Ch4 Oblique Shock and Expansion Waves 4.1 Introduction Supersonic flow over a corner. 4.2 Oblique Shock Relations sin 1 1 M …Mach angle (stronger disturbances) A Mach wave is a limiting case for oblique shocks. i.e. infinitely weak oblique shock Oblique shock wave geometry Given : V1 , 1 , Find : V2 , 2 ..., or Given : V1 , 1 , Find : V2 , 2 ..., Galilean Invariance : 1 2 The tangential component of the flow velocity is preserved. Superposition of uniform velocity does not change static variables. Continuity eq : 1u1 A1 2u2 A2 0 A1 A2 1u1 2u2 ( u ) Momentum eq : ( u ds )u d f d pd s t s s • parallel to the shock 1u1 1 2u2 2 0 1 2 The tangential component of the flow velocity is preserved across an oblique shock wave • Normal to the shock ( 1u1)u1 2u2 u2 P1 P2 P1 1u12 P2 2u22 Energy eq : Q Wshaft Wviscous Pu ds ( f u )d s u2 u2 [ (e )]d (e )u ds 2 2 t s 2 2 u1 u2 ( P1u1 P2u2 ) 1 (e1 )u1 2 (e2 )u2 2 2 2 2 u u 2 2 h 1 h 2 u u 1 1 1 1 2 2 2 u12 u22 h1 h2 2 2 The changes across an oblique shock wave are governed by the normal component of the free-stream velocity. Same algebra as applied to the normal shock equction Mn1 M1 sin For a calorically perfect gas 2 1Mn12 1 1Mn12 2 P2 2 1 Mn12 1 P1 1 Mn12 2 1 Mn22 2 Mn 2 1 1 1 M2 and T2 P2 1 T1 P1 2 Mn2 sin Special case 2 normal shock Note:changes across a normal shock wave the functions of M1 only changes across an oblique shock wave the functions of M1 & tan and u1 1 tan u2 2 tan u1 2 1Mn12 1M12 sin 2 2 tan u2 1 1Mn1 2 1M12 sin 2 2 M12 sin 2 1 tan 2 cot 2 M cos 2 2 1 M relation For =1.4 (transparancy or Handout) Note : 1. For any given M1 ,there is a maximum deflection angle If max max no solution exists for a straight oblique shock wave shock is curved & detached, 2. If max , there are two values of β for a given M1 strong shock solution (large ) M2 is subsonic weak shock solution (small ) M2 is supersonic except for a small region near max 3. 0 4. For a fixed 2 or M1 (weak shock solution) M1 →Finally, there is a M1 below which no solutions are possible →shock detached 5. For a fixed M1 Ex 4.1 , P2 , T2 and 2 , M 2 max Shock detached 4.3 Supersonic Flow over Wedges and Cones •Straight oblique shocks •3-D flow, Ps P2. •Streamlines are curved. •3-D relieving effect. •Weaker shock wave than a wedge of the same , •P2, The flow streamlines behind the shock are straight and parallel to the wedge surface. The pressure on the surface of the wedge is constant = P2 Ex 4.4 Ex 4.5 Ex4.6 2 , T2 are lower Integration (Taylor & Maccoll’s solution, ch 10) 4.4 Shock Polar –graphical explanations c.f Point A in the hodograph plane represents the entire flowfield of region 1 in the physical plane. Shock polar B Increases to V2 C (stronger shock) Locus of all possible velocities behind the oblique shock max Nondimensionalize Vx and Vy by a* (Sec 3.4, a*1=a*2 adiabatic ) * * Shock polar of all possible M 2 for a given M 1 M2 M * 1 1 1 * 2 M 1 M* 2.45, 1 for 1 .4 M * 1 2 if M M1* 1 M 1 M1* 1 M 1 M * 1 M 1 Important properties of the shock polar 1. For a given deflection angle , there are 2 intersection points D&B (strong shock solution) (weak shock solution) 2. OC tangent to the shock polarthe maximum lefleation angle max for a given M1* For 0 max no oblique shock solution 3. Point E & A represent flow with no deflection Mach line normal shock solution 4. OH AB HOA Shock wave angle 5. The shock polars for different mach numbers. M * Vx Vx M * 1 1 a * a * 1 2 2 V M 1* x* M 1* 1 1 a 2 Vy * a 2 ref:1. Ferri, Antonio, “Elements of Aerodynamics of Supersonic Flows” , 1949. 2. Shapiro, A.H., ”The Dynamics and Thermodynamics of Compressible Fluid Flow”, 1953. 4.5 Regular Reflection from a Solid Boundary M 2 M1 2 1 (i.e. the reflected shock wave is not specularly reflected) Ex 4.7 4.6 Pressure – Deflection Diagrams Wave interaction -locus of all possible static pressure behind an oblique shock wave as a function deflection angle for given upstream conditions. Shock wave – a solid boundary Shock – shock Shock – expansion Shock – free boundaries Expansion – expansion (+) (-) (downward consider negative) •Left-running Wave : When standing at a point on the waves and looking “downstream”, you see the wave running-off towards your left. P diagram for sec 4.5 4.7 Intersection of Shocks of Opposite Families •C&D:refracted shocks (maybe expansion waves) •Assume 2 1 shock A is stronger than shock B a streamline going through the shock system A&C experience or a different entropy change than a streamline going through the shock system B&D 1. 2. P4 P4' V4 V4' and have (the same direction. In general they differ in magnitude. ) s4 s4' •Dividing streamline EF (slip line) •If 2 3 coupletely sysmuetric no slip line Assume 4' and 4 are known ' P4 & P4 are known if P4 P4' solution if P4 P4' Assume another 4.8 Intersection of Shocks of the same family Will Mach wave emanate from A & C intersect the shock ? supersonic Point A sin u1 V1 u1 a1 a1 V1 intersection sin 1 1 Point C sin 2 a2 V2 sin Subsonic u2 V2 u 2 a2 2 intersection (or expansion wave) A left running shock intersects another left running shock 4.9 Mach Reflection ( max for M 1 ) ( max for A straight oblique shock M2 ) A regular reflection is not possible Much reflection max for M2 Flow parallel to the upper wall & subsonic 4.10 Detached Shock Wave in Front of a Blunt Body From a to e , the curved shock goes through all possible oblique shock conditions for M1. CFD is needed 4.11 Three – Dimensional Shock Wave Mn1 M1i n P2 , 2 , T2 , h2 , Mn2 Immediately behind the shock at point A Inside the shock layer , non – uniform variation. 4.12 Prandtl – Meyer Expansion Waves Expansion waves are the antithesis of shock waves Centered expansion fan Some qualitative aspects : 1. M2>M1 2. P2 P1 1, 2 1 1, T2 T1 1 3. The expansion fan is a continuous expansion region. Composed of an infinite number of Mach waves. Forward Mach line : 1 sin 1 1 M1 1 Rearward Mach line : 2 sin M 2 4. Streamlines through an expansion wave are smooth curved lines. 1 5. ds 0 i.e. The expansion is isentropic. ( Mach wave) Consider the infinitesimal changes across a very weak wave. (essentially a Mach wave) An infinitesimally small flow deflection. d V cos V dV cos d …tangential component is preserved. V dV cos V cos d 1 d dV dV 1 V 1 d tan sin 1 V tan d M 2 1 tan dV V as 1 M 1 M 2 1 d 0 …governing differential equation for prandtl-Meyer flow general relation holds for perfect, chemically reacting gases real gases. 2 d 1 M M 2 M 2 1 V Ma 1 dV V dV ? V dV Mda adM dV da dM V a M da ? a Specializing to a calorically perfect gas 1 2 a T 0 0 1 M T 2 a 2 1 2 a a0 1 M 2 1 2 dV 1 dM 1 2 M V 1 M 2 2 M 1 dM 2 M2 d 0 2 1 M1 1 2 M 1 M 2 let vM M 2 1 dM M 1 2 M 1 M 2 1 1 1 2 tan M 1 tan 1 M 2 1 1 1 2 M 2 M1 Have the same reference point --- for calorically perfect gas table A.5 for 1.4 M • procedures of calculating a Prandtl-Meyer expansion wave 1. M1 from Table A.5 for the given M1 2. M 2 2 M1 3. M2 from Table A.5 4. the expansion is isentropic 1 1 M 22 T1 2 T2 1 1 M 2 1 2 1 2 1 M2 P1 2 P2 1 1 M 2 1 2 1 T0 , P0 are constant through the wave