XFOIL         Version 6.94
  
 Calculated polar for: WORTMANN FX 08-S-176 AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.080     Re =     0.450 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.4948   0.01449   0.00910  -0.0814  0.5601  0.8447
   0.500   0.5118   0.01534   0.01011  -0.0705  0.5575  0.8912
   1.000   0.5517   0.01540   0.01017  -0.0667  0.5536  0.9077
   1.500   0.6006   0.01548   0.01019  -0.0656  0.5501  0.9185
   2.000   0.6453   0.01542   0.01010  -0.0634  0.5474  0.9274
   2.500   0.6971   0.01541   0.01003  -0.0632  0.5449  0.9341
   3.000   0.7513   0.01533   0.00987  -0.0636  0.5424  0.9384
   3.500   0.8030   0.01567   0.01015  -0.0636  0.5388  0.9424
   4.000   0.8496   0.01557   0.01015  -0.0626  0.5358  0.9483
   4.500   0.8961   0.01563   0.01027  -0.0618  0.5318  0.9525
   5.000   0.9659   0.01320   0.00754  -0.0638  0.5175  0.9551
   5.500   1.0112   0.01196   0.00624  -0.0618  0.4981  0.9605
   6.000   1.0512   0.01167   0.00596  -0.0595  0.4721  0.9656
   6.500   1.0832   0.01178   0.00599  -0.0560  0.4442  0.9711
   7.000   1.0821   0.01312   0.00699  -0.0478  0.3760  0.9812
   7.500   1.0812   0.01607   0.00974  -0.0434  0.3237  0.9921
   8.000   1.0726   0.02005   0.01373  -0.0402  0.2956  1.0000
   8.500   1.0296   0.02744   0.02095  -0.0361  0.2398  1.0000
   9.000   0.9813   0.03503   0.02823  -0.0313  0.1738  1.0000
   9.500   0.9347   0.04317   0.03592  -0.0275  0.0742  1.0000
  10.000   0.9259   0.04896   0.04148  -0.0261  0.0039  1.0000
  10.500   0.9476   0.05228   0.04490  -0.0262  0.0036  1.0000
  11.000   0.9702   0.05556   0.04828  -0.0263  0.0035  1.0000
  11.500   0.9889   0.05935   0.05220  -0.0265  0.0036  1.0000
  12.000   1.0068   0.06331   0.05629  -0.0267  0.0036  1.0000
  12.500   1.0204   0.06788   0.06101  -0.0270  0.0038  1.0000
  13.000   1.0322   0.07276   0.06605  -0.0275  0.0038  1.0000
  13.500   1.0366   0.07878   0.07221  -0.0282  0.0040  1.0000
  14.000   1.0482   0.08403   0.07759  -0.0291  0.0041  1.0000
  14.500   1.0568   0.08989   0.08360  -0.0302  0.0045  1.0000
  15.000   1.0605   0.09655   0.09040  -0.0316  0.0048  1.0000
  15.500   1.0655   0.10299   0.09696  -0.0331  0.0051  1.0000
  16.000   1.0755   0.10844   0.10242  -0.0343  0.0055  1.0000
  16.500   1.0981   0.11238   0.10654  -0.0353  0.0065  1.0000
  17.000   0.9709   0.12024   0.11541  -0.0373  0.0067  1.0000