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WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 77-W-153 AIRFOIL (fx77w153-il)
Reynolds number: 50,000
Max Cl/Cd: 7.77 at α=-1°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx77w153-il-50000.txt
Download as CSV file: xf-fx77w153-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 77-W-153 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2774   0.11771   0.11286  -0.0163   0.8693   0.2203
  -9.250  -0.2689   0.11528   0.11018  -0.0141   0.8303   0.2290
  -9.000  -0.2755   0.11328   0.10810  -0.0149   0.8109   0.2355
  -8.750  -0.2646   0.11058   0.10527  -0.0138   0.7922   0.2458
  -8.500  -0.2571   0.10753   0.10216  -0.0140   0.7780   0.2539
  -8.250  -0.2738   0.10658   0.10124  -0.0167   0.7699   0.2647
  -8.000  -0.2504   0.10279   0.09736  -0.0151   0.7574   0.2776
  -7.750  -0.2352   0.09943   0.09399  -0.0152   0.7473   0.2892
  -7.500  -0.2291   0.09674   0.09126  -0.0152   0.7401   0.3021
  -7.250  -0.2195   0.09397   0.08853  -0.0160   0.7325   0.3177
  -7.000  -0.2110   0.09137   0.08593  -0.0160   0.7261   0.3346
  -6.750  -0.2065   0.08909   0.08368  -0.0163   0.7205   0.3549
  -6.250  -0.1816   0.08390   0.07852  -0.0149   0.7086   0.4015
  -6.000  -0.1647   0.08134   0.07597  -0.0138   0.7030   0.4317
  -5.750  -0.1564   0.07955   0.07423  -0.0122   0.6980   0.4697
  -5.250  -0.1091   0.07424   0.06887  -0.0084   0.6892   0.5469
  -5.000  -0.1876   0.05666   0.04973  -0.0556   0.6933   0.1706
  -4.750  -0.1701   0.05299   0.04553  -0.0558   0.6902   0.1551
  -4.500  -0.1497   0.05055   0.04293  -0.0566   0.6864   0.1512
  -4.250  -0.1308   0.04805   0.03987  -0.0568   0.6832   0.1449
  -4.000  -0.1095   0.04637   0.03753  -0.0564   0.6802   0.1413
  -3.750  -0.0878   0.04470   0.03560  -0.0561   0.6772   0.1436
  -3.500  -0.0646   0.04340   0.03412  -0.0554   0.6742   0.1482
  -3.250  -0.0425   0.04283   0.03323  -0.0559   0.6708   0.1536
  -3.000  -0.0199   0.04224   0.03234  -0.0561   0.6674   0.1582
  -2.750   0.0041   0.04172   0.03174  -0.0564   0.6643   0.1641
  -2.500   0.0297   0.04135   0.03112  -0.0564   0.6612   0.1736
  -2.250   0.0603   0.04076   0.03044  -0.0564   0.6581   0.1840
  -2.000   0.0866   0.04104   0.03074  -0.0578   0.6557   0.1962
  -1.750   0.2683   0.03645   0.02907  -0.0799   0.6470   1.0000
  -1.500   0.2828   0.03757   0.02986  -0.0794   0.6445   1.0000
  -1.250   0.2977   0.03871   0.03069  -0.0786   0.6423   1.0000
  -1.000   0.3113   0.04009   0.03182  -0.0779   0.6411   1.0000
  -0.750   0.3166   0.04215   0.03374  -0.0777   0.6415   1.0000
  -0.500   0.2906   0.04578   0.03741  -0.0766   0.6469   1.0000
  -0.250   0.2759   0.04835   0.03989  -0.0742   0.6512   1.0000
   0.000   0.2732   0.05044   0.04182  -0.0723   0.6546   1.0000
   0.250   0.2865   0.05227   0.04344  -0.0718   0.6575   1.0000
   0.500  -0.0639   0.05735   0.04733  -0.0406   0.9283   0.2344
   0.750   0.0002   0.05711   0.04961  -0.0469   0.9209   1.0000
   1.000   0.0235   0.05822   0.05029  -0.0473   0.8951   1.0000
   1.250   0.0554   0.06036   0.05203  -0.0493   0.8758   1.0000
   1.500   0.0866   0.06259   0.05393  -0.0511   0.8575   1.0000
   1.750   0.1139   0.06467   0.05573  -0.0523   0.8404   1.0000
   2.000   0.1378   0.06657   0.05739  -0.0529   0.8238   1.0000
   2.250   0.1610   0.06846   0.05908  -0.0533   0.8072   1.0000
   2.500   0.1831   0.07033   0.06075  -0.0536   0.7907   1.0000
   2.750   0.2032   0.07211   0.06236  -0.0535   0.7745   1.0000
   3.000   0.2195   0.07371   0.06381  -0.0530   0.7590   1.0000
   3.250   0.2331   0.07527   0.06523  -0.0522   0.7447   1.0000
   3.500   0.2479   0.07706   0.06689  -0.0517   0.7319   1.0000
   3.750   0.2874   0.08078   0.07045  -0.0544   0.7233   1.0000
   4.000   0.2957   0.08182   0.07139  -0.0529   0.7082   1.0000
   4.250   0.3043   0.08312   0.07261  -0.0515   0.6939   1.0000
   4.500   0.3140   0.08476   0.07415  -0.0505   0.6813   1.0000
   4.750   0.3529   0.08869   0.07796  -0.0530   0.6741   1.0000
   5.000   0.3536   0.08933   0.07854  -0.0509   0.6599   1.0000
   5.250   0.3588   0.09076   0.07990  -0.0495   0.6476   1.0000
   5.750   0.3930   0.09525   0.08426  -0.0494   0.6277   1.0000
   6.000   0.3982   0.09695   0.08591  -0.0484   0.6175   1.0000
   6.250   0.4285   0.10019   0.08909  -0.0495   0.6093   1.0000
   6.500   0.4250   0.10113   0.09000  -0.0477   0.5976   1.0000
   6.750   0.4601   0.10518   0.09399  -0.0494   0.5919   1.0000
   7.000   0.4490   0.10548   0.09427  -0.0472   0.5808   1.0000
   7.250   0.4810   0.10940   0.09815  -0.0486   0.5755   1.0000
   7.500   0.4700   0.10987   0.09862  -0.0467   0.5654   1.0000
   7.750   0.4981   0.11339   0.10212  -0.0477   0.5595   1.0000
   8.000   0.4913   0.11439   0.10310  -0.0463   0.5504   1.0000
   8.250   0.5162   0.11757   0.10628  -0.0469   0.5434   1.0000
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