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FX 84-W-097 (fx84w097-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 84-W-097 (fx84w097-il)
Reynolds number: 100,000
Max Cl/Cd: 55.64 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx84w097-il-100000-n5.txt
Download as CSV file: xf-fx84w097-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 84-W-097                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4475   0.09085   0.08602  -0.0278   1.0000   0.0289
  -9.000  -0.4477   0.08622   0.08145  -0.0306   1.0000   0.0289
  -8.750  -0.4347   0.08586   0.08111  -0.0287   1.0000   0.0312
  -8.500  -0.4377   0.08104   0.07637  -0.0320   1.0000   0.0309
  -8.000  -0.4625   0.06460   0.05997  -0.0471   1.0000   0.0290
  -7.250  -0.4794   0.05064   0.04566  -0.0496   0.9993   0.0291
  -7.000  -0.4599   0.04418   0.03872  -0.0547   0.9841   0.0292
  -6.750  -0.4370   0.03911   0.03316  -0.0582   0.9721   0.0296
  -6.500  -0.4119   0.03536   0.02898  -0.0605   0.9612   0.0303
  -6.250  -0.3849   0.03244   0.02565  -0.0622   0.9512   0.0315
  -6.000  -0.3555   0.03026   0.02308  -0.0637   0.9426   0.0341
  -5.750  -0.3295   0.02768   0.01990  -0.0641   0.9321   0.0365
  -5.500  -0.3022   0.02542   0.01705  -0.0642   0.9227   0.0379
  -5.250  -0.2746   0.02352   0.01493  -0.0645   0.9147   0.0400
  -5.000  -0.2489   0.02267   0.01395  -0.0644   0.9045   0.0438
  -4.750  -0.2220   0.02153   0.01252  -0.0641   0.8958   0.0476
  -4.500  -0.1959   0.02029   0.01110  -0.0636   0.8873   0.0507
  -4.250  -0.1710   0.01959   0.01037  -0.0631   0.8779   0.0562
  -4.000  -0.1450   0.01883   0.00945  -0.0625   0.8703   0.0626
  -3.750  -0.1207   0.01813   0.00875  -0.0619   0.8609   0.0695
  -3.500  -0.0955   0.01755   0.00813  -0.0613   0.8527   0.0804
  -3.250  -0.0704   0.01699   0.00752  -0.0607   0.8445   0.0934
  -3.000  -0.0454   0.01652   0.00707  -0.0602   0.8358   0.1146
  -2.750  -0.0202   0.01601   0.00664  -0.0595   0.8284   0.1440
  -2.500   0.0044   0.01552   0.00632  -0.0591   0.8195   0.1926
  -2.250   0.0287   0.01493   0.00603  -0.0584   0.8126   0.2759
  -2.000   0.0512   0.01417   0.00587  -0.0577   0.8037   0.4264
  -1.750   0.0698   0.01333   0.00588  -0.0552   0.7968   0.6550
  -1.500   0.0924   0.01306   0.00597  -0.0526   0.7888   0.8155
  -1.250   0.1265   0.01299   0.00586  -0.0526   0.7825   0.9017
  -1.000   0.1718   0.01294   0.00568  -0.0555   0.7748   0.9535
  -0.750   0.2264   0.01282   0.00533  -0.0606   0.7688   0.9886
  -0.500   0.2613   0.01282   0.00519  -0.0623   0.7599   1.0000
  -0.250   0.2837   0.01287   0.00510  -0.0613   0.7521   1.0000
   0.000   0.3064   0.01294   0.00505  -0.0604   0.7435   1.0000
   0.250   0.3295   0.01302   0.00503  -0.0595   0.7352   1.0000
   0.500   0.3528   0.01309   0.00499  -0.0586   0.7274   1.0000
   0.750   0.3764   0.01321   0.00504  -0.0579   0.7187   1.0000
   1.000   0.4006   0.01328   0.00501  -0.0571   0.7116   1.0000
   1.250   0.4247   0.01342   0.00511  -0.0565   0.7024   1.0000
   1.500   0.4495   0.01352   0.00513  -0.0558   0.6953   1.0000
   1.750   0.4742   0.01367   0.00526  -0.0552   0.6864   1.0000
   2.000   0.4994   0.01380   0.00535  -0.0547   0.6785   1.0000
   2.250   0.5247   0.01392   0.00545  -0.0541   0.6702   1.0000
   2.500   0.5500   0.01408   0.00560  -0.0537   0.6614   1.0000
   2.750   0.5757   0.01419   0.00569  -0.0531   0.6537   1.0000
   3.000   0.6010   0.01437   0.00590  -0.0527   0.6438   1.0000
   3.250   0.6267   0.01452   0.00606  -0.0522   0.6350   1.0000
   3.500   0.6525   0.01466   0.00621  -0.0517   0.6260   1.0000
   3.750   0.6780   0.01486   0.00649  -0.0513   0.6160   1.0000
   4.000   0.7039   0.01502   0.00668  -0.0509   0.6068   1.0000
   4.250   0.7297   0.01518   0.00687  -0.0504   0.5966   1.0000
   4.500   0.7550   0.01536   0.00713  -0.0499   0.5847   1.0000
   4.750   0.7804   0.01555   0.00742  -0.0494   0.5727   1.0000
   5.000   0.8058   0.01573   0.00768  -0.0489   0.5609   1.0000
   5.250   0.8312   0.01592   0.00795  -0.0483   0.5484   1.0000
   5.500   0.8562   0.01612   0.00825  -0.0477   0.5346   1.0000
   5.750   0.8804   0.01629   0.00850  -0.0469   0.5151   1.0000
   6.000   0.9034   0.01643   0.00866  -0.0459   0.4874   1.0000
   6.250   0.9253   0.01665   0.00883  -0.0447   0.4533   1.0000
   6.500   0.9464   0.01701   0.00915  -0.0436   0.4150   1.0000
   6.750   0.9661   0.01752   0.00957  -0.0423   0.3695   1.0000
   7.000   0.9831   0.01830   0.01011  -0.0408   0.3099   1.0000
   7.250   0.9960   0.01951   0.01092  -0.0391   0.2347   1.0000
   7.500   1.0047   0.02119   0.01208  -0.0372   0.1546   1.0000
   7.750   1.0135   0.02292   0.01341  -0.0353   0.1001   1.0000
   8.000   1.0237   0.02445   0.01479  -0.0334   0.0751   1.0000
   8.250   1.0344   0.02585   0.01615  -0.0316   0.0617   1.0000
   8.500   1.0445   0.02722   0.01755  -0.0297   0.0527   1.0000
   8.750   1.0533   0.02858   0.01902  -0.0276   0.0476   1.0000
   9.000   1.0601   0.02992   0.02043  -0.0254   0.0432   1.0000
   9.250   1.0644   0.03155   0.02208  -0.0232   0.0397   1.0000
   9.500   1.0727   0.03302   0.02370  -0.0214   0.0366   1.0000
   9.750   1.0808   0.03464   0.02542  -0.0198   0.0345   1.0000
  10.000   1.0889   0.03635   0.02721  -0.0183   0.0327   1.0000
  10.250   1.0973   0.03840   0.02924  -0.0170   0.0307   1.0000
  10.500   1.1102   0.03999   0.03106  -0.0158   0.0288   1.0000
  10.750   1.1223   0.04178   0.03301  -0.0148   0.0270   1.0000
  11.000   1.1348   0.04376   0.03514  -0.0137   0.0258   1.0000
  11.250   1.1465   0.04587   0.03740  -0.0128   0.0249   1.0000
  11.500   1.1570   0.04818   0.03983  -0.0119   0.0240   1.0000
  11.750   1.1673   0.05089   0.04267  -0.0111   0.0233   1.0000
  12.000   1.1727   0.05404   0.04609  -0.0102   0.0227   1.0000
  12.250   1.1718   0.05709   0.04946  -0.0095   0.0222   1.0000
  12.500   1.1675   0.06047   0.05318  -0.0090   0.0217   1.0000
  12.750   1.1598   0.06418   0.05719  -0.0089   0.0211   1.0000
  13.000   1.1506   0.06827   0.06156  -0.0093   0.0206   1.0000
  13.250   1.1390   0.07282   0.06638  -0.0102   0.0203   1.0000
  13.500   1.1253   0.07784   0.07166  -0.0117   0.0201   1.0000
  13.750   1.1089   0.08359   0.07766  -0.0139   0.0201   1.0000
  14.000   1.0907   0.08996   0.08426  -0.0169   0.0201   1.0000
  14.250   1.0700   0.09721   0.09174  -0.0208   0.0202   1.0000
  14.500   1.0480   0.10546   0.10019  -0.0257   0.0204   1.0000
  14.750   1.0240   0.11496   0.10988  -0.0318   0.0207   1.0000
  15.000   0.9991   0.12590   0.12096  -0.0389   0.0212   1.0000
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