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FX 60-177 AIRFOIL (fx60177-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 60-177 AIRFOIL (fx60177-il)
Reynolds number: 50,000
Max Cl/Cd: 25.03 at α=10°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx60177-il-50000-n5.txt
Download as CSV file: xf-fx60177-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-177 AIRFOIL                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.5233   0.10658   0.09941  -0.0630   1.0001   0.0416
 -12.500  -0.5595   0.09762   0.09039  -0.0666   1.0001   0.0401
 -12.250  -0.6410   0.08505   0.07734  -0.0708   1.0001   0.0366
 -12.000  -0.6644   0.08114   0.07332  -0.0699   1.0001   0.0365
 -11.750  -0.6879   0.07760   0.06965  -0.0684   1.0001   0.0365
 -11.500  -0.7111   0.07441   0.06630  -0.0662   1.0001   0.0366
 -11.250  -0.7337   0.07156   0.06328  -0.0634   1.0001   0.0366
 -11.000  -0.7507   0.06910   0.06076  -0.0605   1.0001   0.0370
 -10.750  -0.7635   0.06708   0.05869  -0.0575   1.0001   0.0376
 -10.500  -0.7780   0.06526   0.05680  -0.0540   1.0001   0.0382
 -10.250  -0.7930   0.06357   0.05502  -0.0502   1.0001   0.0388
 -10.000  -0.8040   0.06176   0.05309  -0.0469   1.0001   0.0398
  -9.750  -0.8119   0.05972   0.05087  -0.0439   1.0001   0.0410
  -9.500  -0.8170   0.05751   0.04840  -0.0410   1.0001   0.0425
  -9.250  -0.8187   0.05517   0.04568  -0.0382   1.0001   0.0442
  -9.000  -0.8141   0.05305   0.04338  -0.0360   1.0001   0.0463
  -8.750  -0.8067   0.05146   0.04175  -0.0341   1.0001   0.0489
  -8.500  -0.7960   0.04973   0.03982  -0.0321   1.0001   0.0519
  -8.250  -0.7802   0.04801   0.03772  -0.0300   1.0001   0.0550
  -8.000  -0.7648   0.04663   0.03647  -0.0284   1.0001   0.0589
  -7.750  -0.7479   0.04550   0.03519  -0.0264   1.0001   0.0636
  -7.500  -0.7270   0.04454   0.03411  -0.0244   1.0001   0.0683
  -7.250  -0.7025   0.04362   0.03319  -0.0240   0.9976   0.0759
  -7.000  -0.6790   0.04268   0.03222  -0.0237   0.9946   0.0841
  -6.750  -0.6591   0.04162   0.03112  -0.0234   0.9908   0.0952
  -6.500  -0.6417   0.04040   0.02995  -0.0232   0.9867   0.1101
  -6.250  -0.6246   0.03900   0.02872  -0.0234   0.9825   0.1334
  -6.000  -0.6123   0.03720   0.02730  -0.0233   0.9774   0.1730
  -5.750  -0.6000   0.03491   0.02584  -0.0240   0.9730   0.2658
  -5.500  -0.5867   0.03390   0.02593  -0.0223   0.9685   0.4132
  -5.250  -0.5661   0.03519   0.02761  -0.0183   0.9638   0.5042
  -5.000  -0.5385   0.03679   0.02912  -0.0163   0.9595   0.5621
  -4.750  -0.5168   0.03830   0.03046  -0.0137   0.9541   0.6031
  -4.500  -0.4932   0.03983   0.03178  -0.0114   0.9489   0.6328
  -4.250  -0.4631   0.04135   0.03305  -0.0101   0.9447   0.6522
  -4.000  -0.4430   0.04216   0.03368  -0.0078   0.9387   0.6693
  -3.750  -0.4168   0.04295   0.03425  -0.0068   0.9333   0.6854
  -3.250  -0.3687   0.04364   0.03455  -0.0053   0.9215   0.7122
  -3.000  -0.3405   0.04365   0.03434  -0.0062   0.9163   0.7247
  -2.750  -0.3181   0.04382   0.03437  -0.0050   0.9101   0.7317
  -2.500  -0.2938   0.04368   0.03405  -0.0053   0.9039   0.7421
  -2.250  -0.2647   0.04379   0.03399  -0.0057   0.8986   0.7502
  -2.000  -0.2458   0.04359   0.03367  -0.0050   0.8907   0.7591
  -1.750  -0.2127   0.04359   0.03350  -0.0063   0.8857   0.7665
  -1.500  -0.1974   0.04334   0.03316  -0.0051   0.8769   0.7746
  -1.250  -0.1657   0.04332   0.03301  -0.0061   0.8715   0.7814
  -1.000  -0.1497   0.04313   0.03273  -0.0051   0.8630   0.7898
  -0.750  -0.1196   0.04309   0.03258  -0.0057   0.8571   0.7961
  -0.500  -0.1016   0.04290   0.03231  -0.0053   0.8486   0.8041
  -0.250  -0.0714   0.04277   0.03210  -0.0059   0.8420   0.8091
   0.000  -0.0514   0.04260   0.03186  -0.0054   0.8327   0.8155
   0.250  -0.0198   0.04238   0.03156  -0.0067   0.8259   0.8213
   0.500  -0.0017   0.04227   0.03141  -0.0055   0.8160   0.8270
   0.750   0.0314   0.04205   0.03112  -0.0072   0.8099   0.8333
   1.000   0.0474   0.04197   0.03103  -0.0057   0.7993   0.8385
   1.250   0.0838   0.04166   0.03066  -0.0075   0.7935   0.8432
   1.500   0.1007   0.04155   0.03053  -0.0066   0.7815   0.8488
   1.750   0.1235   0.04135   0.03032  -0.0062   0.7714   0.8530
   2.000   0.1555   0.04099   0.02994  -0.0071   0.7638   0.8572
   2.250   0.1736   0.04095   0.02990  -0.0064   0.7521   0.8624
   2.750   0.2272   0.04043   0.02940  -0.0067   0.7336   0.8707
   3.000   0.2483   0.04031   0.02931  -0.0062   0.7217   0.8754
   3.250   0.2871   0.03969   0.02869  -0.0080   0.7152   0.8793
   3.500   0.3050   0.03960   0.02865  -0.0068   0.7019   0.8832
   3.750   0.3260   0.03949   0.02858  -0.0062   0.6896   0.8873
   4.000   0.3650   0.03865   0.02778  -0.0076   0.6834   0.8908
   4.250   0.3873   0.03854   0.02771  -0.0073   0.6697   0.8946
   4.500   0.4086   0.03828   0.02751  -0.0064   0.6564   0.8982
   4.750   0.4338   0.03790   0.02720  -0.0060   0.6442   0.9020
   5.000   0.4714   0.03698   0.02634  -0.0070   0.6364   0.9055
   5.250   0.4952   0.03690   0.02634  -0.0068   0.6226   0.9092
   5.500   0.5190   0.03663   0.02613  -0.0063   0.6094   0.9127
   5.750   0.5465   0.03618   0.02575  -0.0061   0.5962   0.9165
   6.000   0.5772   0.03562   0.02526  -0.0063   0.5827   0.9203
   6.250   0.6079   0.03510   0.02478  -0.0065   0.5684   0.9240
   6.500   0.6378   0.03454   0.02428  -0.0064   0.5536   0.9277
   6.750   0.6693   0.03405   0.02382  -0.0067   0.5387   0.9315
   7.000   0.6986   0.03383   0.02362  -0.0070   0.5226   0.9354
   7.250   0.7233   0.03381   0.02366  -0.0067   0.5052   0.9392
   7.500   0.7475   0.03384   0.02372  -0.0064   0.4874   0.9432
   7.750   0.7713   0.03398   0.02387  -0.0062   0.4693   0.9475
   8.000   0.7935   0.03422   0.02415  -0.0058   0.4508   0.9518
   8.250   0.8156   0.03451   0.02446  -0.0055   0.4330   0.9561
   8.500   0.8385   0.03487   0.02483  -0.0053   0.4163   0.9604
   8.750   0.8606   0.03533   0.02534  -0.0052   0.4002   0.9647
   9.000   0.8816   0.03589   0.02595  -0.0051   0.3846   0.9698
   9.250   0.9028   0.03651   0.02663  -0.0051   0.3698   0.9752
   9.500   0.9237   0.03715   0.02732  -0.0051   0.3553   0.9810
   9.750   0.9431   0.03782   0.02805  -0.0050   0.3410   0.9884
  10.000   0.9596   0.03834   0.02861  -0.0044   0.3278   0.9999
  10.250   0.9804   0.03927   0.02959  -0.0046   0.3148   0.9999
  10.500   0.9955   0.04054   0.03100  -0.0045   0.3021   0.9999
  10.750   1.0130   0.04177   0.03236  -0.0046   0.2904   0.9999
  11.000   1.0335   0.04285   0.03350  -0.0049   0.2793   0.9999
  11.250   1.0519   0.04406   0.03479  -0.0052   0.2683   0.9999
  11.500   1.0629   0.04577   0.03669  -0.0049   0.2578   0.9999
  11.750   1.0783   0.04714   0.03814  -0.0050   0.2475   0.9999
  12.000   1.0919   0.04857   0.03966  -0.0050   0.2373   0.9999
  12.250   1.0974   0.05071   0.04200  -0.0046   0.2278   0.9999
  12.500   1.1160   0.05195   0.04324  -0.0049   0.2189   0.9999
  12.750   1.1165   0.05464   0.04623  -0.0046   0.2107   0.9999
  13.000   1.1311   0.05623   0.04788  -0.0048   0.2028   0.9999
  13.250   1.1292   0.05920   0.05111  -0.0046   0.1952   0.9999
  13.500   1.1419   0.06091   0.05288  -0.0048   0.1879   0.9999
  13.750   1.1353   0.06453   0.05681  -0.0049   0.1813   0.9999
  14.000   1.1562   0.06549   0.05768  -0.0053   0.1742   0.9999
  14.250   1.1354   0.07075   0.06335  -0.0057   0.1690   0.9999
  14.500   1.1325   0.07420   0.06695  -0.0063   0.1628   0.9999
  14.750   1.1320   0.07748   0.07034  -0.0071   0.1570   0.9999
  15.000   1.1029   0.08470   0.07789  -0.0093   0.1527   0.9999
  15.250   1.1039   0.08803   0.08131  -0.0105   0.1472   0.9999
  15.500   1.0922   0.09345   0.08688  -0.0126   0.1430   0.9999
  15.750   1.0001   0.11319   0.10699  -0.0221   0.1408   0.9999
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