DESIGNING FOR HELICOPTER

DESIGNING FOR HELICOPTER

A helicopter can be defined as any flying machine using rotating wings to provide lift, propulsion and control forces that enable the aircraft to hover relative to the ground. 

Designing a conceptual helicopter requires the basic knowledge of aerodynamics forces acting on it. Conceptual design includes the designing and calculation of major parts like main rotor disk, tail rotor and fuselage.

 The conceptual design is a primary requirement based on which further designs can be conducted. Basic historical data and empirical formula are the main pillars of design. 

For conceptual design of helicopter, a suitable reference helicopter has been selected based on which assumptions were made. 

Various calculations based on empirical formula and historical graphs have been conducted and compared with the reference helicopter. This had led us to the rotor designing. 

Point calculations and various performance parameters like power, thrust etc for different values of their dependent variable over wide range have been plotted.

CFD ANALYSIS OF TWIN JET SUPERSONIC FLOW

CFD ANALYSIS OF TWIN JET SUPERSONIC FLOW

Supersonic flows are associated with missiles, aircraft and missile engine intake and rocket nozzle. The shape of the nozzle geometry is increasingly attractive in heating, ventilation and air conditioning applications. The objective of the present work is to simulate and understand Supersonic flows with twin free jet Flow at various Mach numbers. 
The purpose is to precisely understand the fluid dynamics and variation of flow properties such as velocity and pressure in supersonic flow regime for various Supersonic flows are associated with missiles, aircraft and missile engine intake and rocket nozzle. 

The shape of the nozzle geometry is increasingly attractive in heating, ventilation and air conditioning applications. The objective of the present work is to simulate and understand Supersonic flows with twin free jet Flow at various Mach numbers. 

The purpose is to precisely understand the fluid dynamics and variation of flow properties such as velocity and pressure in supersonic flow regime for various Mach numbers and dimensionless spacing (B) between two jets. The mesh will be generated in the ICEM software. 

Twin jets flow, generated by two identical parallel axisymmetric nozzles, would be numerically investigated by FLUENT 14.0 software. The Mach number at the nozzle exit can be observed to be less in comparison with designed value. 

This is due to the viscosity and turbulence in fluid near the wall of the duct. The Mach number would be decreased due to shock wave and reversible flow. The results show that the twin jets attract each other.

 The jet flow field and the merging process of two jets vary with dimension less spacing between two jets. The width of the twin jet’s flow spreads linearly downstream and grows with dimension less spacing. 

Comparison of analytical results of the desired parameters will be made with the value obtained after the numerical analysis of the twin jet. The merging between two jets occurs at the location closer to the nozzle exit for the cases with smaller spacing between nozzles.