Add to ORKGAn experimental research program was conducted in the NASA Lewis Research Center 10 x 10 ft supersonic wind tunnel. The 2-D inlet model was designed to study the Mach 3.0 to 5.0 speed range for an over-under turbojet plus ramjet propulsion system. The model was extensively instrumented to provide both analytical code validation data as well as inlet performance information. Support studies for the program include flow field predictions with both 3-D parabolized Navier-Stokes (PNS) and 3-D full Navier-Stokes (FNS) analytical codes. Analytical predictions and experimental results are compared
An experimental investigation was conducted to determine the off-design drag and pressure performanc...
Computational simulations and wind tunnel testing were conducted to explore the operation of the Abe...
A computational parametric study of three-dimensional, sidewall-compression scramjet inlets was perf...
A Mach 5 cruise aircraft was studied in a joint program effort. The propulsion system chosen for thi...
Hypersonic inlet research activity at NASA is reviewed. The basis is the experimental tests performe...
Wind-tunnel tests were conducted on a baseline scramjet inlet model having fixed geometry and swept...
The NASA Langley Research Center has conducted hypersonic propulsion research since the 1960s. A var...
The transonic performance of a dual-throat, single-expansion-ramp nozzle (SERN) was investigated wit...
An investigation of a fixed-geometry, swept external-internal compression inlet was conducted at a M...
A quick-look test was conducted in the 10- by 10-foot supersonic wind tunnel to provide some qualita...
A CFD methodology has been developed for inlet analyses of Rocket-Based Combined Cycle (RBCC) Engine...
Reynolds-Averaged Navier-Stokes (RANS) simulations were performed for the high-speed flowpath and is...
A wind tunnel investigation was conducted at free-stream Mach numbers from 0.55 to 2.0 on a 1/5.2-sc...
A method for computing three dimensional flow in supersonic inlets is described. An approximate set ...
Wind tunnel tests of airframe installation effects on F-106B scale model with simulated underwing en...
An experimental investigation was conducted to determine the off-design drag and pressure performanc...
Computational simulations and wind tunnel testing were conducted to explore the operation of the Abe...
A computational parametric study of three-dimensional, sidewall-compression scramjet inlets was perf...
A Mach 5 cruise aircraft was studied in a joint program effort. The propulsion system chosen for thi...
Hypersonic inlet research activity at NASA is reviewed. The basis is the experimental tests performe...
Wind-tunnel tests were conducted on a baseline scramjet inlet model having fixed geometry and swept...
The NASA Langley Research Center has conducted hypersonic propulsion research since the 1960s. A var...
The transonic performance of a dual-throat, single-expansion-ramp nozzle (SERN) was investigated wit...
An investigation of a fixed-geometry, swept external-internal compression inlet was conducted at a M...
A quick-look test was conducted in the 10- by 10-foot supersonic wind tunnel to provide some qualita...
A CFD methodology has been developed for inlet analyses of Rocket-Based Combined Cycle (RBCC) Engine...
Reynolds-Averaged Navier-Stokes (RANS) simulations were performed for the high-speed flowpath and is...
A wind tunnel investigation was conducted at free-stream Mach numbers from 0.55 to 2.0 on a 1/5.2-sc...
A method for computing three dimensional flow in supersonic inlets is described. An approximate set ...
Wind tunnel tests of airframe installation effects on F-106B scale model with simulated underwing en...
An experimental investigation was conducted to determine the off-design drag and pressure performanc...
Computational simulations and wind tunnel testing were conducted to explore the operation of the Abe...
A computational parametric study of three-dimensional, sidewall-compression scramjet inlets was perf...