AEROSPACE

Turbulent flow past Space Shuttle Launch Vehicle (SSLV)

The configuration consists of a space shuttle in launch configuration, including the external tank, shuttle rocket boosters and some interconnection hardware. Computations are done for a free stream Mach number of 1.05..Read More...
Turbulent flow past Generic Spaceshuttle

Space shuttle is a very complex geometry. This test case demonstrates the the ability of HiFUN in handling complex geometries..Read More...
Turblent supersonic flow past ELAC-1

Computations are performed for supersonic turbulent flow past ELAC-1 (Elliptic Aerodynamic configuration). This is a aerospace vehicle consisting of a delta wing with a sweep angle of 75deg and stabilizer fins at the wing tips..Read More...
Supersonic turbulent flow past M910 spinning projectile

The projectile under consideration is M910 target practice, discarding sabot–traced (TPDS–T) projectile. Computations are performed for a wide range of Mach numbers..Read More...
Supersonic turbulent flow past HB-2 missile

The HB-2 is a hyper velocity ballistic model consisting of an axisymmetric, blunted cone–cylinder body with a flaring. Computations are performed for a range of supersonic Mach numbers..Read More...
Subsonic turbulent flow past NASA Trap Wing full span configuration

In this study, subsonic turbulent computations are performed for NASA Trap wing configuration consisting of a slat, a main wing and a flap..Read More...
Transonic turbulent flow past DLR-F6 Wing Body configuration

DLR-F6 Wing Body configuration representative of a modern, twin-engine, transport aircraft. It is a transonic wing-body design derived from DLR-F4 configuration..Read More...
Transonic turbulent flow past ONERA M6 wing

Computations are performed for steady, transonic and turbulent flow past Onera M6 wing. This test case is one of the first validation test cases considered using HiFUN..Read More...
Supersonic laminar flow past an ogive-cylinder configuration

Computations are performed for supersonic laminar flow past an ogive-cylinder configuration. This configuration is a basic slender aerodynamic body..Read More...
Supersonic inviscid flow past a monoplanar missile configuration

Monoplaner missile configuration considered in this study consists of an ogive nose, a cylinderical body, two wings and a conventional cruciform tail configuration..Read More...
Transonic inviscid flow past ONERA M6 wing

Computations are performed for steady, transonic and inviscid flow past Onera M6 wing. The 3D adaptation feature of HiFUN is validated using this test case..Read More...
Subsonic turbulent flow past OMAR five element configuration

Computations are performed for steady, subsonic and turbulent flow past OMAR five element configuration. The objective of this study is to compare the results obtained using unstructured grid with the one using structured grid..Read More...
Subsonic turbulent flow past MDA four element configuration

Computations are performed for subsonic turbulent flow past MDA four element configuation consisting of a slat, a main element, a main flap and an auxiliary flap..Read More...
Subsonic turbulent flow past three element NHLP2D configuration

Computations are performed for subsonic turbulent flow past NHLP2D configuration consisting of a slat, a main element and a flap. A structured multi-block grid is used for computations..Read More...
Subsonic turbulent flow past two element NLR-7301 configuration

Computations are performed for subsonic turbulent flow past NLR-7301 configuration consisting of a main element and a flap with a gap of 2.6% of the main element chord..Read More...
Transonic turbulent flow past RAE-2822 airfoil

Computations are performed for transonic turbulent flow past RAE-2822 airfoil. This test case is one of the first validation cases performed using HiFUN... Read More...
Hypersonic Inviscid flow past a Double Ellipse configuration

Computations are performed for hypersonic inviscid flow past a double ellipse configuration. In this test case the adaptation feature of code HiFUN is tested and validated.Read More...
Transonic Inviscid flow past NACA-0012 airfoil

Computations are performed for transonic inviscid flow past NACA-0012 airfoil. NACA-0012 is a symmertric airfoil with a maximum thickness equal to 12% of the chord length.. Read More...
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