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S7055 (10.5%) Flat-Bottomed (s7055-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S7055 (10.5%) Flat-Bottomed (s7055-il)
Reynolds number: 50,000
Max Cl/Cd: 36.2 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s7055-il-50000-n5.txt
Download as CSV file: xf-s7055-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S7055 (10.5%) Flat-Bottomed                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3441   0.10646   0.09986  -0.0379   1.0000   0.1151
  -8.750  -0.3568   0.10448   0.09804  -0.0399   1.0000   0.1159
  -8.500  -0.3658   0.10210   0.09579  -0.0407   1.0000   0.1160
  -8.250  -0.3055   0.08513   0.07929  -0.0425   1.0000   0.0602
  -8.000  -0.3616   0.08940   0.08314  -0.0423   1.0000   0.0591
  -7.750  -0.3670   0.08700   0.08085  -0.0404   1.0000   0.0579
  -7.500  -0.3784   0.08470   0.07867  -0.0389   1.0000   0.0568
  -7.250  -0.3907   0.08226   0.07633  -0.0377   1.0000   0.0558
  -7.000  -0.4028   0.07972   0.07386  -0.0366   1.0000   0.0548
  -6.750  -0.4144   0.07681   0.07100  -0.0359   1.0000   0.0538
  -6.500  -0.4239   0.07364   0.06784  -0.0355   1.0000   0.0526
  -6.250  -0.4313   0.06996   0.06413  -0.0355   1.0000   0.0513
  -6.000  -0.4154   0.06262   0.05644  -0.0424   0.9919   0.0492
  -5.500  -0.3704   0.05194   0.04493  -0.0507   0.9750   0.0489
  -5.250  -0.3435   0.04903   0.04182  -0.0534   0.9681   0.0519
  -5.000  -0.3186   0.04543   0.03775  -0.0555   0.9598   0.0545
  -4.750  -0.2903   0.04163   0.03336  -0.0575   0.9528   0.0559
  -4.500  -0.2620   0.03830   0.02938  -0.0587   0.9453   0.0572
  -4.250  -0.2302   0.03547   0.02573  -0.0598   0.9387   0.0601
  -4.000  -0.2016   0.03372   0.02385  -0.0609   0.9313   0.0659
  -3.750  -0.1675   0.03179   0.02140  -0.0621   0.9253   0.0710
  -3.500  -0.1376   0.03035   0.01972  -0.0627   0.9176   0.0791
  -3.250  -0.0996   0.02895   0.01788  -0.0641   0.9124   0.0877
  -3.000  -0.0713   0.02800   0.01686  -0.0644   0.9040   0.0990
  -2.750  -0.0303   0.02689   0.01559  -0.0666   0.8993   0.1115
  -2.500  -0.0027   0.02618   0.01477  -0.0666   0.8902   0.1255
  -2.250   0.0355   0.02530   0.01391  -0.0685   0.8849   0.1569
  -2.000   0.0597   0.02447   0.01338  -0.0681   0.8751   0.2090
  -1.750   0.0841   0.02288   0.01307  -0.0679   0.8681   0.4686
  -1.500   0.1832   0.02148   0.01256  -0.0792   0.8694   1.0000
  -1.250   0.2083   0.02162   0.01235  -0.0789   0.8590   1.0000
  -1.000   0.2324   0.02180   0.01222  -0.0783   0.8487   1.0000
  -0.750   0.2633   0.02188   0.01203  -0.0788   0.8406   1.0000
  -0.500   0.2881   0.02206   0.01197  -0.0783   0.8305   1.0000
  -0.250   0.3112   0.02227   0.01196  -0.0775   0.8199   1.0000
   0.000   0.3396   0.02238   0.01188  -0.0775   0.8114   1.0000
   0.250   0.3654   0.02253   0.01187  -0.0770   0.8017   1.0000
   0.500   0.3875   0.02278   0.01196  -0.0760   0.7908   1.0000
   0.750   0.4132   0.02294   0.01199  -0.0755   0.7813   1.0000
   1.000   0.4416   0.02301   0.01194  -0.0753   0.7726   1.0000
   1.250   0.4632   0.02328   0.01212  -0.0742   0.7613   1.0000
   1.500   0.4870   0.02348   0.01224  -0.0733   0.7510   1.0000
   1.750   0.5179   0.02346   0.01213  -0.0734   0.7434   1.0000
   2.000   0.5390   0.02375   0.01237  -0.0722   0.7318   1.0000
   2.250   0.5616   0.02401   0.01260  -0.0712   0.7209   1.0000
   2.500   0.5873   0.02415   0.01270  -0.0705   0.7111   1.0000
   2.750   0.6153   0.02420   0.01272  -0.0701   0.7021   1.0000
   3.000   0.6370   0.02451   0.01302  -0.0690   0.6904   1.0000
   3.250   0.6602   0.02475   0.01330  -0.0681   0.6793   1.0000
   3.500   0.6860   0.02489   0.01344  -0.0674   0.6690   1.0000
   3.750   0.7140   0.02491   0.01347  -0.0669   0.6594   1.0000
   4.000   0.7359   0.02522   0.01381  -0.0658   0.6471   1.0000
   4.250   0.7587   0.02549   0.01417  -0.0648   0.6351   1.0000
   4.500   0.7823   0.02573   0.01446  -0.0638   0.6234   1.0000
   4.750   0.8073   0.02591   0.01469  -0.0630   0.6120   1.0000
   5.000   0.8338   0.02601   0.01484  -0.0623   0.6008   1.0000
   5.250   0.8584   0.02620   0.01514  -0.0614   0.5887   1.0000
   5.500   0.8806   0.02652   0.01555  -0.0603   0.5755   1.0000
   5.750   0.9031   0.02682   0.01594  -0.0592   0.5621   1.0000
   6.000   0.9256   0.02711   0.01632  -0.0581   0.5485   1.0000
   6.250   0.9481   0.02740   0.01676  -0.0570   0.5346   1.0000
   6.500   0.9704   0.02771   0.01718  -0.0558   0.5204   1.0000
   6.750   0.9924   0.02804   0.01762  -0.0546   0.5059   1.0000
   7.000   1.0143   0.02838   0.01807  -0.0534   0.4910   1.0000
   7.250   1.0360   0.02872   0.01852  -0.0521   0.4759   1.0000
   7.500   1.0556   0.02916   0.01913  -0.0506   0.4597   1.0000
   7.750   1.0729   0.02971   0.01982  -0.0490   0.4428   1.0000
   8.000   1.0903   0.03024   0.02048  -0.0473   0.4255   1.0000
   8.250   1.1080   0.03074   0.02109  -0.0456   0.4079   1.0000
   8.500   1.1260   0.03122   0.02164  -0.0439   0.3902   1.0000
   8.750   1.1373   0.03203   0.02261  -0.0416   0.3713   1.0000
   9.000   1.1496   0.03276   0.02349  -0.0394   0.3523   1.0000
   9.250   1.1615   0.03348   0.02426  -0.0371   0.3334   1.0000
   9.500   1.1673   0.03451   0.02541  -0.0344   0.3140   1.0000
   9.750   1.1723   0.03551   0.02648  -0.0315   0.2952   1.0000
  10.000   1.1763   0.03666   0.02765  -0.0288   0.2765   1.0000
  10.250   1.1776   0.03810   0.02918  -0.0262   0.2576   1.0000
  10.500   1.1783   0.03965   0.03076  -0.0238   0.2390   1.0000
  10.750   1.1779   0.04142   0.03253  -0.0217   0.2209   1.0000
  11.000   1.1754   0.04352   0.03471  -0.0198   0.2023   1.0000
  11.250   1.1721   0.04580   0.03705  -0.0182   0.1849   1.0000
  11.500   1.1679   0.04832   0.03955  -0.0168   0.1687   1.0000
  11.750   1.1628   0.05116   0.04239  -0.0158   0.1528   1.0000
  12.000   1.1575   0.05423   0.04552  -0.0151   0.1380   1.0000
  12.250   1.1514   0.05754   0.04884  -0.0147   0.1244   1.0000
  12.500   1.1449   0.06106   0.05236  -0.0145   0.1124   1.0000
  12.750   1.1379   0.06474   0.05600  -0.0145   0.1018   1.0000
  13.000   1.1307   0.06874   0.06011  -0.0148   0.0910   1.0000
  13.250   1.1252   0.07272   0.06419  -0.0152   0.0823   1.0000
  13.500   1.1187   0.07682   0.06826  -0.0157   0.0750   1.0000
  13.750   1.1117   0.08124   0.07282  -0.0167   0.0677   1.0000
  14.000   1.1062   0.08558   0.07722  -0.0176   0.0622   1.0000
  14.250   1.1006   0.09014   0.08194  -0.0187   0.0570   1.0000
  14.500   1.0945   0.09463   0.08638  -0.0201   0.0525   1.0000
  14.750   1.0879   0.09990   0.09197  -0.0217   0.0490   1.0000
  15.000   1.0817   0.10498   0.09721  -0.0236   0.0459   1.0000
  15.250   1.0784   0.10923   0.10142  -0.0251   0.0430   1.0000
  15.500   1.0707   0.11504   0.10742  -0.0275   0.0412   1.0000
  15.750   1.0587   0.12215   0.11483  -0.0309   0.0400   1.0000
  16.000   1.0466   0.12958   0.12249  -0.0347   0.0395   1.0000
  16.250   1.0321   0.13797   0.13109  -0.0393   0.0394   1.0000
  16.500   1.0138   0.14801   0.14128  -0.0450   0.0398   1.0000
  16.750   0.9961   0.15868   0.15201  -0.0510   0.0404   1.0000
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