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Fage & Collins 2 (fg2-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: Fage & Collins 2 (fg2-il)
Reynolds number: 500,000
Max Cl/Cd: 90.12 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fg2-il-500000-n5.txt
Download as CSV file: xf-fg2-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Fage & Collins 2                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4223   0.08662   0.08450  -0.0181   1.0000   0.0065
  -8.000  -0.4287   0.08394   0.08186  -0.0180   1.0000   0.0069
  -7.750  -0.4403   0.08106   0.07902  -0.0173   1.0000   0.0066
  -7.500  -0.4423   0.07753   0.07551  -0.0185   1.0000   0.0068
  -7.250  -0.4246   0.07158   0.06953  -0.0261   0.9973   0.0071
  -7.000  -0.4018   0.06501   0.06289  -0.0345   0.9935   0.0071
  -6.750  -0.3785   0.05593   0.05366  -0.0438   0.9883   0.0081
  -6.500  -0.3572   0.04989   0.04746  -0.0485   0.9829   0.0085
  -6.000  -0.3119   0.04240   0.03967  -0.0527   0.9712   0.0092
  -5.750  -0.2937   0.03823   0.03529  -0.0529   0.9617   0.0097
  -5.500  -0.2828   0.03085   0.02743  -0.0512   0.9492   0.0112
  -5.250  -0.2619   0.02804   0.02439  -0.0505   0.9389   0.0120
  -5.000  -0.2347   0.02630   0.02247  -0.0509   0.9304   0.0126
  -4.750  -0.2136   0.01984   0.01521  -0.0488   0.9224   0.0157
  -4.500  -0.1747   0.01902   0.01426  -0.0516   0.9150   0.0165
  -4.250  -0.1289   0.01837   0.01347  -0.0559   0.9056   0.0174
  -4.000  -0.0721   0.01673   0.01148  -0.0624   0.8928   0.0198
  -3.750  -0.0213   0.01574   0.01001  -0.0670   0.8723   0.0217
  -3.500   0.0108   0.01416   0.00818  -0.0683   0.8477   0.0229
  -3.250   0.0398   0.01381   0.00770  -0.0687   0.8152   0.0240
  -2.750   0.0848   0.01302   0.00634  -0.0660   0.7198   0.0254
  -2.250   0.1274   0.01236   0.00520  -0.0629   0.6495   0.0263
  -2.000   0.1503   0.01211   0.00479  -0.0618   0.6256   0.0271
  -1.750   0.1734   0.01178   0.00432  -0.0606   0.6054   0.0274
  -1.500   0.1969   0.01146   0.00388  -0.0596   0.5886   0.0277
  -1.250   0.2206   0.01121   0.00354  -0.0586   0.5739   0.0282
  -1.000   0.2443   0.01100   0.00325  -0.0577   0.5603   0.0286
  -0.750   0.2681   0.01087   0.00304  -0.0567   0.5474   0.0291
  -0.500   0.2920   0.01073   0.00285  -0.0558   0.5348   0.0294
  -0.250   0.3159   0.01060   0.00268  -0.0549   0.5225   0.0297
   0.000   0.3388   0.01038   0.00240  -0.0538   0.5098   0.0300
   0.250   0.3617   0.01022   0.00218  -0.0528   0.4957   0.0306
   0.500   0.3847   0.01011   0.00200  -0.0517   0.4790   0.0317
   0.750   0.4082   0.01008   0.00191  -0.0508   0.4611   0.0317
   1.000   0.4318   0.01009   0.00184  -0.0499   0.4415   0.0317
   1.250   0.4556   0.01012   0.00178  -0.0490   0.4223   0.0318
   1.500   0.4796   0.01016   0.00174  -0.0482   0.4056   0.0320
   1.750   0.5033   0.01023   0.00174  -0.0473   0.3877   0.0323
   2.000   0.5274   0.01030   0.00174  -0.0465   0.3740   0.0331
   2.250   0.5516   0.01039   0.00177  -0.0458   0.3611   0.0336
   2.500   0.5759   0.01047   0.00182  -0.0451   0.3506   0.0351
   2.750   0.6001   0.01057   0.00188  -0.0443   0.3418   0.0375
   3.000   0.6248   0.01063   0.00196  -0.0437   0.3344   0.0489
   3.500   0.8095   0.00942   0.00283  -0.0747   0.3066   1.0000
   3.750   0.8331   0.00958   0.00297  -0.0738   0.2997   1.0000
   4.000   0.8570   0.00971   0.00311  -0.0731   0.2935   1.0000
   4.250   0.8804   0.00987   0.00326  -0.0722   0.2846   1.0000
   4.500   0.9036   0.01006   0.00342  -0.0713   0.2704   1.0000
   4.750   0.9264   0.01028   0.00359  -0.0704   0.2529   1.0000
   5.000   0.9481   0.01058   0.00378  -0.0693   0.2224   1.0000
   5.250   0.9633   0.01143   0.00422  -0.0672   0.1522   1.0000
   5.500   0.9826   0.01195   0.00462  -0.0657   0.1277   1.0000
   5.750   1.0033   0.01234   0.00494  -0.0644   0.1117   1.0000
   6.000   1.0236   0.01276   0.00528  -0.0631   0.0909   1.0000
   6.250   1.0337   0.01404   0.00613  -0.0600   0.0213   1.0000
   6.500   1.0539   0.01445   0.00657  -0.0586   0.0147   1.0000
   6.750   1.0741   0.01486   0.00707  -0.0573   0.0128   1.0000
   7.000   1.0934   0.01533   0.00762  -0.0557   0.0113   1.0000
   7.250   1.1108   0.01597   0.00838  -0.0538   0.0096   1.0000
   7.500   1.1304   0.01638   0.00885  -0.0524   0.0090   1.0000
   7.750   1.1485   0.01690   0.00946  -0.0507   0.0083   1.0000
   8.000   1.1657   0.01747   0.01012  -0.0488   0.0077   1.0000
   8.250   1.1821   0.01809   0.01081  -0.0469   0.0072   1.0000
   8.500   1.1956   0.01888   0.01169  -0.0445   0.0067   1.0000
   8.750   1.2051   0.01992   0.01283  -0.0414   0.0063   1.0000
   9.000   1.2176   0.02070   0.01371  -0.0389   0.0062   1.0000
   9.250   1.2332   0.02124   0.01432  -0.0370   0.0057   1.0000
   9.500   1.2424   0.02212   0.01530  -0.0339   0.0054   1.0000
   9.750   1.2506   0.02283   0.01611  -0.0307   0.0051   1.0000
  10.000   1.2535   0.02379   0.01717  -0.0266   0.0050   1.0000
  10.250   1.2596   0.02465   0.01811  -0.0233   0.0048   1.0000
  10.500   1.2657   0.02557   0.01911  -0.0203   0.0047   1.0000
  10.750   1.2681   0.02676   0.02040  -0.0169   0.0045   1.0000
  11.000   1.2687   0.02814   0.02186  -0.0137   0.0043   1.0000
  11.250   1.2691   0.02966   0.02350  -0.0107   0.0043   1.0000
  11.500   1.2618   0.03192   0.02586  -0.0076   0.0041   1.0000
  11.750   1.2623   0.03376   0.02784  -0.0056   0.0041   1.0000
  12.000   1.2588   0.03613   0.03033  -0.0038   0.0041   1.0000
  12.250   1.2593   0.03835   0.03270  -0.0027   0.0040   1.0000
  12.500   1.2568   0.04106   0.03555  -0.0019   0.0039   1.0000
  12.750   1.2542   0.04397   0.03862  -0.0015   0.0039   1.0000
  13.000   1.2503   0.04726   0.04206  -0.0015   0.0038   1.0000
  13.250   1.2454   0.05081   0.04576  -0.0018   0.0037   1.0000
  13.500   1.2391   0.05467   0.04977  -0.0022   0.0037   1.0000
  13.750   1.2331   0.05861   0.05387  -0.0030   0.0036   1.0000
  14.000   1.2285   0.06249   0.05788  -0.0042   0.0035   1.0000
  14.250   1.2177   0.06722   0.06276  -0.0052   0.0035   1.0000
  14.500   1.2081   0.07197   0.06767  -0.0066   0.0035   1.0000
  14.750   1.1985   0.07685   0.07269  -0.0082   0.0035   1.0000
  15.000   1.1869   0.08224   0.07822  -0.0101   0.0035   1.0000
  15.250   1.1795   0.08718   0.08329  -0.0123   0.0034   1.0000
  15.500   1.1776   0.09149   0.08767  -0.0149   0.0031   1.0000
  15.750   1.1554   0.09904   0.09543  -0.0174   0.0033   1.0000
  16.000   1.1378   0.10623   0.10279  -0.0204   0.0035   1.0000
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