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WORTMANN FX 80-080 (fx80080-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 80-080 (fx80080-il)
Reynolds number: 200,000
Max Cl/Cd: 80.43 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx80080-il-200000.txt
Download as CSV file: xf-fx80080-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 80-080                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4502   0.10257   0.09901  -0.0362   1.0000   0.0315
  -9.000  -0.4486   0.09893   0.09540  -0.0379   1.0000   0.0315
  -8.750  -0.4511   0.09248   0.08901  -0.0355   1.0000   0.0330
  -8.500  -0.4470   0.08950   0.08605  -0.0350   1.0000   0.0338
  -8.250  -0.4441   0.08671   0.08326  -0.0347   1.0000   0.0354
  -8.000  -0.4462   0.08358   0.08019  -0.0353   1.0000   0.0361
  -7.750  -0.4516   0.08078   0.07747  -0.0355   1.0000   0.0377
  -7.500  -0.4614   0.07767   0.07444  -0.0360   1.0000   0.0376
  -7.250  -0.4699   0.07431   0.07115  -0.0375   1.0000   0.0386
  -7.000  -0.4832   0.07177   0.06865  -0.0366   1.0000   0.0398
  -6.750  -0.4960   0.06943   0.06633  -0.0346   1.0000   0.0386
  -6.500  -0.5040   0.06663   0.06349  -0.0342   1.0000   0.0410
  -6.250  -0.4970   0.06379   0.06026  -0.0380   0.9993   0.0437
  -6.000  -0.4789   0.05560   0.05182  -0.0436   0.9957   0.0448
  -5.750  -0.4602   0.05158   0.04790  -0.0451   0.9927   0.0469
  -5.500  -0.4329   0.04781   0.04398  -0.0485   0.9893   0.0500
  -5.250  -0.3931   0.04650   0.04176  -0.0522   0.9837   0.0571
  -5.000  -0.3750   0.03903   0.03446  -0.0550   0.9810   0.0602
  -4.750  -0.3441   0.03614   0.03138  -0.0573   0.9784   0.0650
  -4.500  -0.3158   0.03286   0.02767  -0.0590   0.9744   0.0741
  -4.250  -0.2794   0.02584   0.01967  -0.0584   0.9717   0.0390
  -4.000  -0.2466   0.02335   0.01670  -0.0594   0.9690   0.0399
  -3.750  -0.2126   0.02067   0.01353  -0.0601   0.9671   0.0381
  -3.500  -0.1774   0.01873   0.01124  -0.0612   0.9655   0.0384
  -3.250  -0.1469   0.01748   0.00982  -0.0615   0.9625   0.0407
  -3.000  -0.1190   0.01645   0.00868  -0.0615   0.9586   0.0459
  -2.750  -0.0871   0.01555   0.00778  -0.0625   0.9557   0.0542
  -2.500  -0.0531   0.01461   0.00686  -0.0639   0.9533   0.0730
  -2.250  -0.0187   0.01344   0.00615  -0.0659   0.9514   0.1684
  -2.000  -0.0107   0.01160   0.00649  -0.0624   0.9459   0.7203
  -1.750   0.0113   0.01166   0.00670  -0.0602   0.9416   0.8177
  -1.500   0.0385   0.01168   0.00670  -0.0593   0.9387   0.8614
  -1.250   0.0567   0.01173   0.00671  -0.0567   0.9336   0.8953
  -1.000   0.0801   0.01169   0.00667  -0.0552   0.9293   0.9289
  -0.750   0.1408   0.01167   0.00658  -0.0614   0.9305   0.9735
  -0.500   0.2353   0.01157   0.00633  -0.0748   0.9381   1.0000
  -0.250   0.2509   0.01163   0.00635  -0.0732   0.9298   1.0000
   0.000   0.2871   0.01159   0.00625  -0.0754   0.9266   1.0000
   0.250   0.3289   0.01152   0.00614  -0.0786   0.9245   1.0000
   0.500   0.3438   0.01163   0.00623  -0.0767   0.9158   1.0000
   0.750   0.3821   0.01154   0.00613  -0.0790   0.9123   1.0000
   1.000   0.4255   0.01140   0.00600  -0.0823   0.9098   1.0000
   1.250   0.4422   0.01152   0.00613  -0.0804   0.9001   1.0000
   1.500   0.4852   0.01132   0.00595  -0.0833   0.8964   1.0000
   1.750   0.5076   0.01137   0.00602  -0.0823   0.8868   1.0000
   2.000   0.5437   0.01116   0.00584  -0.0835   0.8788   1.0000
   2.250   0.5805   0.01083   0.00557  -0.0846   0.8685   1.0000
   2.500   0.6098   0.01058   0.00535  -0.0841   0.8547   1.0000
   2.750   0.6377   0.01037   0.00516  -0.0834   0.8399   1.0000
   3.000   0.6629   0.01026   0.00508  -0.0824   0.8250   1.0000
   3.250   0.6869   0.01014   0.00502  -0.0810   0.8079   1.0000
   3.500   0.7117   0.01000   0.00495  -0.0798   0.7890   1.0000
   3.750   0.7353   0.00985   0.00485  -0.0783   0.7652   1.0000
   4.000   0.7584   0.00974   0.00478  -0.0767   0.7348   1.0000
   4.250   0.7802   0.00970   0.00471  -0.0749   0.6895   1.0000
   4.500   0.7952   0.01005   0.00457  -0.0714   0.5611   1.0000
   4.750   0.7954   0.01159   0.00503  -0.0661   0.3692   1.0000
   5.000   0.7994   0.01337   0.00584  -0.0622   0.1974   1.0000
   5.250   0.8117   0.01480   0.00673  -0.0598   0.1148   1.0000
   5.500   0.8280   0.01594   0.00765  -0.0580   0.0821   1.0000
   5.750   0.8454   0.01706   0.00873  -0.0561   0.0636   1.0000
   6.000   0.8623   0.01843   0.01008  -0.0542   0.0531   1.0000
   6.250   0.8832   0.01937   0.01105  -0.0530   0.0451   1.0000
   6.500   0.9040   0.02113   0.01291  -0.0518   0.0400   1.0000
   6.750   0.9268   0.02217   0.01404  -0.0509   0.0344   1.0000
   7.000   0.9515   0.02504   0.01702  -0.0505   0.0301   1.0000
   7.250   0.9770   0.02709   0.01938  -0.0496   0.0282   1.0000
   7.500   0.9991   0.02881   0.02137  -0.0485   0.0250   1.0000
   7.750   1.0181   0.03032   0.02297  -0.0474   0.0224   1.0000
   8.000   1.0357   0.03408   0.02712  -0.0459   0.0216   1.0000
   8.250   1.0488   0.03793   0.03143  -0.0436   0.0215   1.0000
   8.500   0.9970   0.03292   0.02797  -0.0328   0.0253   1.0000
   8.750   0.9880   0.03914   0.03462  -0.0289   0.0275   1.0000
   9.000   0.9772   0.04479   0.04051  -0.0257   0.0292   1.0000
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