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WORTMANN FX 76-100 (fx76100-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 76-100 (fx76100-il)
Reynolds number: 50,000
Max Cl/Cd: 25.55 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx76100-il-50000.txt
Download as CSV file: xf-fx76100-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 76-100                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6750   0.09203   0.08468  -0.0120   1.0000   0.1714
  -9.500  -0.6747   0.08633   0.07898  -0.0137   1.0000   0.1676
  -9.250  -0.7829   0.07077   0.06337  -0.0231   1.0000   0.1419
  -9.000  -0.7914   0.06570   0.05813  -0.0226   1.0000   0.1404
  -8.750  -0.8012   0.06075   0.05293  -0.0215   1.0000   0.1400
  -8.500  -0.8110   0.05593   0.04773  -0.0199   1.0000   0.1404
  -8.250  -0.8051   0.05230   0.04396  -0.0184   1.0000   0.1439
  -8.000  -0.7962   0.04913   0.04061  -0.0167   1.0000   0.1478
  -7.750  -0.7921   0.04528   0.03633  -0.0146   1.0000   0.1503
  -7.500  -0.7881   0.04178   0.03215  -0.0120   1.0000   0.1550
  -7.250  -0.7701   0.03960   0.03002  -0.0106   1.0000   0.1638
  -7.000  -0.7594   0.03663   0.02646  -0.0082   1.0000   0.1713
  -6.750  -0.7411   0.03466   0.02440  -0.0066   1.0000   0.1836
  -6.500  -0.7234   0.03274   0.02234  -0.0048   1.0000   0.1986
  -6.250  -0.7052   0.03084   0.02033  -0.0030   1.0000   0.2167
  -6.000  -0.6862   0.02936   0.01895  -0.0012   1.0000   0.2406
  -5.750  -0.6683   0.02790   0.01757   0.0009   1.0000   0.2705
  -5.500  -0.6516   0.02655   0.01623   0.0032   1.0000   0.3066
  -5.250  -0.6333   0.02541   0.01536   0.0055   1.0000   0.3448
  -5.000  -0.6165   0.02441   0.01440   0.0079   1.0000   0.3854
  -4.750  -0.5980   0.02355   0.01377   0.0102   1.0000   0.4248
  -4.500  -0.5799   0.02271   0.01307   0.0126   1.0000   0.4653
  -4.250  -0.5611   0.02196   0.01248   0.0150   1.0000   0.5065
  -4.000  -0.5415   0.02126   0.01198   0.0175   1.0000   0.5499
  -3.750  -0.5217   0.02061   0.01150   0.0201   1.0000   0.5976
  -3.500  -0.5012   0.02005   0.01114   0.0227   1.0000   0.6509
  -3.250  -0.4790   0.01973   0.01105   0.0258   1.0000   0.7092
  -3.000  -0.4524   0.01976   0.01120   0.0286   1.0000   0.7726
  -2.750  -0.4050   0.02039   0.01177   0.0285   1.0000   0.8382
  -2.500  -0.3073   0.02152   0.01247   0.0189   1.0000   0.8999
  -2.250  -0.1735   0.02175   0.01213   0.0002   1.0000   0.9510
  -2.000  -0.0562   0.02068   0.01068  -0.0181   1.0000   0.9957
  -1.750  -0.0379   0.01989   0.00982  -0.0189   1.0000   1.0000
  -1.500  -0.0319   0.01933   0.00925  -0.0169   1.0000   1.0000
  -1.250  -0.0259   0.01889   0.00880  -0.0147   1.0000   1.0000
  -1.000  -0.0198   0.01856   0.00846  -0.0122   1.0000   1.0000
  -0.750  -0.0141   0.01831   0.00821  -0.0094   1.0000   1.0000
  -0.500  -0.0088   0.01813   0.00805  -0.0064   1.0000   1.0000
  -0.250  -0.0042   0.01803   0.00795  -0.0033   1.0000   1.0000
   0.000   0.0000   0.01800   0.00791   0.0000   1.0000   1.0000
   0.250   0.0043   0.01803   0.00795   0.0033   1.0000   1.0000
   0.500   0.0089   0.01813   0.00804   0.0065   1.0000   1.0000
   0.750   0.0141   0.01830   0.00821   0.0094   1.0000   1.0000
   1.000   0.0199   0.01855   0.00846   0.0122   1.0000   1.0000
   1.250   0.0259   0.01889   0.00880   0.0147   1.0000   1.0000
   1.500   0.0319   0.01933   0.00925   0.0169   1.0000   1.0000
   1.750   0.0380   0.01988   0.00982   0.0189   1.0000   1.0000
   2.000   0.0558   0.02067   0.01066   0.0182   0.9958   1.0000
   2.250   0.1744   0.02174   0.01213  -0.0003   0.9507   1.0000
   2.500   0.3074   0.02152   0.01246  -0.0189   0.8999   1.0000
   2.750   0.4050   0.02038   0.01177  -0.0284   0.8381   1.0000
   3.000   0.4522   0.01976   0.01119  -0.0286   0.7724   1.0000
   3.250   0.4789   0.01973   0.01105  -0.0257   0.7090   1.0000
   3.500   0.5012   0.02005   0.01113  -0.0227   0.6507   1.0000
   3.750   0.5216   0.02061   0.01150  -0.0200   0.5972   1.0000
   4.000   0.5414   0.02126   0.01195  -0.0175   0.5497   1.0000
   4.250   0.5611   0.02196   0.01248  -0.0151   0.5067   1.0000
   4.500   0.5799   0.02272   0.01308  -0.0126   0.4652   1.0000
   4.750   0.5980   0.02355   0.01378  -0.0102   0.4248   1.0000
   5.000   0.6165   0.02442   0.01441  -0.0079   0.3854   1.0000
   5.250   0.6332   0.02540   0.01534  -0.0054   0.3448   1.0000
   5.500   0.6515   0.02654   0.01621  -0.0032   0.3066   1.0000
   5.750   0.6682   0.02789   0.01756  -0.0009   0.2705   1.0000
   6.000   0.6860   0.02935   0.01895   0.0012   0.2403   1.0000
   6.250   0.7053   0.03084   0.02032   0.0030   0.2165   1.0000
   6.500   0.7232   0.03275   0.02236   0.0048   0.1983   1.0000
   6.750   0.7410   0.03467   0.02441   0.0066   0.1834   1.0000
   7.000   0.7595   0.03663   0.02644   0.0082   0.1711   1.0000
   7.250   0.7701   0.03963   0.03005   0.0106   0.1638   1.0000
   7.500   0.7883   0.04179   0.03216   0.0120   0.1551   1.0000
   7.750   0.7920   0.04530   0.03635   0.0146   0.1503   1.0000
   8.000   0.7963   0.04911   0.04059   0.0167   0.1478   1.0000
   8.250   0.8031   0.05251   0.04422   0.0184   0.1444   1.0000
   8.500   0.8114   0.05595   0.04775   0.0198   0.1404   1.0000
   8.750   0.8016   0.06075   0.05294   0.0215   0.1400   1.0000
   9.000   0.7921   0.06567   0.05810   0.0226   0.1404   1.0000
   9.250   0.7823   0.07083   0.06343   0.0231   0.1419   1.0000
   9.500   0.6036   0.10102   0.09344  -0.0039   0.2501   1.0000
   9.750   0.5866   0.11180   0.10416  -0.0130   0.3222   1.0000
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