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FX 77-W-270 (fx77w270-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 77-W-270 (fx77w270-il)
Reynolds number: 50,000
Max Cl/Cd: 1.41 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx77w270-il-50000.txt
Download as CSV file: xf-fx77w270-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 77-W-270                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6109   0.08627   0.07938  -0.0599   0.7272   0.1484
 -11.750  -0.6375   0.08115   0.07408  -0.0601   0.7251   0.1475
 -11.500  -0.6670   0.07711   0.06980  -0.0589   0.7233   0.1466
 -11.250  -0.6858   0.07322   0.06558  -0.0580   0.7211   0.1461
 -11.000  -0.6951   0.06972   0.06170  -0.0572   0.7186   0.1461
 -10.750  -0.6964   0.06657   0.05815  -0.0566   0.7159   0.1466
 -10.500  -0.6909   0.06376   0.05491  -0.0561   0.7132   0.1475
 -10.250  -0.6814   0.06125   0.05191  -0.0556   0.7107   0.1488
 -10.000  -0.6528   0.05940   0.05008  -0.0569   0.7077   0.1516
  -9.750  -0.6253   0.05778   0.04838  -0.0584   0.7049   0.1552
  -9.500  -0.6027   0.05613   0.04639  -0.0595   0.7024   0.1592
  -9.250  -0.5704   0.05503   0.04543  -0.0610   0.6997   0.1648
  -9.000  -0.5452   0.05400   0.04416  -0.0617   0.6970   0.1718
  -8.750  -0.5158   0.05335   0.04365  -0.0624   0.6938   0.1816
  -8.500  -0.4898   0.05273   0.04310  -0.0625   0.6909   0.1943
  -8.250  -0.4632   0.05223   0.04268  -0.0621   0.6884   0.2097
  -8.000  -0.4331   0.05203   0.04274  -0.0629   0.6866   0.2292
  -7.750  -0.4041   0.05188   0.04294  -0.0637   0.6856   0.2555
  -7.500  -0.3846   0.05158   0.04313  -0.0634   0.6852   0.2923
  -7.250  -0.3775   0.05104   0.04347  -0.0616   0.6852   0.3548
  -7.000  -0.3233   0.05841   0.05219  -0.0558   0.6834   0.4858
  -6.750  -0.2738   0.06575   0.05934  -0.0538   0.6814   0.5283
  -6.500  -0.2639   0.06909   0.06256  -0.0514   0.6817   0.5619
  -6.250  -0.2191   0.07487   0.06818  -0.0507   0.6817   0.5851
  -6.000  -0.1740   0.08009   0.07324  -0.0509   0.6815   0.6097
  -5.750  -0.2910   0.07910   0.07259  -0.0421   0.6984   0.6186
  -5.500  -0.2897   0.08235   0.07577  -0.0385   0.7061   0.6391
  -5.250  -0.7013   0.06458   0.05663  -0.0186   0.9822   0.2764
  -5.000  -0.6816   0.06413   0.05844  -0.0174   0.9774   0.4230
  -4.750  -0.6576   0.07268   0.06757  -0.0069   0.9599   0.5844
  -4.500  -0.6256   0.07758   0.07206  -0.0055   0.9425   0.6390
  -4.250  -0.6022   0.08177   0.07608  -0.0004   0.9253   0.6631
  -4.000  -0.5803   0.08504   0.07917   0.0040   0.9085   0.6866
  -3.750  -0.5584   0.08794   0.08189   0.0080   0.8940   0.7100
  -3.500  -0.5236   0.09168   0.08543   0.0101   0.8838   0.7396
  -3.250  -0.5090   0.09294   0.08655   0.0141   0.8684   0.7639
  -3.000  -0.4418   0.09839   0.09177   0.0110   0.8621   0.7991
  -2.750  -0.3970   0.10037   0.09358   0.0092   0.8456   0.8275
  -2.500  -0.2770   0.10641   0.09936  -0.0066   0.8314   0.8680
  -2.250  -0.2182   0.10881   0.10153  -0.0136   0.8222   0.8961
  -2.000  -0.1778   0.10994   0.10251  -0.0181   0.8065   0.9155
  -1.750  -0.0733   0.11411   0.10642  -0.0344   0.7988   0.9440
  -1.500  -0.0761   0.11329   0.10552  -0.0319   0.7830   0.9522
  -1.250  -0.0047   0.11637   0.10840  -0.0428   0.7770   0.9680
  -1.000  -0.0193   0.11530   0.10727  -0.0383   0.7617   0.9714
  -0.750   0.0505   0.11833   0.11011  -0.0490   0.7551   0.9828
  -0.500   0.0374   0.11749   0.10923  -0.0450   0.7404   0.9854
  -0.250   0.0832   0.11968   0.11127  -0.0511   0.7341   0.9922
   0.000   0.0682   0.11940   0.11094  -0.0469   0.7238   0.9924
   0.250   0.0904   0.12036   0.11179  -0.0487   0.7149   0.9952
   0.500   0.1357   0.12337   0.11466  -0.0543   0.7107   0.9999
   0.750   0.1093   0.12210   0.11338  -0.0485   0.6976   0.9999
   1.000   0.1261   0.12318   0.11435  -0.0486   0.6913   0.9999
   1.250   0.1542   0.12590   0.11693  -0.0504   0.6882   0.9999
   1.500   0.1207   0.12384   0.11489  -0.0438   0.6748   0.9999
   1.750   0.1366   0.12505   0.11600  -0.0437   0.6695   0.9999
   2.000   0.1618   0.12770   0.11853  -0.0450   0.6666   0.9999
   2.250   0.1280   0.12575   0.11659  -0.0387   0.6552   0.9999
   2.500   0.1395   0.12670   0.11745  -0.0380   0.6494   0.9999
   2.750   0.1605   0.12884   0.11949  -0.0385   0.6460   0.9999
   3.000   0.1382   0.12809   0.11874  -0.0340   0.6387   0.9999
   3.250   0.1401   0.12837   0.11896  -0.0321   0.6310   0.9999
   3.500   0.1554   0.12980   0.12030  -0.0317   0.6265   0.9999
   3.750   0.1798   0.13280   0.12321  -0.0325   0.6239   0.9999
   4.000   0.1440   0.13021   0.12064  -0.0266   0.6138   0.9999
   4.250   0.1524   0.13098   0.12135  -0.0254   0.6079   0.9999
   4.500   0.1691   0.13283   0.12312  -0.0251   0.6046   0.9999
   4.750   0.1926   0.13629   0.12650  -0.0257   0.6027   0.9999
   5.000   0.1494   0.13234   0.12259  -0.0192   0.5930   0.9999
   5.250   0.1559   0.13295   0.12315  -0.0178   0.5876   0.9999
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