Aerodynamic Flow and Effects around a Double Edge Aerofoil in Supersonic Flow

The first 200 words of this essay...

Aerodynamic Flow and Effects around a Double Edge Aerofoil in Supersonic Flow

Experiment Objectives 3

Introduction 3

Background 3

Nomenclature 4

Experimental Apparatus 5

Experimental Procedure 7

Results 8

Pressure Tap Readings 8

Schlieren Images 10

Theory and Calculations 12

Mach number and Pressure Ratio 12

Lift and Drag Coefficients 14

Discussion 16

Conclusion 17

References 18

Appendix 19

Tables of Calculations 19

Convergent-Divergent Nozzle Flows 22

Supersonic Aerofoil Flow 22

Theoretical Lift and Drag Coefficients 23

Experiment Objectives

The purpose of this lab is to analyze the changes in the aerodynamic properties, such as the Mach number, Pressure and also Lift, Drag and Pressure coefficients, in supersonic flow around a double wedge aerofoil. Also to see the effects of oblique shock waves on these properties.

Introduction

Background

A high-speed wind tunnel is a pressurized, intermittent-flow facility capable of running in the subsonic, transonic and supersonic flow regimes. A supersonic wind tunnel is a wind tunnel that produces supersonic speeds (1.2<M<5). Supersonic speeds can be achieved with an appropriate design of a convergent divergent nozzle.