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FX 61-163 AIRFOIL (fx61163-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 61-163 AIRFOIL (fx61163-il)
Reynolds number: 50,000
Max Cl/Cd: 6.11 at α=0.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx61163-il-50000.txt
Download as CSV file: xf-fx61163-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-163 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3509   0.12833   0.12171  -0.0263   1.0001   0.3019
 -10.500  -0.3204   0.12248   0.11583  -0.0260   1.0001   0.3094
 -10.250  -0.3231   0.11982   0.11326  -0.0262   1.0001   0.3195
  -9.750  -0.3150   0.11325   0.10683  -0.0264   1.0001   0.3347
  -9.500  -0.3097   0.10954   0.10318  -0.0269   1.0001   0.3366
  -9.250  -0.3946   0.09215   0.08611  -0.0469   1.0001   0.1768
  -9.000  -0.4561   0.08214   0.07635  -0.0547   1.0001   0.1565
  -8.750  -0.4855   0.07718   0.07152  -0.0552   1.0001   0.1450
  -8.500  -0.5364   0.07475   0.06928  -0.0530   1.0001   0.1427
  -8.250  -0.5802   0.07412   0.06878  -0.0483   1.0001   0.1419
  -8.000  -0.6273   0.07350   0.06813  -0.0443   1.0001   0.1406
  -7.750  -0.6334   0.07089   0.06550  -0.0420   1.0001   0.1334
  -7.500  -0.6683   0.06759   0.06164  -0.0414   1.0001   0.1235
  -7.250  -0.6652   0.06416   0.05822  -0.0401   1.0001   0.1196
  -7.000  -0.6725   0.06036   0.05350  -0.0406   1.0001   0.1096
  -6.750  -0.6624   0.05689   0.04994  -0.0401   1.0001   0.1075
  -6.500  -0.6508   0.05362   0.04637  -0.0400   1.0001   0.1050
  -6.250  -0.6354   0.05040   0.04269  -0.0403   1.0001   0.1019
  -6.000  -0.5932   0.04702   0.03819  -0.0444   0.9946   0.0964
  -5.750  -0.5555   0.04437   0.03510  -0.0467   0.9886   0.0952
  -5.500  -0.5170   0.04203   0.03237  -0.0487   0.9829   0.0953
  -5.250  -0.4835   0.03992   0.03015  -0.0494   0.9769   0.0976
  -5.000  -0.4497   0.03865   0.02893  -0.0498   0.9714   0.1048
  -4.750  -0.4225   0.03785   0.02805  -0.0483   0.9654   0.1117
  -4.500  -0.3901   0.03717   0.02739  -0.0477   0.9601   0.1240
  -4.250  -0.3705   0.03603   0.02652  -0.0469   0.9541   0.1434
  -4.000  -0.3406   0.03150   0.02484  -0.0508   0.9495   0.4069
  -3.750  -0.3621   0.03862   0.03237  -0.0293   0.9429   0.6646
  -3.500  -0.2288   0.04891   0.04175  -0.0122   0.9409   0.8629
  -3.250  -0.1616   0.04774   0.04006  -0.0207   0.9349   0.8832
  -3.000  -0.1223   0.04697   0.03897  -0.0250   0.9286   0.8980
  -2.750  -0.1016   0.04648   0.03828  -0.0262   0.9218   0.9088
  -2.500  -0.0634   0.04593   0.03745  -0.0305   0.9158   0.9197
  -2.250  -0.0361   0.04548   0.03682  -0.0329   0.9087   0.9288
  -2.000   0.0110   0.04496   0.03605  -0.0387   0.9028   0.9386
  -1.750   0.0162   0.04501   0.03600  -0.0372   0.8958   0.9453
  -1.500   0.0581   0.04469   0.03549  -0.0422   0.8895   0.9530
  -1.250   0.0704   0.04483   0.03554  -0.0420   0.8830   0.9591
  -1.000   0.1016   0.04479   0.03537  -0.0451   0.8761   0.9653
  -0.750   0.1287   0.04494   0.03539  -0.0474   0.8699   0.9713
  -0.500   0.1491   0.04518   0.03555  -0.0487   0.8627   0.9767
  -0.250   0.1902   0.04533   0.03558  -0.0534   0.8561   0.9825
   0.000   0.1985   0.04589   0.03610  -0.0528   0.8489   0.9871
   0.250   0.2505   0.04605   0.03616  -0.0591   0.8419   0.9924
   0.500   0.2478   0.04694   0.03705  -0.0569   0.8352   0.9965
   0.750   0.2894   0.04733   0.03736  -0.0613   0.8281   0.9999
   1.000   0.2672   0.04840   0.03845  -0.0557   0.8226   0.9999
   1.250   0.2641   0.04920   0.03924  -0.0529   0.8168   0.9999
   1.500   0.2760   0.04994   0.03994  -0.0523   0.8108   0.9999
   1.750   0.2543   0.05089   0.04091  -0.0469   0.8067   0.9999
   2.000   0.2511   0.05168   0.04169  -0.0442   0.8016   0.9999
   2.250   0.2618   0.05250   0.04249  -0.0434   0.7958   0.9999
   2.500   0.2417   0.05336   0.04336  -0.0386   0.7937   0.9999
   2.750   0.2273   0.05417   0.04419  -0.0347   0.7923   0.9999
   3.000   0.2158   0.05504   0.04506  -0.0313   0.7933   0.9999
   3.250   0.2116   0.05608   0.04610  -0.0291   0.7960   0.9999
   3.500   0.0305   0.05405   0.04435  -0.0060   0.9489   0.9999
   3.750   0.0610   0.05589   0.04616  -0.0097   0.9346   0.9999
   4.000   0.0907   0.05774   0.04799  -0.0133   0.9201   0.9999
   4.250   0.1200   0.05962   0.04986  -0.0167   0.9056   0.9999
   4.500   0.1499   0.06161   0.05185  -0.0202   0.8906   0.9999
   4.750   0.1791   0.06363   0.05387  -0.0235   0.8757   0.9999
   5.000   0.2075   0.06568   0.05594  -0.0266   0.8608   0.9999
   5.250   0.2353   0.06776   0.05805  -0.0296   0.8458   0.9999
   5.500   0.2617   0.06984   0.06016  -0.0324   0.8311   0.9999
   5.750   0.2874   0.07197   0.06233  -0.0350   0.8165   0.9999
   6.000   0.3117   0.07412   0.06455  -0.0375   0.8022   0.9999
   6.250   0.3361   0.07636   0.06684  -0.0399   0.7878   0.9999
   6.500   0.3599   0.07866   0.06921  -0.0423   0.7735   0.9999
   6.750   0.3833   0.08104   0.07165  -0.0446   0.7593   0.9999
   7.000   0.4068   0.08344   0.07414  -0.0469   0.7441   0.9999
   7.250   0.4293   0.08591   0.07670  -0.0490   0.7297   0.9999
   7.500   0.4513   0.08842   0.07929  -0.0511   0.7147   0.9999
   7.750   0.4728   0.09104   0.08200  -0.0532   0.7006   0.9999
   8.000   0.4939   0.09373   0.08482  -0.0552   0.6863   0.9999
   8.250   0.5161   0.09662   0.08782  -0.0573   0.6728   0.9999
   8.500   0.5375   0.09951   0.09081  -0.0593   0.6585   0.9999
   8.750   0.5580   0.10241   0.09383  -0.0612   0.6439   0.9999
   9.000   0.5776   0.10535   0.09690  -0.0630   0.6291   0.9999
   9.250   0.5969   0.10834   0.10001  -0.0647   0.6144   0.9999
   9.500   0.6161   0.11140   0.10320  -0.0664   0.5996   0.9999
   9.750   0.6359   0.11458   0.10651  -0.0681   0.5849   0.9999
  10.000   0.6543   0.11773   0.10981  -0.0697   0.5702   0.9999
  10.250   0.6700   0.12077   0.11297  -0.0710   0.5554   0.9999
  10.500   0.6584   0.12288   0.11516  -0.0711   0.5454   0.9999
  10.750   0.6685   0.12609   0.11847  -0.0724   0.5330   0.9999
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