(a) (b) 1 Fig. 1 Flat plate and nozzle model ) 1 (c) ; Cp (c) 1. 2 Ma = 5. 0 P 0 = 1. 1MPa T 0 = 373K; M j = 3. 0 P 0 j = 2. 08MPa T 0 j = 373K

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1 24 4 Vol. 24, No ACTA AERODYNAMICA SINICA Dec.,2006 : (2006) ,2, 3 1 ( ; ; ) : Roe Harten2Yee AUSM + Navier2Stokes, Baldwin2Lomax, B2L F y 5 3 : ; ; ; Ξ : V : A 0, F( y),,, y max [1 ],,, 3 4 F max ( y) y max, B2L [2 ] ( ) k2,,, F ( y) [3,4 ],B2L [7 ], B2L 1 (a),, F ( y) M j = 3, d = y max 6mm 1 (b), Visbal [5 ] ; Degni, x [6 ] ( ), y, ( 1 (a) Ξ : ; : : ( ) ( ) : (19672).

2 (a) (b) 1 Fig. 1 Flat plate and nozzle model ) 1 (c) ; Cp (c) 1. 2 Ma = 5. 0 P 0 = 1. 1MPa T 0 = 373K; M j = 3. 0 P 0 j = 2. 08MPa T 0 j = 373K M j = 3 P j ΠP s = 23. 7, Re = Πm 2. 1 B2L 24mm 18mm 1. 3 Aso [11 ] B2L k2 Aso [4 ] B2L Navier2Stokes [12214 ] EASM Reynold [8, Roe ] Harten2 Yee TVD [9 ] Meng2sing Liou AUSM + [10 ] ; B2L F( y) = Baldwin2Lomax(B2L) y (1 - exp ( - y + ΠA + ) ) F max y max y,, y , F ( y) [6 ] Crocco :, ; 2 Dhinagaran [3 ],A +, 2 xπd = - 10, - 5,5,10, Blasius 1Π7 F( y), ( xπd < 0), F( y) 2 3 ( xπ d > 0),, F T = T w + ( T aw - T w ) ū / u e rū 2 / Cp ( y) Degni [6 ] : T ; T w, ; T aw ; 2 xπd = - 5, F r ; ū ; u e ( y), F max

3 4 : 405 y max ( = 0 ) ( 3 (a) ) [2 ] B2L ( y > = 30mm) Visbal (a) 3 ( b) F max ( = ) 4 (a) P s PΠP s xπd ( d ) ( : ),,,, ;, 3 4 (b) ( : (a), 78 ; ) ( ), ( ),, ( F( y) 3 4 ), 45 ; 3 (b), 4 (c), y < ( : ; F max 71), y max 3 (a), xπd = - 15 xπd = - 5 xπd = 5 xπd = 15 2 F( y) Fig. 2 Distributions of F( y) at several positions in the symmetrical plane

4 406 24,, M j = 3, P j ΠP s = M j ,,, P j M j, P j M j, 5 Roe B2L 5 5 (a b c) ( = ) = 45 = 90 6 (a) ( PΠP s ) 6 (b), II, 6 (b),, 45 ;

5 4 : 407, 45, 7 ( ),,,

6 Roe AUSM + 8,,,AUSM +,, 9 Roe TVD,,,, (a) ( = ) (b) = 45 9 Roe TVD Fig. 9 Pressure contours by Roe &TVD scheme (c) = 90 (d) = ( Ma = 5. 0, P j / P s = 23. 7) Fig. 8 Simulating results by different schemes compared with experimental data ( Ma = 5. 0, P j / P s = 23. 7) 10 Roe AUSM + Fig. 10 Streamlines by Roe & AUSM + scheme 3 (1) Π N2S, B2L B2 L

7 4 : 409, B2L turbulence model for two2dimentional shock wave boundary, layer interactions [ R]. AIAA [6 ] DEGANI D, B. SCHIFF L. Computation of supersonic viscous flows around pointed bodies at large incidence[ R]. AIAA [7 ] NI Z Y, LI S X, SUN Y T. Visualization of pressure contour (2) and oil flow pattern on interactive flowfield [ A ]. 7th Asian, symposium on visualization [ C]. Singapore [8 ] ROE P L. Approximate Riemann solvers, parameter vectors, (3) (2) : [ 9 ] YEE H C, WARMING R F, HARTEN A. Implicit total vari2 ation diminishing schemes( TVD) for steady state calculations : [1 ] LI S X, NI Z Y. Free jet flow and interacted jet flow [A ], 7th Asian Symposium on Visualization [ C]. Singapore,2003. [2 ] BALDWIN B, LOMAX H. Thin layer approximation and al2 gebraic model for separated turbulent flows [ R ]. AIAA [3 ] DHINAGARAN R, BOSE T K. Two2dimensional jet interac2 tion flowfield predictions with an algebraic turbulence model [ R]. AIAA [4 ] ASO S, etc. A study on mixing phenomena in three2dimen2 sional supersonic flow with circular injection[ R ]. AIAA [5 ] VISBAL M, KNIGHT D. Evaluation of the Baldwin2Lomax and difference schemes [J ]. J. Comp. Phys., 1981, 43 [J ]. J. Comp. Phys. 1985, 57 (2) : [10 ] LIOU M S. Progress towards an improved CFD method : AUSM + [ R]. AIAA [11 ] ASO S, OKUYAMA S. Experimental study on mixing phe2 nomena in supersonic flows with slot injection[ R ]. AIAA [12 ] KAZUYUKI T, MAKOTO Y. Computation of supersonic tur2 bulent flowfield with secondary jet normal to freestream[ R ]. AIAA [13 ] CHENAULT C F, BERAN S. k2 and Reynolds stress turbu2 lence model comparisons for two2dimensional injection flow [J ]. AIAA Journal, 1998, 36 (8) : [14 ] KENZAKOWSKI D C, PAPP J L, DASH S M. Evaluation of advanced turbulence models and variable PrandtlΠSchmidt number methodology for propulsive flows [ R ]. AIAA Numerical simulation of lateral jet interaction turbulent flowfield WANGJun2qi 1,2, LI Su2xun 3, SUN Mao 1 (1. Aeronautics Academy of Science and Engineering, Beijing University of Aeronautics &Astronautics, Beijing , China ; 2. College of Energy and Power, Shandong University, Jinan , China ; 3. China Academy of Aerospace and Aerodynamics, Beijing , China) Abstract : A numerical method of the supersonic turbulent flow on the flat plate interacted by supersonic lateral jet is presented in this paper. Three numerical schemes Roe s FDS, Harten2Yee s TVD and Meng2Sing Liou s AUSM + in spatial discretization of Reynolds2averaged Navier2Stokes equations with Baldwin2Lomax turbulence model were used for nu2 merical simulation. Some modifications were proposed in the B2L turbulent model, so that the length of the separation region in the interaction flowfield was properly predicted. The free stream Mach number of 5. 0 and jet Mach number of 3. 0 are the comparison case between experimental and numerical results. It shows that this numerical method is reasonable. Key words : lateral jet ; supersonic flow ; turbulence model ; difference scheme