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Fage & Collins 3 (fg3-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Fage & Collins 3 (fg3-il)
Reynolds number: 500,000
Max Cl/Cd: 90.36 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fg3-il-500000.txt
Download as CSV file: xf-fg3-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3440   0.10819   0.10604  -0.0304   1.0000   0.0159
  -9.500  -0.3480   0.10552   0.10341  -0.0303   1.0000   0.0160
  -9.250  -0.3613   0.10348   0.10142  -0.0288   1.0000   0.0160
  -9.000  -0.3581   0.09935   0.09732  -0.0297   0.9991   0.0161
  -8.750  -0.3440   0.09562   0.09358  -0.0307   0.9977   0.0163
  -8.500  -0.3275   0.09196   0.08991  -0.0337   0.9957   0.0167
  -8.250  -0.3131   0.08789   0.08585  -0.0383   0.9930   0.0168
  -8.000  -0.2973   0.08425   0.08220  -0.0428   0.9893   0.0178
  -7.750  -0.2813   0.07964   0.07759  -0.0496   0.9856   0.0181
  -7.500  -0.2710   0.07550   0.07345  -0.0548   0.9777   0.0187
  -7.250  -0.2497   0.06923   0.06711  -0.0651   0.9696   0.0199
  -7.000  -0.2250   0.06276   0.06050  -0.0742   0.9628   0.0202
  -6.750  -0.2092   0.05782   0.05540  -0.0775   0.9552   0.0203
  -6.500  -0.1882   0.05300   0.05042  -0.0805   0.9508   0.0204
  -6.250  -0.1790   0.04768   0.04505  -0.0817   0.9460   0.0208
  -6.000  -0.1603   0.04499   0.04231  -0.0827   0.9406   0.0212
  -5.750  -0.1338   0.04203   0.03925  -0.0852   0.9372   0.0219
  -5.500  -0.1066   0.03883   0.03589  -0.0873   0.9323   0.0231
  -5.250  -0.0672   0.03562   0.03212  -0.0889   0.9265   0.0258
  -5.000  -0.0388   0.02949   0.02561  -0.0918   0.9226   0.0265
  -4.750  -0.0125   0.02726   0.02330  -0.0930   0.9156   0.0271
  -4.500   0.0202   0.02545   0.02136  -0.0952   0.9101   0.0284
  -4.250   0.0484   0.02394   0.01961  -0.0954   0.9033   0.0312
  -4.000   0.0699   0.02197   0.01704  -0.0932   0.8956   0.0339
  -3.750   0.0918   0.02009   0.01513  -0.0928   0.8884   0.0350
  -3.500   0.1154   0.01901   0.01394  -0.0922   0.8805   0.0366
  -3.250   0.1362   0.01825   0.01302  -0.0905   0.8722   0.0395
  -3.000   0.1582   0.01703   0.01148  -0.0890   0.8646   0.0446
  -2.750   0.1769   0.01618   0.01063  -0.0872   0.8554   0.0471
  -2.500   0.2019   0.01642   0.01071  -0.0861   0.8466   0.0532
  -2.250   0.2198   0.01469   0.00888  -0.0843   0.8365   0.0590
  -2.000   0.2409   0.01455   0.00867  -0.0826   0.8250   0.0653
  -1.750   0.2610   0.01357   0.00763  -0.0811   0.8128   0.0760
  -1.000   0.3378   0.01092   0.00440  -0.0771   0.7572   0.0474
  -0.750   0.3595   0.01065   0.00393  -0.0753   0.7283   0.0440
  -0.500   0.3786   0.01053   0.00364  -0.0731   0.6933   0.0435
  -0.250   0.3942   0.01038   0.00330  -0.0703   0.6501   0.0437
   0.000   0.4069   0.01048   0.00315  -0.0668   0.5958   0.0432
   0.250   0.4194   0.01069   0.00310  -0.0634   0.5425   0.0427
   0.500   0.4335   0.01073   0.00293  -0.0604   0.5025   0.0425
   0.750   0.4500   0.01074   0.00278  -0.0579   0.4733   0.0425
   1.000   0.4676   0.01072   0.00262  -0.0557   0.4506   0.0431
   1.250   0.4867   0.01073   0.00251  -0.0538   0.4328   0.0440
   1.500   0.5070   0.01078   0.00247  -0.0522   0.4179   0.0449
   1.750   0.5280   0.01085   0.00245  -0.0508   0.4050   0.0468
   2.000   0.5497   0.01091   0.00246  -0.0495   0.3938   0.0496
   2.250   0.5713   0.01101   0.00250  -0.0482   0.3843   0.0526
   2.500   0.7984   0.00999   0.00350  -0.0950   0.3564   1.0000
   2.750   0.8207   0.01014   0.00360  -0.0939   0.3494   1.0000
   3.000   0.8419   0.01035   0.00373  -0.0927   0.3434   1.0000
   3.250   0.8648   0.01047   0.00385  -0.0917   0.3379   1.0000
   3.500   0.8867   0.01065   0.00400  -0.0906   0.3326   1.0000
   3.750   0.9082   0.01086   0.00417  -0.0894   0.3276   1.0000
   4.000   0.9310   0.01100   0.00432  -0.0884   0.3230   1.0000
   4.250   0.9529   0.01119   0.00449  -0.0873   0.3183   1.0000
   4.500   0.9738   0.01146   0.00472  -0.0860   0.3139   1.0000
   4.750   0.9968   0.01157   0.00489  -0.0851   0.3093   1.0000
   5.000   1.0189   0.01175   0.00506  -0.0841   0.3047   1.0000
   5.250   1.0396   0.01198   0.00525  -0.0828   0.2981   1.0000
   5.500   1.0622   0.01209   0.00542  -0.0819   0.2925   1.0000
   5.750   1.0828   0.01231   0.00560  -0.0806   0.2859   1.0000
   6.000   1.1047   0.01247   0.00581  -0.0795   0.2811   1.0000
   6.250   1.1258   0.01262   0.00597  -0.0783   0.2729   1.0000
   6.500   1.1469   0.01280   0.00618  -0.0772   0.2666   1.0000
   6.750   1.1674   0.01298   0.00636  -0.0759   0.2577   1.0000
   7.000   1.1882   0.01315   0.00654  -0.0747   0.2456   1.0000
   7.250   1.2067   0.01343   0.00675  -0.0731   0.2277   1.0000
   7.500   1.2205   0.01406   0.00712  -0.0707   0.1782   1.0000
   7.750   1.2057   0.01656   0.00877  -0.0635   0.0453   1.0000
   8.000   1.2114   0.01753   0.00965  -0.0595   0.0240   1.0000
   8.250   1.2248   0.01801   0.01022  -0.0569   0.0217   1.0000
   8.500   1.2363   0.01861   0.01089  -0.0540   0.0200   1.0000
   8.750   1.2456   0.01935   0.01171  -0.0508   0.0186   1.0000
   9.000   1.2506   0.02033   0.01284  -0.0470   0.0174   1.0000
   9.250   1.2599   0.02106   0.01367  -0.0440   0.0167   1.0000
   9.500   1.2693   0.02180   0.01449  -0.0412   0.0159   1.0000
   9.750   1.2740   0.02281   0.01560  -0.0377   0.0152   1.0000
  10.000   1.2807   0.02373   0.01660  -0.0348   0.0146   1.0000
  10.250   1.2845   0.02485   0.01782  -0.0316   0.0143   1.0000
  10.500   1.2854   0.02620   0.01925  -0.0284   0.0138   1.0000
  10.750   1.2803   0.02803   0.02120  -0.0247   0.0134   1.0000
  11.000   1.2817   0.02955   0.02282  -0.0221   0.0134   1.0000
  11.250   1.2611   0.03280   0.02620  -0.0178   0.0128   1.0000
  11.500   1.2601   0.03480   0.02830  -0.0157   0.0128   1.0000
  11.750   1.2501   0.03774   0.03135  -0.0132   0.0125   1.0000
  12.000   1.2512   0.03985   0.03355  -0.0119   0.0124   1.0000
  12.250   1.2527   0.04205   0.03586  -0.0108   0.0121   1.0000
  12.500   1.2511   0.04462   0.03852  -0.0096   0.0121   1.0000
  12.750   1.2502   0.04722   0.04122  -0.0086   0.0120   1.0000
  13.000   1.2507   0.04976   0.04384  -0.0078   0.0119   1.0000
  13.250   1.2519   0.05233   0.04654  -0.0074   0.0114   1.0000
  13.500   1.2528   0.05496   0.04925  -0.0070   0.0112   1.0000
  13.750   1.2537   0.05765   0.05203  -0.0067   0.0109   1.0000
  14.000   1.2544   0.06043   0.05488  -0.0066   0.0105   1.0000
  14.250   1.2565   0.06295   0.05749  -0.0057   0.0104   1.0000
  14.500   1.2591   0.06551   0.06015  -0.0053   0.0104   1.0000
  14.750   1.2613   0.06816   0.06289  -0.0047   0.0103   1.0000
  15.000   1.2634   0.07088   0.06574  -0.0040   0.0103   1.0000
  15.250   1.2638   0.07365   0.06845  -0.0046   0.0095   1.0000
  15.500   1.2632   0.07713   0.07224  -0.0039   0.0101   1.0000
  15.750   1.2576   0.08142   0.07679  -0.0035   0.0106   1.0000
  16.000   1.2545   0.08498   0.08041  -0.0046   0.0101   1.0000
  16.250   1.2400   0.09111   0.08689  -0.0044   0.0112   1.0000
  16.500   1.2249   0.09714   0.09312  -0.0060   0.0114   1.0000
  16.750   1.0187   0.10025   0.09648   0.0002   0.0109   1.0000
  17.000   0.9993   0.10379   0.10018  -0.0007   0.0110   1.0000
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