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BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il)
Reynolds number: 50,000
Max Cl/Cd: 36.32 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx69h083-il-50000.txt
Download as CSV file: xf-fx69h083-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4969   0.10319   0.09698  -0.0019   1.0000   0.2055
  -8.000  -0.5028   0.10081   0.09469  -0.0043   1.0000   0.2160
  -7.750  -0.4945   0.09677   0.09069  -0.0040   1.0000   0.2291
  -7.500  -0.4906   0.09318   0.08717  -0.0042   1.0000   0.2427
  -7.250  -0.4912   0.08998   0.08404  -0.0056   1.0000   0.2574
  -7.000  -0.4878   0.08629   0.08043  -0.0060   1.0000   0.2739
  -6.750  -0.4774   0.08275   0.07693  -0.0040   1.0000   0.2980
  -6.500  -0.4740   0.07967   0.07392  -0.0028   1.0000   0.3268
  -6.250  -0.4622   0.07635   0.07065   0.0017   1.0000   0.3668
  -6.000  -0.4623   0.07396   0.06830   0.0050   1.0000   0.4117
  -5.750  -0.4366   0.07027   0.06463   0.0126   1.0000   0.4721
  -5.500  -0.4011   0.06672   0.06100   0.0198   1.0000   0.5609
  -5.000  -0.2403   0.05435   0.04818   0.0207   1.0000   0.8484
  -4.750  -0.2851   0.05422   0.04828   0.0245   1.0000   0.7775
  -4.500  -0.3467   0.05374   0.04819   0.0256   1.0000   0.6812
  -4.250  -0.3904   0.04563   0.03856  -0.0233   1.0000   0.2301
  -4.000  -0.3573   0.04039   0.03241  -0.0249   1.0000   0.1563
  -3.750  -0.3323   0.03724   0.02834  -0.0240   1.0000   0.1323
  -3.500  -0.3113   0.03429   0.02509  -0.0230   1.0000   0.1254
  -3.250  -0.2890   0.03208   0.02242  -0.0220   1.0000   0.1252
  -3.000  -0.2655   0.03011   0.02004  -0.0211   1.0000   0.1268
  -2.750  -0.2399   0.02821   0.01772  -0.0202   1.0000   0.1258
  -2.500  -0.2137   0.02659   0.01574  -0.0194   1.0000   0.1276
  -2.250  -0.1865   0.02527   0.01402  -0.0187   1.0000   0.1325
  -2.000  -0.1588   0.02400   0.01274  -0.0184   1.0000   0.1501
  -1.750  -0.1309   0.02288   0.01156  -0.0180   1.0000   0.1740
  -1.500  -0.0694   0.01811   0.00953  -0.0213   1.0000   1.0000
  -1.250  -0.0539   0.01836   0.00929  -0.0197   1.0000   1.0000
  -1.000  -0.0380   0.01865   0.00917  -0.0184   1.0000   1.0000
  -0.750  -0.0215   0.01898   0.00920  -0.0173   1.0000   1.0000
  -0.500  -0.0046   0.01934   0.00930  -0.0164   1.0000   1.0000
  -0.250   0.0126   0.01976   0.00949  -0.0157   1.0000   1.0000
   0.000   0.0299   0.02022   0.00974  -0.0151   1.0000   1.0000
   0.250   0.0474   0.02072   0.01007  -0.0146   1.0000   1.0000
   0.500   0.0650   0.02128   0.01044  -0.0142   1.0000   1.0000
   0.750   0.0826   0.02189   0.01092  -0.0140   1.0000   1.0000
   1.000   0.1104   0.02266   0.01157  -0.0158   0.9960   1.0000
   1.250   0.1651   0.02376   0.01254  -0.0226   0.9816   1.0000
   1.500   0.2134   0.02475   0.01345  -0.0280   0.9659   1.0000
   1.750   0.2590   0.02571   0.01438  -0.0328   0.9499   1.0000
   2.000   0.3034   0.02664   0.01532  -0.0372   0.9336   1.0000
   2.250   0.3479   0.02755   0.01628  -0.0414   0.9173   1.0000
   2.500   0.3936   0.02841   0.01722  -0.0456   0.9013   1.0000
   2.750   0.4241   0.02923   0.01812  -0.0470   0.8832   1.0000
   3.000   0.4609   0.03001   0.01901  -0.0493   0.8654   1.0000
   3.250   0.5040   0.03067   0.01988  -0.0523   0.8482   1.0000
   3.500   0.5403   0.03132   0.02069  -0.0541   0.8303   1.0000
   3.750   0.5682   0.03204   0.02156  -0.0543   0.8116   1.0000
   4.000   0.6021   0.03259   0.02237  -0.0552   0.7945   1.0000
   4.250   0.6362   0.03307   0.02307  -0.0558   0.7783   1.0000
   4.500   0.6597   0.03379   0.02399  -0.0551   0.7599   1.0000
   4.750   0.6869   0.03423   0.02466  -0.0543   0.7409   1.0000
   5.000   0.7234   0.03394   0.02468  -0.0536   0.7230   1.0000
   5.250   0.7459   0.03418   0.02524  -0.0516   0.7007   1.0000
   5.500   0.7833   0.03296   0.02436  -0.0493   0.6799   1.0000
   5.750   0.8148   0.03155   0.02328  -0.0457   0.6541   1.0000
   6.000   0.8435   0.03026   0.02232  -0.0420   0.6267   1.0000
   6.250   0.8687   0.02899   0.02146  -0.0378   0.5931   1.0000
   6.500   0.8895   0.02491   0.01730  -0.0287   0.5152   1.0000
   6.750   0.8854   0.02438   0.01604  -0.0204   0.3461   1.0000
   7.000   0.8715   0.02866   0.01826  -0.0149   0.1684   1.0000
   7.250   0.8826   0.03206   0.02113  -0.0121   0.1247   1.0000
   7.500   0.9062   0.03454   0.02351  -0.0105   0.1030   1.0000
   7.750   0.9400   0.03768   0.02663  -0.0098   0.0933   1.0000
   8.000   0.9674   0.04075   0.02988  -0.0090   0.0858   1.0000
   8.250   0.9888   0.04434   0.03390  -0.0079   0.0809   1.0000
   8.500   1.0066   0.04797   0.03809  -0.0063   0.0795   1.0000
   8.750   1.0206   0.05206   0.04269  -0.0047   0.0798   1.0000
   9.000   1.0307   0.05645   0.04753  -0.0032   0.0807   1.0000
   9.250   1.0390   0.06122   0.05265  -0.0018   0.0820   1.0000
   9.500   1.0444   0.06575   0.05758  -0.0003   0.0840   1.0000
   9.750   1.0204   0.06979   0.06240   0.0021   0.0873   1.0000
  10.000   1.0002   0.07457   0.06753   0.0032   0.0897   1.0000
  10.250   0.9795   0.07912   0.07226   0.0040   0.0915   1.0000
  10.500   0.9602   0.08405   0.07731   0.0036   0.0931   1.0000
  10.750   0.9646   0.08967   0.08299   0.0034   0.0969   1.0000
  11.000   0.9242   0.09578   0.08921  -0.0009   0.0976   1.0000
  11.250   0.8729   0.10734   0.10076  -0.0119   0.1004   1.0000
  11.500   0.8573   0.11687   0.11015  -0.0177   0.1062   1.0000
  11.750   0.8371   0.12745   0.12062  -0.0252   0.1169   1.0000
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