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Falcon (falcon-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Falcon (falcon-il)
Reynolds number: 50,000
Max Cl/Cd: 30.2 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-falcon-il-50000-n5.txt
Download as CSV file: xf-falcon-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Falcon                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5709   0.09761   0.09012  -0.0285   1.0000   0.0635
 -10.750  -0.5889   0.08926   0.08179  -0.0338   1.0000   0.0630
 -10.500  -0.6145   0.08148   0.07400  -0.0388   1.0000   0.0624
 -10.250  -0.6426   0.07523   0.06768  -0.0414   1.0000   0.0619
 -10.000  -0.6690   0.07048   0.06282  -0.0411   1.0000   0.0616
  -9.750  -0.6924   0.06653   0.05874  -0.0389   1.0000   0.0616
  -9.500  -0.7096   0.06261   0.05460  -0.0366   1.0000   0.0617
  -9.250  -0.7220   0.05886   0.05058  -0.0340   1.0000   0.0622
  -9.000  -0.7308   0.05527   0.04664  -0.0311   1.0000   0.0631
  -8.750  -0.7368   0.05177   0.04268  -0.0279   1.0000   0.0645
  -8.500  -0.7340   0.04895   0.03957  -0.0253   1.0000   0.0661
  -8.250  -0.7230   0.04706   0.03761  -0.0235   1.0000   0.0681
  -8.000  -0.7128   0.04485   0.03520  -0.0214   1.0000   0.0701
  -7.750  -0.7020   0.04247   0.03252  -0.0192   1.0000   0.0721
  -7.500  -0.6903   0.04021   0.02982  -0.0169   1.0000   0.0754
  -7.250  -0.6755   0.03832   0.02772  -0.0150   1.0000   0.0788
  -7.000  -0.6586   0.03687   0.02622  -0.0135   1.0000   0.0824
  -6.750  -0.6406   0.03522   0.02431  -0.0119   1.0000   0.0868
  -6.500  -0.6222   0.03373   0.02266  -0.0103   1.0000   0.0921
  -6.250  -0.6034   0.03256   0.02146  -0.0089   1.0000   0.0978
  -6.000  -0.5829   0.03129   0.01996  -0.0075   1.0000   0.1049
  -5.750  -0.5643   0.03028   0.01903  -0.0061   1.0000   0.1126
  -5.500  -0.5442   0.02924   0.01790  -0.0047   1.0000   0.1217
  -5.250  -0.5256   0.02838   0.01698  -0.0031   1.0000   0.1327
  -5.000  -0.5078   0.02750   0.01616  -0.0015   1.0000   0.1443
  -4.750  -0.4906   0.02668   0.01536   0.0002   1.0000   0.1577
  -4.500  -0.4743   0.02591   0.01461   0.0019   1.0000   0.1733
  -4.000  -0.4439   0.02439   0.01324   0.0054   1.0000   0.2148
  -3.750  -0.4300   0.02350   0.01270   0.0071   1.0000   0.2484
  -3.500  -0.4042   0.02203   0.01222   0.0063   0.9910   0.3835
  -3.250  -0.3723   0.02116   0.01221   0.0059   0.9777   0.5698
  -3.000  -0.3320   0.02106   0.01244   0.0048   0.9658   0.6805
  -2.750  -0.2860   0.02127   0.01271   0.0029   0.9548   0.7587
  -2.500  -0.2372   0.02157   0.01291   0.0002   0.9431   0.8148
  -2.250  -0.1788   0.02197   0.01315  -0.0041   0.9326   0.8562
  -2.000  -0.1111   0.02243   0.01338  -0.0103   0.9235   0.8940
  -1.750  -0.0378   0.02263   0.01334  -0.0182   0.9123   0.9164
  -1.500   0.0189   0.02249   0.01300  -0.0238   0.8954   0.9295
  -1.250   0.0694   0.02233   0.01266  -0.0284   0.8748   0.9417
  -1.000   0.1216   0.02213   0.01229  -0.0332   0.8534   0.9522
  -0.750   0.1712   0.02191   0.01189  -0.0375   0.8319   0.9631
  -0.500   0.2168   0.02172   0.01155  -0.0411   0.8084   0.9744
  -0.250   0.2611   0.02155   0.01122  -0.0444   0.7856   0.9860
   0.000   0.3049   0.02139   0.01089  -0.0478   0.7634   0.9973
   0.250   0.3314   0.02130   0.01066  -0.0479   0.7414   1.0000
   0.500   0.3519   0.02125   0.01048  -0.0468   0.7215   1.0000
   0.750   0.3725   0.02124   0.01033  -0.0456   0.7026   1.0000
   1.000   0.3932   0.02126   0.01022  -0.0444   0.6848   1.0000
   1.250   0.4137   0.02132   0.01017  -0.0432   0.6675   1.0000
   1.500   0.4340   0.02142   0.01017  -0.0419   0.6507   1.0000
   1.750   0.4543   0.02154   0.01020  -0.0406   0.6346   1.0000
   2.000   0.4747   0.02170   0.01028  -0.0394   0.6191   1.0000
   2.250   0.4954   0.02188   0.01040  -0.0382   0.6036   1.0000
   2.500   0.5161   0.02210   0.01056  -0.0370   0.5884   1.0000
   2.750   0.5367   0.02233   0.01075  -0.0358   0.5737   1.0000
   3.000   0.5573   0.02259   0.01098  -0.0346   0.5592   1.0000
   3.250   0.5778   0.02286   0.01122  -0.0333   0.5453   1.0000
   3.500   0.5982   0.02315   0.01146  -0.0320   0.5316   1.0000
   3.750   0.6191   0.02343   0.01171  -0.0307   0.5185   1.0000
   4.000   0.6397   0.02373   0.01196  -0.0294   0.5052   1.0000
   4.250   0.6594   0.02409   0.01233  -0.0280   0.4913   1.0000
   4.500   0.6791   0.02446   0.01270  -0.0266   0.4777   1.0000
   4.750   0.6992   0.02484   0.01309  -0.0252   0.4646   1.0000
   5.000   0.7196   0.02521   0.01345  -0.0239   0.4520   1.0000
   5.250   0.7406   0.02556   0.01375  -0.0226   0.4399   1.0000
   5.500   0.7596   0.02602   0.01426  -0.0211   0.4266   1.0000
   5.750   0.7789   0.02650   0.01481  -0.0197   0.4138   1.0000
   6.000   0.7984   0.02698   0.01531  -0.0183   0.4015   1.0000
   6.250   0.8187   0.02743   0.01575  -0.0169   0.3899   1.0000
   6.500   0.8381   0.02795   0.01633  -0.0155   0.3781   1.0000
   6.750   0.8562   0.02856   0.01702  -0.0140   0.3659   1.0000
   7.000   0.8751   0.02916   0.01767  -0.0126   0.3547   1.0000
   7.250   0.8958   0.02966   0.01813  -0.0114   0.3446   1.0000
   7.500   0.9122   0.03044   0.01908  -0.0097   0.3330   1.0000
   7.750   0.9300   0.03118   0.01991  -0.0083   0.3227   1.0000
   8.000   0.9503   0.03179   0.02051  -0.0071   0.3137   1.0000
   8.250   0.9653   0.03276   0.02165  -0.0054   0.3035   1.0000
   8.500   0.9840   0.03351   0.02246  -0.0041   0.2950   1.0000
   8.750   0.9997   0.03448   0.02358  -0.0025   0.2862   1.0000
   9.000   1.0172   0.03543   0.02463  -0.0012   0.2788   1.0000
   9.250   1.0321   0.03651   0.02586   0.0004   0.2710   1.0000
   9.500   1.0495   0.03748   0.02691   0.0017   0.2643   1.0000
   9.750   1.0609   0.03880   0.02848   0.0035   0.2570   1.0000
  10.000   1.0830   0.03954   0.02921   0.0043   0.2514   1.0000
  10.250   1.0868   0.04146   0.03148   0.0066   0.2452   1.0000
  10.500   1.1003   0.04274   0.03290   0.0081   0.2397   1.0000
  10.750   1.1160   0.04391   0.03420   0.0094   0.2347   1.0000
  11.000   1.1128   0.04617   0.03678   0.0121   0.2293   1.0000
  11.250   1.1236   0.04758   0.03834   0.0137   0.2243   1.0000
  11.500   1.1347   0.04894   0.03982   0.0153   0.2195   1.0000
  11.750   1.1132   0.05207   0.04323   0.0190   0.2153   1.0000
  12.000   1.1374   0.05130   0.04237   0.0203   0.2056   1.0000
  12.250   1.1063   0.05554   0.04691   0.0232   0.2025   1.0000
  12.500   1.0717   0.06113   0.05272   0.0240   0.1998   1.0000
  13.000   1.0420   0.06890   0.06066   0.0236   0.1881   1.0000
  13.250   0.9682   0.08430   0.07613   0.0174   0.1909   1.0000
  13.500   0.8205   0.11595   0.10738   0.0007   0.1841   1.0000
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