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FX 77-W-270S (fx77w270s-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 77-W-270S (fx77w270s-il)
Reynolds number: 50,000
Max Cl/Cd: 1.61 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx77w270s-il-50000.txt
Download as CSV file: xf-fx77w270s-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 77-W-270S                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3343   0.10424   0.09749  -0.0687   0.7237   0.1706
 -12.000  -0.2955   0.10560   0.09882  -0.0667   0.7175   0.1734
 -11.750  -0.6011   0.07466   0.06700  -0.0758   0.7357   0.1547
 -11.500  -0.6173   0.07148   0.06362  -0.0741   0.7322   0.1544
 -11.250  -0.6326   0.06880   0.06070  -0.0716   0.7288   0.1542
 -11.000  -0.6424   0.06620   0.05781  -0.0693   0.7254   0.1542
 -10.750  -0.6482   0.06383   0.05510  -0.0668   0.7221   0.1544
 -10.500  -0.6500   0.06171   0.05260  -0.0646   0.7190   0.1549
 -10.250  -0.6248   0.05943   0.05035  -0.0659   0.7146   0.1569
 -10.000  -0.5996   0.05784   0.04876  -0.0669   0.7108   0.1601
  -9.750  -0.5829   0.05642   0.04719  -0.0667   0.7077   0.1635
  -9.500  -0.5708   0.05510   0.04559  -0.0658   0.7052   0.1671
  -9.250  -0.5478   0.05369   0.04403  -0.0660   0.7024   0.1716
  -9.000  -0.5126   0.05255   0.04292  -0.0673   0.6993   0.1788
  -8.750  -0.4821   0.05149   0.04170  -0.0677   0.6964   0.1875
  -8.500  -0.4454   0.05095   0.04126  -0.0701   0.6933   0.2004
  -8.250  -0.3747   0.05028   0.04107  -0.0759   0.6889   0.2278
  -8.000  -0.3464   0.04999   0.04099  -0.0765   0.6868   0.2569
  -7.750  -0.3286   0.04982   0.04135  -0.0758   0.6856   0.2944
  -7.500  -0.3233   0.04983   0.04210  -0.0734   0.6851   0.3438
  -7.250  -0.2535   0.05681   0.05034  -0.0696   0.6820   0.4764
  -7.000  -0.1702   0.06662   0.05984  -0.0667   0.6776   0.5217
  -6.750  -0.1343   0.07105   0.06405  -0.0642   0.6753   0.5558
  -6.500  -0.0561   0.07687   0.06955  -0.0650   0.6722   0.5830
  -6.250  -0.0491   0.07892   0.07152  -0.0632   0.6727   0.6113
  -6.000   0.0172   0.08316   0.07560  -0.0665   0.6721   0.6378
  -5.750  -0.5741   0.06243   0.05609  -0.0308   0.7682   0.4099
  -3.500  -0.6519   0.08466   0.07868   0.0280   0.8885   0.7336
  -3.000  -0.3547   0.10556   0.09886  -0.0022   0.8612   0.8083
  -2.750  -0.3303   0.10698   0.10012  -0.0019   0.8472   0.8394
  -2.500  -0.1629   0.11438   0.10718  -0.0257   0.8369   0.8952
  -2.250  -0.1374   0.11452   0.10719  -0.0275   0.8205   0.9191
  -2.000   0.0570   0.11932   0.11169  -0.0625   0.8058   0.9999
  -1.750   0.0712   0.11934   0.11157  -0.0630   0.7944   0.9999
  -1.250   0.0814   0.11959   0.11160  -0.0608   0.7725   0.9999
  -1.000   0.1060   0.12114   0.11299  -0.0630   0.7679   0.9999
  -0.750   0.0867   0.12012   0.11194  -0.0578   0.7531   0.9999
  -0.500   0.1055   0.12105   0.11272  -0.0587   0.7466   0.9999
   0.000   0.1057   0.12147   0.11298  -0.0547   0.7267   0.9999
   0.250   0.1292   0.12309   0.11446  -0.0561   0.7218   0.9999
   0.500   0.1105   0.12257   0.11391  -0.0514   0.7105   0.9999
   0.750   0.1212   0.12315   0.11439  -0.0508   0.7025   0.9999
   1.000   0.1434   0.12495   0.11607  -0.0518   0.6984   0.9999
   1.250   0.1244   0.12457   0.11566  -0.0474   0.6895   0.9999
   1.500   0.1298   0.12492   0.11593  -0.0460   0.6806   0.9999
   1.750   0.1499   0.12652   0.11742  -0.0465   0.6758   0.9999
   2.000   0.1796   0.12991   0.12069  -0.0485   0.6733   0.9999
   2.250   0.1386   0.12689   0.11770  -0.0411   0.6594   0.9999
   2.500   0.1541   0.12813   0.11885  -0.0409   0.6540   0.9999
   2.750   0.1776   0.13068   0.12129  -0.0418   0.6510   0.9999
   3.000   0.1496   0.12944   0.12006  -0.0367   0.6428   0.9999
   3.250   0.1534   0.12986   0.12042  -0.0350   0.6349   0.9999
   3.500   0.1700   0.13138   0.12185  -0.0349   0.6302   0.9999
   3.750   0.1957   0.13447   0.12485  -0.0359   0.6274   0.9999
   4.000   0.1611   0.13229   0.12269  -0.0302   0.6180   0.9999
   4.250   0.1666   0.13291   0.12326  -0.0288   0.6113   0.9999
   4.500   0.1812   0.13443   0.12471  -0.0283   0.6071   0.9999
   4.750   0.2034   0.13730   0.12750  -0.0288   0.6045   0.9999
   5.000   0.1770   0.13596   0.12616  -0.0244   0.5983   0.9999
   5.250   0.1747   0.13591   0.12608  -0.0222   0.5901   0.9999
   5.500   0.1864   0.13712   0.12724  -0.0213   0.5851   0.9999
   5.750   0.2057   0.13956   0.12961  -0.0213   0.5820   0.9999
   6.000   0.2314   0.14382   0.13380  -0.0221   0.5803   0.9999
   6.250   0.1819   0.13894   0.12896  -0.0155   0.5713   0.9999
   6.500   0.1858   0.13947   0.12946  -0.0139   0.5653   0.9999
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