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FX 61-147 AIRFOIL (fx61147-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 61-147 AIRFOIL (fx61147-il)
Reynolds number: 50,000
Max Cl/Cd: 28.68 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx61147-il-50000-n5.txt
Download as CSV file: xf-fx61147-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-147 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3587   0.10265   0.09587  -0.0491   1.0000   0.0459
  -9.750  -0.3659   0.09781   0.09113  -0.0507   1.0000   0.0448
  -9.500  -0.3771   0.09210   0.08557  -0.0532   1.0000   0.0435
  -9.000  -0.4489   0.07951   0.07299  -0.0597   1.0000   0.0401
  -8.750  -0.4674   0.07690   0.07045  -0.0580   1.0000   0.0399
  -8.500  -0.4868   0.07429   0.06789  -0.0563   1.0000   0.0397
  -8.250  -0.5041   0.07148   0.06508  -0.0548   1.0000   0.0396
  -8.000  -0.5192   0.06864   0.06219  -0.0532   1.0000   0.0394
  -7.750  -0.5310   0.06579   0.05926  -0.0516   1.0000   0.0393
  -7.500  -0.5404   0.06279   0.05611  -0.0502   1.0000   0.0392
  -7.250  -0.5455   0.05984   0.05299  -0.0489   1.0000   0.0391
  -7.000  -0.5449   0.05654   0.04941  -0.0485   0.9993   0.0391
  -6.750  -0.5174   0.05166   0.04393  -0.0531   0.9909   0.0393
  -6.500  -0.4871   0.04749   0.03911  -0.0570   0.9820   0.0406
  -6.250  -0.4554   0.04433   0.03578  -0.0603   0.9743   0.0435
  -6.000  -0.4227   0.04148   0.03252  -0.0628   0.9652   0.0460
  -5.750  -0.3888   0.03877   0.02936  -0.0645   0.9564   0.0477
  -5.500  -0.3499   0.03666   0.02668  -0.0664   0.9490   0.0517
  -5.250  -0.3203   0.03479   0.02480  -0.0668   0.9390   0.0560
  -5.000  -0.2881   0.03343   0.02327  -0.0667   0.9299   0.0598
  -4.750  -0.2534   0.03227   0.02192  -0.0670   0.9217   0.0669
  -4.500  -0.2252   0.03113   0.02077  -0.0670   0.9105   0.0750
  -4.250  -0.1951   0.02990   0.01949  -0.0678   0.8998   0.0866
  -4.000  -0.1581   0.02829   0.01794  -0.0704   0.8917   0.1106
  -3.750  -0.1299   0.02541   0.01622  -0.0737   0.8801   0.2513
  -3.500  -0.1210   0.02574   0.01813  -0.0668   0.8677   0.5617
  -3.250  -0.0986   0.02746   0.01965  -0.0623   0.8559   0.6501
  -3.000  -0.0845   0.02935   0.02143  -0.0545   0.8457   0.7066
  -2.750  -0.0625   0.02976   0.02158  -0.0513   0.8347   0.7334
  -2.500  -0.0344   0.02950   0.02101  -0.0514   0.8231   0.7459
  -2.250  -0.0041   0.02922   0.02046  -0.0513   0.8131   0.7550
  -2.000   0.0313   0.02884   0.01978  -0.0526   0.8044   0.7644
  -1.750   0.0588   0.02856   0.01925  -0.0529   0.7927   0.7738
  -1.500   0.0877   0.02827   0.01875  -0.0529   0.7823   0.7811
  -1.250   0.1249   0.02788   0.01810  -0.0550   0.7740   0.7896
  -1.000   0.1491   0.02768   0.01774  -0.0542   0.7623   0.7961
  -0.750   0.1786   0.02747   0.01733  -0.0551   0.7516   0.8039
  -0.500   0.2134   0.02712   0.01679  -0.0560   0.7438   0.8095
  -0.250   0.2377   0.02703   0.01656  -0.0560   0.7321   0.8165
   0.000   0.2641   0.02689   0.01629  -0.0559   0.7217   0.8223
   0.250   0.2995   0.02664   0.01587  -0.0573   0.7140   0.8282
   0.500   0.3223   0.02665   0.01579  -0.0570   0.7028   0.8345
   0.750   0.3483   0.02659   0.01563  -0.0569   0.6933   0.8400
   1.000   0.3811   0.02649   0.01540  -0.0581   0.6852   0.8459
   1.250   0.4026   0.02656   0.01543  -0.0574   0.6750   0.8513
   1.500   0.4333   0.02650   0.01528  -0.0581   0.6671   0.8568
   1.750   0.4583   0.02661   0.01535  -0.0582   0.6577   0.8624
   2.000   0.4828   0.02668   0.01540  -0.0579   0.6491   0.8676
   2.250   0.5125   0.02671   0.01537  -0.0586   0.6411   0.8731
   2.500   0.5343   0.02694   0.01560  -0.0581   0.6320   0.8784
   2.750   0.5661   0.02691   0.01554  -0.0589   0.6250   0.8835
   3.000   0.5857   0.02727   0.01593  -0.0583   0.6155   0.8896
   3.250   0.6191   0.02722   0.01585  -0.0593   0.6093   0.8943
   3.500   0.6354   0.02766   0.01636  -0.0581   0.5997   0.9007
   3.750   0.6666   0.02776   0.01647  -0.0589   0.5931   0.9061
   4.000   0.6846   0.02819   0.01700  -0.0580   0.5843   0.9124
   4.250   0.7147   0.02837   0.01719  -0.0588   0.5777   0.9185
   4.500   0.7335   0.02885   0.01781  -0.0580   0.5691   0.9254
   4.750   0.7639   0.02907   0.01807  -0.0588   0.5627   0.9319
   5.000   0.7836   0.02963   0.01876  -0.0583   0.5540   0.9398
   5.250   0.8142   0.02992   0.01913  -0.0593   0.5474   0.9477
   5.500   0.8369   0.03054   0.01992  -0.0594   0.5388   0.9575
   5.750   0.8680   0.03097   0.02047  -0.0607   0.5315   0.9691
   6.000   0.8937   0.03158   0.02123  -0.0615   0.5232   1.0000
   6.250   0.9190   0.03228   0.02207  -0.0621   0.5158   1.0000
   6.500   0.9439   0.03302   0.02295  -0.0627   0.5081   1.0000
   6.750   0.9676   0.03387   0.02394  -0.0632   0.5006   1.0000
   7.000   0.9931   0.03463   0.02488  -0.0638   0.4929   1.0000
   7.250   1.0136   0.03568   0.02610  -0.0640   0.4852   1.0000
   7.500   1.0398   0.03644   0.02702  -0.0647   0.4777   1.0000
   7.750   1.0554   0.03775   0.02852  -0.0643   0.4696   1.0000
   8.000   1.0833   0.03843   0.02937  -0.0651   0.4624   1.0000
   8.250   1.0906   0.04012   0.03129  -0.0639   0.4535   1.0000
   8.500   1.1255   0.04039   0.03173  -0.0651   0.4467   1.0000
   8.750   1.1200   0.04264   0.03418  -0.0627   0.4368   1.0000
   9.000   1.1681   0.04197   0.03368  -0.0648   0.4299   1.0000
   9.250   1.1549   0.04464   0.03655  -0.0617   0.4193   1.0000
   9.500   1.1576   0.04656   0.03864  -0.0603   0.4097   1.0000
   9.750   1.2055   0.04532   0.03764  -0.0615   0.4013   1.0000
  10.000   1.1772   0.04938   0.04185  -0.0584   0.3903   1.0000
  10.250   1.1725   0.05200   0.04464  -0.0571   0.3798   1.0000
  10.500   1.2133   0.05048   0.04332  -0.0570   0.3697   1.0000
  10.750   1.2204   0.05178   0.04480  -0.0559   0.3581   1.0000
  11.000   1.1912   0.05700   0.05015  -0.0548   0.3464   1.0000
  11.250   1.1817   0.06054   0.05383  -0.0545   0.3341   1.0000
  11.500   1.1865   0.06240   0.05585  -0.0540   0.3213   1.0000
  11.750   1.1928   0.06400   0.05761  -0.0536   0.3077   1.0000
  12.000   1.1968   0.06596   0.05976  -0.0533   0.2935   1.0000
  12.250   1.1979   0.06838   0.06232  -0.0532   0.2788   1.0000
  12.500   1.1963   0.07123   0.06530  -0.0534   0.2628   1.0000
  12.750   1.1996   0.07327   0.06744  -0.0534   0.2450   1.0000
  13.000   1.2029   0.07531   0.06950  -0.0534   0.2254   1.0000
  13.250   1.1946   0.07956   0.07382  -0.0543   0.2073   1.0000
  13.500   1.1938   0.08256   0.07679  -0.0548   0.1873   1.0000
  13.750   1.1904   0.08616   0.08032  -0.0556   0.1689   1.0000
  14.000   1.1851   0.09026   0.08437  -0.0566   0.1519   1.0000
  14.250   1.1804   0.09437   0.08838  -0.0577   0.1370   1.0000
  14.500   1.1753   0.09869   0.09263  -0.0590   0.1239   1.0000
  14.750   1.1705   0.10310   0.09698  -0.0604   0.1123   1.0000
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