Numerical studies of reverse flows controlled by undulating leading edge
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摘要
The improved delayed detached-eddy simulation(IDDES) method is used to simulate the reverse flows past an NACA0012 airfoil at medium(10°) and large(30°) angles of attack. The numerical results of the baseline configuration are compared with the available measurements. The effects of the undulating leading edge with four different amplitudes are compared and analyzed at angle of attack of 10°. Based on these analyses, the amplitude of A/C=0.04 yields the best performance. Compared with the uncontrolled case, the performances of the undulating leading edge are greatly improved with reducing of the aerodynamic fluctuations. Furthermore, the mechanisms of performance are explored by comparing the local flow structures near the undulations.
The improved delayed detached-eddy simulation(IDDES) method is used to simulate the reverse flows past an NACA0012 airfoil at medium(10°) and large(30°) angles of attack. The numerical results of the baseline configuration are compared with the available measurements. The effects of the undulating leading edge with four different amplitudes are compared and analyzed at angle of attack of 10°. Based on these analyses, the amplitude of A/C=0.04 yields the best performance. Compared with the uncontrolled case, the performances of the undulating leading edge are greatly improved with reducing of the aerodynamic fluctuations. Furthermore, the mechanisms of performance are explored by comparing the local flow structures near the undulations.
The improved delayed detached-eddy simulation(IDDES) method is used to simulate the reverse flows past an NACA0012 airfoil at medium(10°) and large(30°) angles of attack. The numerical results of the baseline configuration are compared with the available measurements. The effects of the undulating leading edge with four different amplitudes are compared and analyzed at angle of attack of 10°. Based on these analyses, the amplitude of A/C=0.04 yields the best performance. Compared with the uncontrolled case, the performances of the undulating leading edge are greatly improved with reducing of the aerodynamic fluctuations. Furthermore, the mechanisms of performance are explored by comparing the local flow structures near the undulations.
引文
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23 Y.F.Zhang,H.X.Chen,and S.Fu,Sci.China-Phys.Mech.Astron.55,828(2012).
24 Q.Li,D.Sun,and H.X.Zhang,Sci.China-Phys.Mech.Astron.56,1062(2013).
25 J.B.Huang,Z.X.Xiao,J.Liu,and S.Fu,Sci.China-Phys.Mech.Astron.55,260(2012).
26 Z.Xiao,J.Liu,J.Huang,and S.Fu,AIAA J.50,1119(2012).
27 Z.X.Xiao,J.Liu,J.B.Huang,and S.Fu,“Comparisons of three improved DES methods on unsteady flows past tandem cylinders”,AIAA Paper No.2012-0231,2012.
28 Z.X.Xiao,and K.Y.Luo,Acta Mech.Sin.31,799(2015).
29 Z.Xiao,J.Liu,K.Luo,J.Huang,and S.Fu,AIAA J.51,107(2013).
30 F.R.Menter,AIAA J.32,1598(1994).
31 A.Pope,The forces and pressures over an NACA0015 airfoil through180 degrees angle of attack,Georgia Technical Report(Daniel Guggenheim School of Aeronautics,1947).
32 H.Johari,C.W.Henoch,D.Custodio,and A.Levshin,AIAA J.45,2634(2007).
33 K.L.Hansen,R.M.Kelso,and B.B.Dally,AIAA J.49,185(2011).
34 P.Chaitanya,P.Joseph,S.Narayanan,C.Vanderwel,J.Turner,J.W.Kim,and B.Ganapathisubramani,J.Fluid Mech.818,435(2017).
2 A.H.Lind,L.R.Smith,J.I.Milluzzo,and A.R.Jones,J.Aircraft 53,1248(2016).
3 A.H.Lind,and A.R.Jones,AIAA J.53,2621(2015).
4 A.H.Lind,J.N.Lefebvre,and A.R.Jones,AIAA J.52,2751(2014).
5 J.Hodara,A.H.Lind,A.R.Jones,and M.J.Smith,J Am Helicopter Soc.61,1(2016).
6 M.J.Smith,N.D.Liggett,and B.C.G.Koukol,J.Aircraft 48,2012(2011).
7 C.J.Clifford,A.Singhal,and M.Samimy,“A Study of physics and control of a flow over an airfoil in fully-reversed condition”,AIAApaper No.2014-1265,2014.
8 F.E.Fish,and J.M.Battle,J.Morphol.225,51(1995).
9 M.Zhao,M.Zhang,and J.Xu,Eng.Appl.Comput.Fluid Mech.11,193(2017).
10 A.Skillen,A.Revell,A.Pinelli,U.Piomelli,and J.Favier,AIAA J.53,464(2014).
11 R.Pérez-Torró,and J.W.Kim,J.Fluid Mech.813,23(2017).
12 D.Custodio,C.W.Henoch,and H.Johari,AIAA J.53,1878(2015).
13 N.Rostamzadeh,R.M.Kelso,and B.Dally,Theor.Comput.Fluid Dyn.31,1(2016).
14 F.Tong,W.Qiao,K.Xu,L.Wang,W.Chen,and X.Wang,J.Sound Vib.419,200(2018).
15 M.D.Bolzon,R.M.Kelso,and M.Arjomandi,J.Aerosp.Eng.29,04015013(2015).
16 N.Rostamzadeh,K.L.Hansen,R.M.Kelso,and B.B.Dally,Phys.Fluids 26,107101(2014).
17 K.L.Hansen,N.Rostamzadeh,R.M.Kelso,and B.B.Dally,J.Fluid Mech.788,730(2016).
18 M.L.Shur,P.R.Spalart,M.K.Strelets,and A.K.Travin,Int.J.Heat Fluid Flow 29,1638(2008).
19 Y.Q.Wang,and C.Q.Liu,Sci.China-Phys.Mech.Astron.60,114712(2017).
20 H.Zh,and S.Fu,Sci.China-Phys.Mech.Astron.60,104712(2017).
21 Z.Jiao,and S.Fu,Sci.China-Phys.Mech.Astron.61,114711(2018).
22 S.Y.Chen,Y.C.Chen,Z.H.Xia,K.Qu,Y.P.Shi,Z.L.Xiao,Q.H.Liu,Q.D.Cai,F.Liu,C.Lee,R.K.Zhang,and J.S.Cai,Sci.ChinaPhys.Mech.Astron.56,270(2013).
23 Y.F.Zhang,H.X.Chen,and S.Fu,Sci.China-Phys.Mech.Astron.55,828(2012).
24 Q.Li,D.Sun,and H.X.Zhang,Sci.China-Phys.Mech.Astron.56,1062(2013).
25 J.B.Huang,Z.X.Xiao,J.Liu,and S.Fu,Sci.China-Phys.Mech.Astron.55,260(2012).
26 Z.Xiao,J.Liu,J.Huang,and S.Fu,AIAA J.50,1119(2012).
27 Z.X.Xiao,J.Liu,J.B.Huang,and S.Fu,“Comparisons of three improved DES methods on unsteady flows past tandem cylinders”,AIAA Paper No.2012-0231,2012.
28 Z.X.Xiao,and K.Y.Luo,Acta Mech.Sin.31,799(2015).
29 Z.Xiao,J.Liu,K.Luo,J.Huang,and S.Fu,AIAA J.51,107(2013).
30 F.R.Menter,AIAA J.32,1598(1994).
31 A.Pope,The forces and pressures over an NACA0015 airfoil through180 degrees angle of attack,Georgia Technical Report(Daniel Guggenheim School of Aeronautics,1947).
32 H.Johari,C.W.Henoch,D.Custodio,and A.Levshin,AIAA J.45,2634(2007).
33 K.L.Hansen,R.M.Kelso,and B.B.Dally,AIAA J.49,185(2011).
34 P.Chaitanya,P.Joseph,S.Narayanan,C.Vanderwel,J.Turner,J.W.Kim,and B.Ganapathisubramani,J.Fluid Mech.818,435(2017).