Delta Wing

The delta wings in modern days large operated in jet fighter aircraft. The tremendous changes in the wing design of delta wing. Using 2-D and 3-D model analysis for different delta wing configuration will be analyzed Using ANSYS-FLUENT. 

The simulation of different configuration will be carried out using k-Ω (SST) model for sonic, transonic, supersonic conditions. 

The optimum performance carried out of different configuration to be analyzed & calculating wave drag by manual technique. Compare different delta wing configuration by graphs which plotted in Microsoft word.

INJECTORS USED IN SCRAMJET COMBUSTOR

Using 2-D model, the cold flow analysis of scramjet engine will be carried out using ANSYS-Fluent. The simulation for different parameters such as cold flow performance, injection of hydrogen in combustor and process of combustion by addition of heat will be compared for two different types of injectors. i.e. planer strut injector and ojival body injector. The turbulence model used for simulation will be k-ε . The overall performance of both injectors will be analysed on the basis of above mentioned parameters.

THEORETICAL AND NUMERICAL ANALYSIS OF SR-71'S INLET FOR DIFFERENT MACH REGIME

The objective of this research project is to carry out theoretical and numerical simulation of SR-71’s inlet for different Mach no. such as 1.7, 2.0, 2.5, 3.0 and 3.2. The SR-71’s inlet was having a variable spike geometry, which helps in sufficient airflow within the engine at supersonic speed and in pressure recovery. 

Modelling and numerical analysis are being carried out in ANSYS-ICEM AND FLUENT. To validate the theoretical values/results, the computational analysis for the same Mach no, will be done.

 The work is to be carried out to observe the changes across the shock in the inlet of SR-71. Additionally, stagnation pressure recovery calculation will also be done for the prescribed range of supersonic Mach no’s.

CFD ANALYSIS OF AN INTEGRATED RAMJET ENGINE

CFD ANALYSIS OF AN INTEGRATED RAMJET ENGINE

Using 3-D and 2-D axis-symmetrical model, the cold flow performance of an integrated ramjet engine will be predicted for different Mach numbers and the analysis will be carried out in the CFD Tutor and ANSYS-Fluent respectively. 

Along with the cold flow analysis the hot flow analysis for ramjet engine will also be carried out. Lastly for different air-fuel ratios at the given mach numbers the optimum thrust condition will be analysed for given flight conditions. 

The overall performance of an integrated ramjet engine comprising of air intake, combustor and nozzle will be investigated through the above simulations.

DESIGN, MODELLING AND ANALYSIS OF SUPERSONIC PASSENGER TRANSPORT

DESIGN, MODELLING AND ANALYSIS OF SUPERSONIC PASSENGER TRANSPORT

In recent years new configurations for large commercial transport aircraft have been investigated to meet an increasing demand in international travel, particularly between major capital cities (hubs).

 Supersonic Green Machine is one of two designs presented in April 2010 to the NASA Aeronautics Research Mission Directorate for its NASA Research Announcement funded studies into advanced supersonic cruise aircraft that could enter service in the 2030 2035 timeframe. 

The green machine will also have Combustors to help to reduce the amount of nitrous oxide emission by 75%. The Green Machine will be able to reach speeds of 1,218 mph (1,960 Km/h) and would take 8 to 9 hours from the UK to Australia. 

The purpose of this project to design the Supersonic green machine cad model from the conceptual design presented by NASA and examine the viscous, compressible and steady-state flow over the aircraft using computer simulation techniques. This project outlines the development of a computational mo

NUMERICAL AND ANALYTICAL ANALYSIS ON BI-CONVEX AIRFOIL FOR DIFFERENT FLOW REGIMES

NUMERICAL AND ANALYTICAL ANALYSIS ON BI-CONVEX AIRFOIL FOR DIFFERENT FLOW REGIMES

The problem has been taken up to find the aerodynamic characteristics of bi-convex airfoil. The Bi-Convex airfoils are used at supersonic and hypersonic speeds. 

The aerodynamic characteristics will be obtained for different thickness values for the Bi-Convex airfoil. 

At different flow regimes the Numerical analysis of the bi-convex airfoilwill be done and the results so obtained will be compared with the Analytical values obtained based on the expansion and oblique shockwave theory. 

The numerical analysis will be carried out using ANSYS - FLUENT.

DESIGNING, TESTING AND ANALYSIS OF LOW SPEED SUBSONIC WIND TUNNEL

DESIGNING, TESTING AND ANALYSIS OF LOW SPEED SUBSONIC WIND TUNNEL

This final year project is intended to design and fabricate a wind tunnel equipped with test section for the experimental research at our institute. 

The aim is to make a wind tunnel of low subsonic speed and to test various test profiles which we have made ourselves. 

The team has to make the design of the wind tunnel as the main challenge in the project is to develop the wind tunnel and then the aerodynamic characteristics test are to be conducted for various test profiles. 

The main hurdle is to properly seal the entire structure of wind tunnel and also the number of hours the team has to put after it as we are new to such fabrication.

 A fan is kept at the end of the diffuser section of the wind tunnel which creates the suction of air at the inlet chamber of the wind tunnel. The test section is kept transparent so as we can measure the aerodynamic characteristics over the surface of the test profile.

 We will be obtaining various parameters from the experiment and then we will compare those obtained results with the results obtained by CFD analysis.

 The results obtained by CFD analysis are almost similar to the results obtained from the experiment. The contours of various parameters were plotted so as to analyse the flow over the test profile.

SIMULATION AND ANALYSIS OF AIRCRAFT’S PITCH AXIS USING DIFFERENT CONTROLLERS

SIMULATION AND ANALYSIS OF AIRCRAFT’S PITCH AXIS USING DIFFERENT CONTROLLERS

process control problems can be adequately and routinely solved by conventional Proportional - Integral – Derivative control strategies. 

The overriding reason that the PID controller is so widely accepted is its simple structure which has proved to be very robust with regard to many commonly met process control problems as for instance, disturbance and nonlinearities. Relay feedback method have been widely used in tuning PID controller due to its closed loop nature.

 In this work, Relay based PID controller has been designed and successfully implemented on a DC motor in SISO (Single Input Single Output) configuration. 

Other than this, state feedback controller has been applied and further its results are compared with PID controller. 

In this simulation, the pitch axis will be controlled using DC motor. The entire simulation has been carried out in MATLAB environment. Results demonstrate the effectiveness of the design controller.

STRESS ANALYSIS OF A REAR PRESSURE BULKHEAD OF THE FUSELAGE STRUCTURE

STRESS ANALYSIS OF A REAR PRESSURE BULKHEAD OF THE FUSELAGE STRUCTURE

When designing an aircraft, it’s all about finding the optimum proportion of the weight of the vehicle and payload. It needs to be strong and stiff enough to withstand the exceptional circumstances in which it has to operate. Durability is an important factor. 

Also, if a part fails, it doesn’t necessarily result in failure of the whole aircraft. A bulkhead is the physical partition that divides a plane into different classes or sections.

 Typically, a bulkhead is a wall but can also be curtain or screen. In addition to separating classes from one another, i.e. business and economy, bulkheads can be found throughout the plane, separating the seats from the gallery and lavatory areas.

 A pressure bulkhead assembly adapted for installation in an aircraft fuselage includes a bulkhead web and reinforcing structure. The bulkhead web has a first side facing the pressurized compartment and a second side opposite the first side.

 The reinforcing structure, which is formed from a series of primary beam members, secondary beam members, and connecting elements, is provided on the second side of the bulkhead web. 

A rear pressure bulkhead with all stiffening members is considered in this analysis. Due to internal pressurization the rear pressure bulkhead will undergo out of plane bending. 

One surface of the pressure bulkhead will undergo tension and the other will undergo compression simultaneously, as a result the stiffening members attached to the rear pressure bulkhead will also undergo tension and compression modes. 

A Stress analysis is carried out on rear pressure bulkhead panel to identify the maximum tensile stress location. Fatigue life to crack initiation at the location of highest tensile stress will be predicted.

THERMAL ANALYSIS OF GAS TURBINE BLADE

THERMAL ANALYSIS OF GAS TURBINE BLADE

A turbine blade is the individual component which makes up the turbine section of a gas turbine. The blades are responsible for extracting energy from the high temperature, high pressure gas produced by the combustor.

 Turbine blades are subjected to very strenuous environments inside a gas turbine. They face high temperatures, high stresses, and a potentially high vibration environment. 

All three of these factors can lead to blade failures, which can destroy the engine, and turbine blades are carefully designed to resist those conditions. Here we specified only in temperature parameter.

 Cooling of gas turbine blades is a major consideration because they are subjected to high temperature working conditions. The forced convection heat transfer from the blade to the cooling air will reduce the temperature of the blade to allowable limits. 

Finite volume analysis is used in the present work to examine steady state thermal for Graphite, Stainless Steel & Titanium. In design and analysis of Gas turbine blade, CATIA is used for design of solid model and ANSYS is for analysis.

 Three different models consisting of solid blade and blades with varying number of holes are analyzed to find out the optimum number of cooling holes

TO STUDY THE FEASIBILITY OF SETTING UP THE SURVEILLANCE RADAR ELEMENT (SRE) AFTER INSTALLATION AT AI

TO STUDY THE FEASIBILITY OF SETTING UP THE SURVEILLANCE RADAR ELEMENT (SRE) AFTER INSTALLATION AT AI

Theoretically, the lobe pattern of a High Power microwave primary radar system may be covering the entire space all around the radar station but practically the pattern differs depending upon various reasons like topology of the surrounding area within the coverage distance of radar which we will evaluate at the Porbandar Radar Station. 

Factors which affect the lobe pattern are  -Presence of mountain/tall hills, -Tall buildings and industrial structure, -Large water body etc.

CFD ANALYSIS FOR MISSILE-FIN CONFIGURATION

CFD ANALYSIS FOR MISSILE-FIN CONFIGURATION

Missile is an object or weapon suitable for throwing, projecting or directing at a target. The fin is attached at the end of the missile. Fin is the stabilizing and guiding unit of a missile. 

It is an aerodynamic surface of the missile for the purpose of giving directional stability and for good maneuverability. The purpose of this project is to compare maneuverability of missile by using different fin design. 

In this study, investigation of aerodynamic coefficient and flow structure in subsonic flow on missile configuration by using different types of fin design. Viscous based model is being used to simulate the flow. 

Analysis of fin configuration and its behaviour by changing angle of attack and check which design of fin gives good stability. II

SUPERSONIC FLOW OVER DOUBLE CIRCULAR ARC AND EDGE AIRFOIL

SUPERSONIC FLOW OVER DOUBLE CIRCULAR ARC AND EDGE AIRFOIL

With the given task, the numerical part and simulation part have to be completed separately and after the results it has to be compared whether the commercial codes in CFD is using working turbulence models. 

The numerical analysis part has to be started by understanding the given data. The theory about the given data then have to be analyzed and calculated with right understanding of the formulas. 

The sequent for the solving the task would be started by geometrical analysis of the airfoil. Thickness of the airfoil could be found easily with geometry.

 After determining the thickness of the airfoil, location of the leading edge shocks has to be study. Strength of the shock could be determined after the study of the pressure difference after the shock over entrance pressure of the shock. 

Lift and drag coefficient could be calculated by only neglecting the expansion waves caused by the bi-conical surface. As the area and pressure varies by the geometry, differential calculations are used in order to calculate both drag and lift coefficient.

DESIGN OF HIGH SPEED VTOL AIRCRAFT

DESIGN OF HIGH SPEED VTOL AIRCRAFT

the primary technical objectives of the VTOL design are to demonstrate radical improvements in flight speeds, hover efficiency, and cruise efficiency of VTOL aircraft, and to demonstrate the ability to perform useful work throughout the flight envelope.

TO DESIGN LONG RANGE BUSINESS JET AIRCRAFT AND FLOW ANALYSIS OVER WING.

TO DESIGN LONG RANGE BUSINESS JET AIRCRAFT AND FLOW ANALYSIS OVER WING.

aircraft design is a separate discipline of aeronautical engineering – different from analytical disciplines such as aerodynamics, structures, controls, and propulsion. It is not just the actual layout, but also the analytical processes used to determine what should be designed and how the design should be modified to better meet the requirements. Aircraft design can be broken into three major parts – conceptual design, preliminary design, and detail design. 

We here mainly concentrate on developing a conceptual design of a Business Jet. . Business jet, private jet or, colloquially, Bizet is a term describing a jet aircraft, usually of smaller size, designed for transporting groups of business people or wealthy individuals. Business jets may be adapted for other roles, such as the evacuation of casualties or parcel deliveries, and a few may be used by public bodies, governments or the armed forces. 

The more formal terms of corporate jet, executive jet, VIP transport or business jet tend to be used by the firms that build, sell, buy and charter these aircraft. The starting point of any aircraft is to clearly identify its purpose. 

With modern Business aircrafts, a proposal for a new design usually comes as the response to internal studies that aim to project future market needs. Our main purpose is to design long range business jet aircraft with passenger capacity of 14 to 16 and its range is 6000 nm. 

The cruising altitude of our aircraft is 40,000 feet. Two engines will be kept at the empennage section and how much thrust is required will be estimated after designing is completed. The tail section will be in T shape. 

We will design our business jet with the help of Catia V5 and than analysis will be carried out over the wing. The analysis of wing will be carried out by keeping in mind the angle of attack and stalling speed.

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.

TO STUDY A STEADY AND UNSTEADY CFD ANALYSIS OVER DELTA WING

TO STUDY A STEADY AND UNSTEADY CFD ANALYSIS OVER DELTA WING

The study is aimed at assessing the application of the latest un stationary CFD method, detached Eddy simulation, to simulate the flow field around blunt leading edge delta wings.

 For this purpose using different sweep back angle delta wing to perform numerical investigations at the Reynolds numbers of 6 million, Mach number of 0.4 and Angle of Attack of 18.5 to 24. As the nature of the study is mainly exploratory, various numerical grids have been used. 

Viscous flow model will be used to realize the real flow physics. To study the behavior of the high-performance aircrafts featuring delta wing plan forms, in the past simplified geometry was the sharp leading edge, slender delta wing

FLOW ANALYSIS OF ROCKET NOZZLE FOR VARIABLE DIVERGENCE ANGLE

FLOW ANALYSIS OF ROCKET NOZZLE FOR VARIABLE DIVERGENCE ANGLE

A nozzle is used to give the direction to the gases coming out of the combustion chamber. Nozzle is a tube with variable cross-sectional area. 

Nozzles are generally used to control the rate of flow, speed, direction, mass, shape, and/or the pressure of the exhaust stream that emerges from them. 

The nozzle is used to convert the chemical-thermal energy generated in the combustion chamber into kinetic energy. The nozzle converts the low velocity, high pressure, high temperature gas in the combustion chamber into high velocity gas of lower pressure and low temperature. 

Our study is carried using software’s like fluent for analyzing the flows in the nozzle. 

Numerical study has been conducted to understand the air flows in a conical nozzle at different divergence degrees of angle using two-dimensional axisymmetric models, which solves the governing equations by a control volume method. The nozzle geometry co-ordinates are taken by using of method of characteristics which usually designed for De-Laval nozzle. 

The present study is aimed at investigating the supersonic flow in conical nozzle for Mach number 3 at various divergence degree of angle. The throat diameter and inlet diameter is same for all nozzles with various divergence degree of angles. The flow is simulated using fluent software. 

The flow parameters like pressure, Area of nozzle at exit are defined prior to the simulation. The result shows the variation in the Mach number, pressure, temperature distribution and turbulence intensity.

NUMERICAL INVESTIGATION OF TRAPPED VORTEX COMBUSTOR

NUMERICAL INVESTIGATION OF TRAPPED VORTEX COMBUSTOR

A new combustor concept referred as the trapped vortex combustor (TVC) employs a vortex that is trapped inside a cavity to stabilize the flame. The cavity is formed between two axis-symmetric disks mounted in tandem. 

TVC offers many advantages when compared to conventional swirl stabilizers. In the present work, numerical investigation of cold flow (non-reacting) through 3D trapped vortex combustor will be performed.

 Commercial CFD software Fluent has been used for this study. The other main objective of our study will be to evaluate the performance and combustion stability of trapped vortex combustor when the fuel-air ratios are varied. 

This will in turn lead to change in diameter of air injection holes present at the cavity walls. For different fuel-air ratios, diameters will be calculated from one dimensional continuity equation.

CFD ANALYSIS FOR HIGH-LIFT CONFIGURATION TO CAPTURE AERODYNAMIC COEFFICIENT

 CFD ANALYSIS FOR HIGH-LIFT CONFIGURATION TO CAPTURE AERODYNAMIC COEFFICIENT

The sizing and efficiency of an aircraft is largely determined by the performance of its high-lift system. Subsonic civil transports most often use deployable multi-element aerofoils to achieve the maximum-lift requirements for landing, as well as the high lift-to-drag ratios for take-off. However, these systems produce very complex flow fields which are not fully understood by the scientific community. In order to compete in today's market place, aircraft manufacturers will have to design better high-lift systems. As part of this effort, computational aerodynamic tools are being used to provide preliminary flowfield information for instrumentation development, and to provide additional insight during the data analysis and interpretation process. Flow computation around a simplified three element high lift configuration without the fuselage and a realistic high lift configuration with fuselage are performed to study flow near wing-fuselage junction and also determine the flow separation with angle of attack.

CFD ANALYSIS USING DIFFERENT MESHING SCHEMES

CFD ANALYSIS USING DIFFERENT MESHING SCHEMES

The multigrid algorithm is an extremely efficient method of approximating the solution to a given problem. The functions involved in the calculations are all discrete, or discontinuous, 

The algorithm's efficiency lies in the fact that once an approximate solution to the problem is found its accuracy can be improved using calculations on increasingly sparse grids which require less processing power. 

In this project the theory behind the multigrid algorithm was studied and a computer analysis was done in solving the problem of natural convection. 

Stream function-Vorticity approach and the Bossinesq approximation were used in the analysis. Also, the same problem was solved using the Multigrid algorithm using Fluent software. The results obtained were matched with the analytical results.

COLD FLOW ANALYSIS OF SCRAMJET ENGINE

COLD FLOW ANALYSIS OF SCRAMJET ENGINE

The combined analytical and computational analysis is carried on the scramjet engine design. Numerical turbulence model is verified for better prediction of results computationally.

 Then Computational analysis is carried out for different ramp at inlet to obtain efficient intake. Factors considered are total pressure loss, entropy change, pressure ratio and temperature ratio in analysis of different ramp design. 

Furthermore a flow field prediction of complete scramjet engine with cold flow is carried out computationally. 

Then solution of separation bubble by including circular slit inside isolator is tested computationally. Circular slit is modified for minimum temperature and turbulent kinetic energy inside isolator section.

AERODYNAMIC ANALYSIS OF WIND TURBINE BLADE

AERODYNAMIC ANALYSIS OF WIND TURBINE BLADE

Computational Fluid Dynamics (CFD) software was used to compare the performance of a wind turbine blade. The geometry was simplified to 2D airfoils and the surrounding flow field. 

It was found that the lift/drag characteristics of the two airfoils across a range of angles of attack were virtually identical, meaning that the torque force exerted on the wind turbine blades would also be identical and therefore as would the power outputs of the two turbines.

 However, the simple model ignored a number of important issues, such as 3D effects on the idealized blade geometry. Further modelling and/or experimental validation work is needed to increase confidence in the quality of the results.