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BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il)
Reynolds number: 200,000
Max Cl/Cd: 69.65 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx69h083-il-200000.txt
Download as CSV file: xf-fx69h083-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BELL/WORTMANN FX 69-H-083 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  -0.4963   0.09259   0.08942  -0.0061   1.0000   0.0315
  -8.000  -0.4933   0.08863   0.08550  -0.0091   1.0000   0.0323
  -7.750  -0.4911   0.08446   0.08137  -0.0130   1.0000   0.0331
  -7.500  -0.4863   0.07994   0.07686  -0.0180   1.0000   0.0341
  -7.250  -0.4779   0.07514   0.07204  -0.0233   1.0000   0.0354
  -7.000  -0.4638   0.07012   0.06690  -0.0302   1.0000   0.0373
  -6.750  -0.4472   0.06632   0.06283  -0.0350   1.0000   0.0382
  -6.500  -0.4358   0.06286   0.05916  -0.0361   1.0000   0.0384
  -6.250  -0.4388   0.05595   0.05232  -0.0359   1.0000   0.0395
  -6.000  -0.4388   0.05342   0.04984  -0.0333   1.0000   0.0405
  -5.750  -0.4397   0.05144   0.04785  -0.0304   1.0000   0.0415
  -5.500  -0.4388   0.04940   0.04575  -0.0278   1.0000   0.0429
  -5.250  -0.4066   0.04534   0.04141  -0.0314   0.9953   0.0477
  -5.000  -0.3739   0.04020   0.03573  -0.0348   0.9893   0.0531
  -4.750  -0.3422   0.03702   0.03250  -0.0376   0.9850   0.0576
  -4.500  -0.3082   0.03348   0.02851  -0.0401   0.9801   0.0681
  -4.250  -0.2756   0.03091   0.02572  -0.0424   0.9747   0.0823
  -4.000  -0.2388   0.02826   0.02279  -0.0450   0.9709   0.0963
  -3.750  -0.1953   0.02123   0.01430  -0.0431   0.9667   0.0408
  -3.500  -0.1588   0.01951   0.01218  -0.0439   0.9606   0.0392
  -3.250  -0.1225   0.01744   0.00996  -0.0457   0.9562   0.0431
  -3.000  -0.0918   0.01607   0.00840  -0.0457   0.9480   0.0435
  -2.750  -0.0599   0.01500   0.00725  -0.0461   0.9417   0.0459
  -2.500  -0.0337   0.01445   0.00663  -0.0454   0.9319   0.0504
  -2.250  -0.0100   0.01355   0.00575  -0.0443   0.9227   0.0557
  -2.000   0.0146   0.01306   0.00519  -0.0432   0.9147   0.0645
  -1.750   0.0311   0.01129   0.00453  -0.0413   0.9041   0.3208
  -1.500   0.1265   0.00954   0.00462  -0.0530   0.9082   1.0000
  -1.250   0.1476   0.00954   0.00446  -0.0515   0.8962   1.0000
  -1.000   0.1688   0.00953   0.00431  -0.0499   0.8849   1.0000
  -0.750   0.1902   0.00952   0.00414  -0.0483   0.8742   1.0000
  -0.500   0.2132   0.00951   0.00402  -0.0473   0.8626   1.0000
  -0.250   0.2363   0.00950   0.00391  -0.0462   0.8514   1.0000
   0.000   0.2594   0.00949   0.00380  -0.0450   0.8404   1.0000
   0.250   0.2825   0.00947   0.00369  -0.0439   0.8299   1.0000
   0.500   0.3060   0.00945   0.00358  -0.0428   0.8192   1.0000
   0.750   0.3303   0.00946   0.00352  -0.0420   0.8074   1.0000
   1.000   0.3548   0.00947   0.00347  -0.0412   0.7958   1.0000
   1.250   0.3792   0.00948   0.00343  -0.0403   0.7839   1.0000
   1.500   0.4035   0.00948   0.00338  -0.0394   0.7710   1.0000
   1.750   0.4279   0.00949   0.00333  -0.0385   0.7572   1.0000
   2.000   0.4527   0.00951   0.00330  -0.0378   0.7437   1.0000
   2.250   0.4777   0.00955   0.00331  -0.0371   0.7306   1.0000
   2.500   0.5027   0.00960   0.00335  -0.0364   0.7162   1.0000
   2.750   0.5277   0.00965   0.00337  -0.0357   0.7003   1.0000
   3.000   0.5526   0.00970   0.00340  -0.0350   0.6839   1.0000
   3.250   0.5777   0.00979   0.00346  -0.0343   0.6681   1.0000
   3.500   0.6029   0.00990   0.00359  -0.0338   0.6517   1.0000
   3.750   0.6282   0.01003   0.00373  -0.0332   0.6351   1.0000
   4.000   0.6535   0.01017   0.00389  -0.0327   0.6181   1.0000
   4.250   0.6785   0.01033   0.00406  -0.0321   0.6004   1.0000
   4.500   0.7035   0.01051   0.00425  -0.0315   0.5806   1.0000
   4.750   0.7282   0.01071   0.00449  -0.0309   0.5583   1.0000
   5.000   0.7529   0.01092   0.00472  -0.0302   0.5331   1.0000
   5.250   0.7766   0.01115   0.00492  -0.0294   0.4978   1.0000
   5.500   0.7981   0.01156   0.00511  -0.0283   0.4355   1.0000
   5.750   0.8188   0.01219   0.00546  -0.0273   0.3645   1.0000
   6.000   0.8357   0.01340   0.00612  -0.0261   0.2397   1.0000
   6.250   0.8410   0.01657   0.00795  -0.0237   0.0442   1.0000
   6.500   0.8584   0.01801   0.00948  -0.0221   0.0336   1.0000
   6.750   0.8770   0.01920   0.01080  -0.0206   0.0300   1.0000
   7.000   0.8942   0.02051   0.01217  -0.0192   0.0267   1.0000
   7.250   0.9079   0.02262   0.01431  -0.0173   0.0240   1.0000
   7.500   0.9278   0.02417   0.01598  -0.0159   0.0232   1.0000
   7.750   0.9489   0.02607   0.01801  -0.0146   0.0226   1.0000
   8.000   0.9711   0.02838   0.02056  -0.0135   0.0225   1.0000
   8.250   0.9926   0.03123   0.02369  -0.0123   0.0228   1.0000
   8.500   1.0111   0.03498   0.02778  -0.0110   0.0235   1.0000
   8.750   1.0313   0.03852   0.03156  -0.0099   0.0251   1.0000
   9.000   1.0417   0.04353   0.03751  -0.0062   0.0315   1.0000
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