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WORTMANN FX 80-080 (fx80080-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 80-080 (fx80080-il)
Reynolds number: 100,000
Max Cl/Cd: 55.16 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx80080-il-100000-n5.txt
Download as CSV file: xf-fx80080-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4637   0.12202   0.11673  -0.0272   1.0000   0.0412
 -10.250  -0.4651   0.11908   0.11386  -0.0303   1.0000   0.0416
 -10.000  -0.4647   0.11585   0.11068  -0.0328   1.0000   0.0418
  -9.750  -0.4645   0.11228   0.10718  -0.0350   1.0000   0.0419
  -9.500  -0.4585   0.10651   0.10145  -0.0333   1.0000   0.0429
  -9.250  -0.4517   0.10274   0.09769  -0.0325   1.0000   0.0438
  -9.000  -0.4485   0.09929   0.09428  -0.0330   1.0000   0.0443
  -8.750  -0.4471   0.09572   0.09076  -0.0337   1.0000   0.0448
  -8.500  -0.3513   0.07429   0.06978  -0.0392   1.0000   0.0402
  -8.000  -0.3700   0.06453   0.06014  -0.0416   1.0000   0.0286
  -7.750  -0.3778   0.06111   0.05680  -0.0406   1.0000   0.0279
  -7.500  -0.3928   0.05831   0.05411  -0.0394   1.0000   0.0276
  -7.250  -0.4719   0.07138   0.06676  -0.0436   1.0000   0.0281
  -7.000  -0.4769   0.06819   0.06359  -0.0428   1.0000   0.0273
  -6.750  -0.4821   0.06509   0.06049  -0.0418   1.0000   0.0267
  -6.500  -0.4868   0.06168   0.05702  -0.0409   1.0000   0.0261
  -6.250  -0.4881   0.05828   0.05353  -0.0400   1.0000   0.0254
  -6.000  -0.4639   0.05214   0.04708  -0.0452   0.9946   0.0244
  -5.750  -0.4378   0.04625   0.04079  -0.0493   0.9894   0.0235
  -5.500  -0.4123   0.04107   0.03514  -0.0520   0.9839   0.0229
  -5.250  -0.3831   0.03629   0.02980  -0.0544   0.9796   0.0226
  -5.000  -0.3553   0.03248   0.02543  -0.0557   0.9751   0.0231
  -4.750  -0.3263   0.02987   0.02231  -0.0568   0.9709   0.0257
  -4.500  -0.2946   0.02735   0.01919  -0.0578   0.9678   0.0278
  -4.250  -0.2623   0.02495   0.01619  -0.0587   0.9652   0.0285
  -4.000  -0.2347   0.02321   0.01407  -0.0586   0.9608   0.0292
  -3.750  -0.2054   0.02123   0.01190  -0.0591   0.9575   0.0310
  -3.500  -0.1745   0.01998   0.01057  -0.0599   0.9547   0.0337
  -3.250  -0.1415   0.01927   0.00968  -0.0611   0.9523   0.0416
  -3.000  -0.1166   0.01823   0.00865  -0.0608   0.9474   0.0474
  -2.750  -0.0871   0.01744   0.00781  -0.0613   0.9436   0.0611
  -2.500  -0.0554   0.01672   0.00710  -0.0624   0.9407   0.0938
  -2.250  -0.0247   0.01556   0.00663  -0.0638   0.9383   0.2345
  -2.000  -0.0114   0.01407   0.00684  -0.0610   0.9328   0.6540
  -1.750   0.0100   0.01405   0.00698  -0.0586   0.9285   0.7882
  -1.500   0.0349   0.01403   0.00695  -0.0570   0.9255   0.8497
  -1.250   0.0531   0.01398   0.00688  -0.0539   0.9202   0.9103
  -1.000   0.1345   0.01386   0.00661  -0.0639   0.9256   0.9854
  -0.750   0.1696   0.01390   0.00650  -0.0661   0.9216   1.0000
  -0.500   0.1947   0.01394   0.00641  -0.0661   0.9157   1.0000
  -0.250   0.2276   0.01395   0.00632  -0.0676   0.9122   1.0000
   0.000   0.2495   0.01406   0.00635  -0.0670   0.9055   1.0000
   0.250   0.2795   0.01413   0.00635  -0.0679   0.9009   1.0000
   0.500   0.3143   0.01416   0.00634  -0.0696   0.8977   1.0000
   0.750   0.3359   0.01434   0.00648  -0.0688   0.8903   1.0000
   1.000   0.3683   0.01442   0.00654  -0.0700   0.8862   1.0000
   1.250   0.3976   0.01453   0.00665  -0.0706   0.8807   1.0000
   1.500   0.4259   0.01464   0.00680  -0.0709   0.8742   1.0000
   1.750   0.4624   0.01464   0.00683  -0.0726   0.8701   1.0000
   2.000   0.4856   0.01480   0.00704  -0.0719   0.8610   1.0000
   2.250   0.5202   0.01478   0.00708  -0.0731   0.8551   1.0000
   2.500   0.5478   0.01482   0.00720  -0.0729   0.8453   1.0000
   2.750   0.5767   0.01478   0.00730  -0.0728   0.8339   1.0000
   3.000   0.6071   0.01461   0.00722  -0.0727   0.8200   1.0000
   3.250   0.6397   0.01426   0.00697  -0.0726   0.8018   1.0000
   3.500   0.6633   0.01409   0.00688  -0.0710   0.7784   1.0000
   3.750   0.6876   0.01392   0.00681  -0.0695   0.7518   1.0000
   4.000   0.7129   0.01375   0.00677  -0.0682   0.7188   1.0000
   4.250   0.7345   0.01370   0.00677  -0.0662   0.6706   1.0000
   4.500   0.7590   0.01376   0.00645  -0.0644   0.5572   1.0000
   4.750   0.7693   0.01497   0.00669  -0.0607   0.3868   1.0000
   5.000   0.7785   0.01648   0.00740  -0.0577   0.2465   1.0000
   5.250   0.7936   0.01773   0.00819  -0.0559   0.1617   1.0000
   5.500   0.8106   0.01888   0.00911  -0.0543   0.1122   1.0000
   5.750   0.8287   0.01994   0.01004  -0.0529   0.0825   1.0000
   6.000   0.8466   0.02104   0.01100  -0.0514   0.0634   1.0000
   6.250   0.8653   0.02209   0.01215  -0.0500   0.0524   1.0000
   6.500   0.8830   0.02337   0.01356  -0.0482   0.0458   1.0000
   6.750   0.9014   0.02471   0.01496  -0.0468   0.0406   1.0000
   7.000   0.9214   0.02611   0.01650  -0.0456   0.0348   1.0000
   7.250   0.9428   0.02772   0.01826  -0.0446   0.0310   1.0000
   7.500   0.9642   0.02983   0.02053  -0.0437   0.0280   1.0000
   7.750   0.9863   0.03185   0.02289  -0.0428   0.0237   1.0000
   8.000   1.0075   0.03428   0.02568  -0.0417   0.0212   1.0000
   8.250   1.0251   0.03682   0.02853  -0.0403   0.0195   1.0000
   8.500   1.0373   0.03956   0.03148  -0.0388   0.0177   1.0000
   8.750   1.0472   0.04262   0.03508  -0.0364   0.0162   1.0000
   9.000   1.0533   0.04601   0.03901  -0.0338   0.0149   1.0000
   9.250   1.0532   0.04992   0.04341  -0.0308   0.0146   1.0000
   9.500   1.0479   0.05387   0.04777  -0.0276   0.0144   1.0000
   9.750   1.0372   0.05759   0.05183  -0.0241   0.0143   1.0000
  10.000   1.0225   0.06119   0.05571  -0.0208   0.0143   1.0000
  10.250   1.0044   0.06512   0.05988  -0.0183   0.0143   1.0000
  10.500   0.9856   0.06934   0.06431  -0.0171   0.0144   1.0000
  10.750   0.9653   0.07418   0.06933  -0.0173   0.0145   1.0000
  11.000   0.9454   0.07962   0.07493  -0.0189   0.0146   1.0000
  11.250   0.9240   0.08637   0.08180  -0.0224   0.0148   1.0000
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