Recent improvements in technology have allowed the design of rockets to launch satellites. Reusable shuttles were then used to limit launch costs. A new stage is needed for horizontal takeoff and landing aerospace planes. These single or two stage vehicles will need new propulsion systems, able to provide enough thrust in the whole flight corridor. Mixed propulsion systems seem to be well adapted to this need. During atmospheric flight air breathing engines are necessary to improve performances. Thus inlets will have to be installed. The success of this project will depend on the choice of the inlets, for which mass flow ratios is a paramount objective. Pressure recovery seems to be of less importance at high Mach numbers because of structural stresses. Current design methods are examined which are based on: (1) semiempirical predictions, using experimental data bases, shock boundary layer interaction laws, shock and side overflow losses; (2) 2-D and 3-D Euler codes taking into account the internal bleed effects; and (3) Navier-Stokes codes for specific problems. Some examples of inlet design are presented for rocket ramrocket engines. Problems of inlet integration are presented.
Supersonic-Hypersonic Inlet Studies for Aerospaceplane
1990
11 pages
Report
No indication
English
Jet & Gas Turbine Engines , Aircraft , Aerodynamics , Manned Spacecraft , Spacecraft Trajectories & Flight Mechanics , Aerospace planes , Air breathing engines , Flow distribution , Hypersonic inlets , Supersonic inlets , Propulsion system configurations , Propulsion system performance , Boundary layers , Euler equations of motion , Mach number , Mass flow , Navier-stokes equation , Pressure recovery , Shock layers , Foreign technology
International aerospaceplane efforts
NTRS | 1992
|Numerical studies of supersonic/hypersonic combustion
AIAA | 1992
|