1.5093   0.06474   0.05836  -0.0348   0.0358   1.0000
  15.500   1.4986   0.06953   0.06327  -0.0359   0.0336   1.0000
  15.750   1.4865   0.07468   0.06852  -0.0372   0.0321   1.0000
  16.000   1.4727   0.08020   0.07415  -0.0388   0.0310   1.0000
  16.250   1.4582   0.08597   0.08003  -0.0406   0.0303   1.0000
  16.500   1.4452   0.09164   0.08583  -0.0424   0.0297   1.0000
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