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...
Turbulent 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...

AUTOMOBILE

Subsonic turbulent flow past Generic Formula-1 car

In this study, subsonic turbulent flow computations are performed past a generic Formula-1 car..Read More...
Subsonic turbulent flow past Ahmed body

In this study, subsonic turbulent flow computations are performed past a Ahmed body. Simulation of flow around the bluff "Ahmed body ..Read More...

 

WORKSHOPS

SPICES-09: Symposium on Promotion of Indigenious CFD in Engineering Sciences

SPICES-09 was a national initiative to evaluate indigenious CFD tools for various features such as accuracy, efficiency, robustness and scalability...Read More...
4th AIAA Drag Prediction Workshop 

Drag prediction workshop is an initiative by Applied Aerospace Technical Committee to provide an impartial forum to evaluate RANS solvers and to identify areas in CFD needing research and development.Read More...
1st AIAA CFD High Lift Prediction Workshop 

High lift prediction workshop is an initiative by Applied Aerospace Technical Committee to provide an impartial forum to evaluate numerical prediction capability and advance the understanding of high lift flows....Read More...

 

2nd AIAA CFD High Lift Prediction Workshop 

2nd High Lift Prediction Workshop held at San-diego C.A. on June 2013, is to access the current generation CFD tool for predicting high lift flows for a representative landing configuration...Read More...

SPICES-13: Symposium on Promotion of Indigenious CFD in Engineering Sciences

SPICES-09 was a national initiative to evaluate indigenious CFD tools for various features such as accuracy, efficiency, robustness and scalability...Read More...

5th AIAA Drag Prediction Workshop

Drag prediction workshop is an initiative by Applied Aerospace Technical Committee to provide an impartial forum to evaluate RANS solvers and to identify areas in CFD needing research and development.Read More...

 

INTERNAL FLOW

AGARD S Duct

Demonstrate the capability of the flow solver HiFUN to carry out internal flow simulation. Read More...

 

Diffuser

Evaluate capabilities of flow solver HiFUN in predicting internal flow through diffuser configurations with varied divergent angles. Read More...

.