1.Overview

2.CFD simulation approach

3.What is included in the package

4.Package Costing

5.Add Ons

F-16 fighter aircraft is an American single-engine supersonic multirole fighter aircraft. The flow around fighter aircraft is dominated by vertical wakes as generated at sharp leading edges of strakes and wings. The interaction of vertical wakes with the structure of the aircraft is of major interest with regard to aerodynamic effects related to the fighter aircraft operation.

Aerodynamics simulations are performed in CFD to assess the Drag and Lift forces which are among the key parameters of design of the body streamline. Drag forces are directly proportional to the speed of the aircraft.

The F-16 Fighter aircraft has a maximum cruising altitude of 55,000 ft. It can fly at twice the speed of sound, or around 1,500 miles per hour.

In this simulation package, the fighter jet is simulated for an altitude of 40,000 ft cruising at a Mach number of 2. The drag forces along with the streamlines are studied around the aircraft. team of skilled engineers has experience in mechanical, electrical, and environmental engineering, among others. We work closely with our clients to understand their unique needs and develop customized solutions that meet their requirements. From project planning to design and construction, we are committed to delivering high-quality results on every project.

- Mach number of 2.0 is considered for the speed of aircraft

- Air properties are considered according to the altitude of 40,000ft since the air properties mainly density varies significantly with the altitude.

- Air compressibility is included in the simulation for better prediction of shock waves

- Mesh is sufficiently refined near the wall along with the insertion of boundary layers to precisely simulate the near wall phenomenon

- The aircraft upstream and wake region mesh density is controlled to capture the turbulence and eddies formed at the trail of aircraft.

- Angle of Attack is set as zero for this simulation which can be varied by just using the different vector input at entry boundary condition

Drag and Lift forces are one of the main parameters considered for the aircraft designs. In addition to these forces, the other major parameter investigated is the boundary layer formed on the entire aircraft body. The overall maneuvering depends on the aerodynamic behavior of an aircraft. Boundary layer formation and type has a significant impact on the frictional heating on the aircraft surface. Typically, it is observed that the heat transfer rates increase exponentially in the transition (between laminar and turbulent boundary layer) region.

Below are the parameters that can be typically investigated in this current CFD package.

1. Drag and Lift coefficient at various Mach numbers

2. Drag and Lift coefficient at various angle of attack for a given Mach number

3. Wing airfoil shape effect on the aerodynamic performance of the aircraft

4. Shock wave effects at various Mach numbers

- 3D cleaned CAD model of the fighter jet

- Ansys Fluent Mesh file

- Step by step procedure for simulation setup and result processing 

- Online technical support for any questions and help related to using this package

Below are few additional services that can be combined with the above package

1. Online training on below topics - INR 6000 + GST (18%) 

   - Geometry preparation, meshing modules, solving & result processing 

2. Case and data files – INR 8,000 + GST (18%)