Providing Quality CFD
Software and Solutions
Pulse Detonation Engine
A time accurate simulation of a PDE (pulse detonation engine) using a hydrogen-air model and finite-rate chemistry. Click for movie
Spinning Missile
A time accurate simulation of a spinning missile with dithering canards. Motion was prescribed, Mach 1.5, spinning at around 3000 deg/sec, at 3 deg aoa. Courtesy of Dynetics
Jet Interaction
Multiple jet interaction computation. Two sonic jets with normal injection into a supersonic flow. The flow domain was 3-D and the Wilcox k-omega turbulence model was used. Mach contours displayed.
Interceptor Missile
Velocity vectors colored by temperature depicting the separation and recirculation region upstream of a control jet thruster on a finned interceptor missile. This 3-D, turbulent, chemically-reacting CFD calculation was performed with GASP on a Cray T90. Courtesy of SY Technology
Dual-Nozzle Rocket
GASP has been used to obtain a solution for a dual-nozzle missile at Mach 5.72 and an altitude of 47.8 Km.
Space Shuttle
Mach 1.3 flow about space shuttle orbiter using GASP v4 with chimera grids. Grids system courtesy of R. Gomez,
NASA Johnson Space Center
Hypersonic Design
As part of the Hypercomputing & Design (HPCd) project at Rutgers University, GASP was used as a tool for CFD simulations.
Shock Boundary Layer Interaction
Hypersonic shock wave boundary layer interaction around a double cone geometry. See Reference.
DES Simulation
Iso-surface of velocity for an Apollo capsule detached eddy simulation. Click for movie
SSTO Vehicle
Mach contours for a generic Single-Stage-To-Orbit (SSTO) vehicle.
F-16
Pressure contours on an F-16 using an unstructured mesh.
AeroSpike
Pressure contours and particle traces for Mach 6.0 flow over a missile with an aerospike.
Missile Design
Supersonic flow over a missile body with a wrap-around fin. This work was accomplished at the Aeromechanics Division of the Air Force Research Laboratories
Pontiac Fiero
This figure shows the mach contours of a 60 mph flow over a Pontiac Fiero. Geometry obtained from SGI demos.
Supersonic Forebody
Inviscid flow of a perfect gas about an analytically defined surface representing a generic high-performance aircraft forebody.
HSCT
Wing and fuselage of High Speed Civil Transport (HSCT) at Mach 2.4.
Payload Fairing
Flow through multi-port payload fairing vents on the Tital IV vehicle. The above figure represents pressure contours. Grid compliments of Lockheed Martin, Denver.
