NAVIER-STOKES EQUATIONSUBSONIC FLOWBOUNDARY LAYERSCOMPUTERIZED SIMULATIONA Bluebell nozzle design concept is proposed for jet noise reduction with minimal thrust loss or even thrust augmentation. A Bluebell nozzle has a sinusoidal lip line edge (chevrons) and a sinusoidal cross section shape with linear...
We normally calculate the mass flow on the basis of the simplifying assumptions described previously, which results in the usual equation for the ideal nozzle mass flow (11.2)m˙i=pcAtTcWcRuΓ. In this equation, At is the throat area, which is assumed to be choked, and (11.3)Γ=γ(2γ...
The section addresses the theory, practice, and case study for evaluating frequency response. 8.1.3.1 Theory The angular equation of motion for the null-balance method using the pendulum model shown in Fig. 8.9 is expressed as: Sign in to download full-size image Figure 8.9. A dynamical ...
The right side of the rocket thrust equation is the one used in the rocket thrust calculator, where it is important to point out that dm/dtdm/dt represents the variation of mass with time (which is the mass exhausted by the jet rocket per unit time). Let's see now what are all those...
Furthermore, one of the technical trends in LPRE development is to increase chamber pressure for the advantages of higher specific impulse, more compactness, and relatively higher nozzle expansion ratio [2]. Elevating the chamber pressure makes the cooling of thrust chamber more difficult because ...
A variable area, convergent-divergent (10) nozzle for directing the flow of exhaust gas from an aircraft turbine engine to achieve thrust vectoring about yaw, pitch and roll axes includes a convergent section (16) and a divergent section (18) each comprised of hingedly connected planar members...
Simulations of a two-dimensional convergent-divergent nozzle with shock-vector control method of fluidic injection for pitch vector control was performed with CFD, using Spalart-Allmaras one equation turbulence model. A static freestream condition (M = 0,05) at Mach numbers from M = 0,3 to 1...
4) axisymmetric vectoring exhaust nozzle(AVEN) 轴对称推力矢量喷管 1. Setting up the configuration bifurcation equation of the axisymmetric vectoring exhaust nozzle(AVEN) and utilizing the homotopy tracing approach,the configuration bifurcation behaviors of the AVEN driving parallel mechanism and the ...
For the gas flow field, the explicit "non oscillatory containing no free parameters and dissipative scheme" (NND scheme) of the finite difference method is utilized in the body fitted coordinate to solve the governing partial differential equation——the Euler equation. The two fields are coupling...
In consideration of the effect of solid rocket mo torthrust deviationand transverse shift,the stage separation process of two-s tage ground-to-air missile was modeled and simulated by using six-freedom-de gree ballistic equation,and the process of principal control signal sheltered by booster was...