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Fage & Collins 3 (fg3-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: Fage & Collins 3 (fg3-il)
Reynolds number: 500,000
Max Cl/Cd: 89.03 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fg3-il-500000-n5.txt
Download as CSV file: xf-fg3-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Fage & Collins 3                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2630   0.08321   0.08106  -0.0530   0.9810   0.0079
  -8.000  -0.2604   0.07549   0.07337  -0.0584   0.9489   0.0079
  -7.750  -0.2502   0.06954   0.06739  -0.0658   0.9376   0.0082
  -7.500  -0.2275   0.06234   0.06010  -0.0761   0.9303   0.0083
  -7.250  -0.2007   0.05436   0.05197  -0.0869   0.9237   0.0092
  -7.000  -0.1640   0.04920   0.04664  -0.0954   0.9178   0.0094
  -6.750  -0.1277   0.04499   0.04225  -0.1021   0.9122   0.0102
  -6.500  -0.1003   0.03924   0.03620  -0.1070   0.9041   0.0107
  -6.250  -0.0944   0.03111   0.02754  -0.1061   0.8946   0.0121
  -6.000  -0.0699   0.02926   0.02548  -0.1067   0.8866   0.0124
  -5.750  -0.0497   0.02870   0.02485  -0.1059   0.8785   0.0131
  -5.500  -0.0326   0.02637   0.02225  -0.1043   0.8710   0.0139
  -5.250  -0.0308   0.02125   0.01650  -0.0987   0.8619   0.0161
  -5.000  -0.0102   0.02069   0.01583  -0.0975   0.8536   0.0165
  -4.750   0.0120   0.02057   0.01566  -0.0966   0.8450   0.0172
  -4.500   0.0298   0.01935   0.01423  -0.0945   0.8375   0.0182
  -4.250   0.0479   0.01740   0.01182  -0.0918   0.8295   0.0201
  -4.000   0.0662   0.01631   0.01050  -0.0898   0.8195   0.0211
  -3.750   0.0875   0.01568   0.00978  -0.0885   0.8093   0.0217
  -3.500   0.1091   0.01509   0.00907  -0.0872   0.7966   0.0222
  -3.250   0.1307   0.01453   0.00836  -0.0858   0.7803   0.0229
  -3.000   0.1527   0.01401   0.00767  -0.0843   0.7616   0.0240
  -2.750   0.1742   0.01360   0.00705  -0.0828   0.7392   0.0250
  -2.500   0.1950   0.01318   0.00639  -0.0811   0.7121   0.0255
  -2.250   0.2150   0.01286   0.00585  -0.0792   0.6816   0.0258
  -2.000   0.2336   0.01270   0.00546  -0.0771   0.6441   0.0262
  -1.750   0.2502   0.01269   0.00520  -0.0745   0.5981   0.0266
  -1.500   0.2663   0.01253   0.00477  -0.0720   0.5514   0.0272
  -1.250   0.2832   0.01226   0.00428  -0.0696   0.5100   0.0275
  -1.000   0.3020   0.01204   0.00391  -0.0677   0.4806   0.0277
  -0.750   0.3213   0.01185   0.00360  -0.0659   0.4573   0.0281
  -0.500   0.3413   0.01169   0.00335  -0.0643   0.4394   0.0285
  -0.250   0.3616   0.01156   0.00315  -0.0627   0.4237   0.0292
   0.000   0.3822   0.01149   0.00300  -0.0612   0.4094   0.0297
   0.250   0.4032   0.01143   0.00287  -0.0597   0.3968   0.0301
   0.500   0.4246   0.01137   0.00276  -0.0584   0.3855   0.0303
   0.750   0.4462   0.01134   0.00268  -0.0570   0.3757   0.0310
   1.000   0.4679   0.01134   0.00263  -0.0558   0.3670   0.0320
   1.250   0.4901   0.01131   0.00257  -0.0546   0.3596   0.0323
   1.500   0.5120   0.01133   0.00253  -0.0534   0.3521   0.0323
   1.750   0.5344   0.01133   0.00251  -0.0523   0.3458   0.0327
   2.000   0.5567   0.01137   0.00250  -0.0511   0.3395   0.0329
   2.250   0.5788   0.01142   0.00251  -0.0500   0.3337   0.0333
   2.500   0.6013   0.01147   0.00253  -0.0489   0.3279   0.0342
   2.750   0.6230   0.01155   0.00257  -0.0477   0.3222   0.0350
   3.000   0.6449   0.01161   0.00261  -0.0465   0.3172   0.0367
   3.250   0.6667   0.01167   0.00267  -0.0453   0.3126   0.0401
   3.750   0.9180   0.01092   0.00398  -0.0918   0.2938   1.0000
   4.000   0.9398   0.01109   0.00413  -0.0906   0.2904   1.0000
   4.250   0.9625   0.01122   0.00428  -0.0897   0.2871   1.0000
   4.500   0.9847   0.01137   0.00444  -0.0887   0.2836   1.0000
   4.750   1.0065   0.01155   0.00461  -0.0876   0.2800   1.0000
   5.000   1.0276   0.01175   0.00480  -0.0864   0.2762   1.0000
   5.250   1.0500   0.01190   0.00499  -0.0854   0.2717   1.0000
   5.500   1.0714   0.01208   0.00517  -0.0842   0.2651   1.0000
   5.750   1.0924   0.01228   0.00536  -0.0830   0.2572   1.0000
   6.000   1.1125   0.01253   0.00557  -0.0817   0.2454   1.0000
   6.250   1.1334   0.01273   0.00577  -0.0805   0.2361   1.0000
   6.500   1.1532   0.01299   0.00601  -0.0791   0.2246   1.0000
   6.750   1.1725   0.01328   0.00627  -0.0777   0.2138   1.0000
   7.000   1.1892   0.01372   0.00660  -0.0758   0.1891   1.0000
   7.250   1.1928   0.01504   0.00743  -0.0717   0.1131   1.0000
   7.500   1.1845   0.01696   0.00885  -0.0654   0.0210   1.0000
   7.750   1.1980   0.01744   0.00935  -0.0629   0.0157   1.0000
   8.000   1.2129   0.01783   0.00980  -0.0606   0.0144   1.0000
   8.250   1.2269   0.01828   0.01033  -0.0583   0.0127   1.0000
   8.500   1.2397   0.01883   0.01094  -0.0558   0.0113   1.0000
   8.750   1.2504   0.01951   0.01173  -0.0529   0.0101   1.0000
   9.000   1.2632   0.02007   0.01237  -0.0505   0.0097   1.0000
   9.250   1.2757   0.02065   0.01302  -0.0482   0.0090   1.0000
   9.500   1.2867   0.02133   0.01378  -0.0457   0.0086   1.0000
   9.750   1.2963   0.02210   0.01463  -0.0430   0.0080   1.0000
  10.000   1.3059   0.02287   0.01547  -0.0405   0.0077   1.0000
  10.250   1.3104   0.02397   0.01667  -0.0374   0.0071   1.0000
  10.500   1.3170   0.02497   0.01776  -0.0348   0.0067   1.0000
  10.750   1.3213   0.02617   0.01907  -0.0320   0.0065   1.0000
  11.000   1.3269   0.02734   0.02033  -0.0296   0.0063   1.0000
  11.250   1.3281   0.02884   0.02195  -0.0269   0.0061   1.0000
  11.500   1.3301   0.03039   0.02361  -0.0245   0.0059   1.0000
  11.750   1.3297   0.03219   0.02551  -0.0222   0.0058   1.0000
  12.000   1.3301   0.03404   0.02747  -0.0203   0.0056   1.0000
  12.250   1.3279   0.03623   0.02977  -0.0184   0.0054   1.0000
  12.500   1.3254   0.03862   0.03229  -0.0170   0.0054   1.0000
  12.750   1.3239   0.04108   0.03484  -0.0159   0.0052   1.0000
  13.000   1.3169   0.04430   0.03817  -0.0151   0.0051   1.0000
  13.250   1.3093   0.04785   0.04186  -0.0147   0.0051   1.0000
  13.500   1.3034   0.05146   0.04558  -0.0148   0.0050   1.0000
  13.750   1.2922   0.05599   0.05023  -0.0153   0.0049   1.0000
  14.000   1.2846   0.06025   0.05460  -0.0162   0.0048   1.0000
  14.250   1.2773   0.06465   0.05910  -0.0172   0.0045   1.0000
  14.500   1.2601   0.07034   0.06491  -0.0183   0.0046   1.0000
  14.750   1.2521   0.07483   0.06951  -0.0192   0.0046   1.0000
  15.000   1.2443   0.07925   0.07403  -0.0201   0.0045   1.0000
  15.250   1.2422   0.08305   0.07795  -0.0212   0.0044   1.0000
  15.500   1.2339   0.08747   0.08244  -0.0220   0.0044   1.0000
  15.750   1.2309   0.09141   0.08650  -0.0231   0.0042   1.0000
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