introduction
Contents
Introduction 2
Theory 3
LIFT COEFFICIENT 3
DRAG COEFFICIENT 4
VORTEX 6
SLENDER WING-BODY 6
VORTEX-LATTICE METHOD (VORLATM1) 7
POLHAMUS LEADING EDGE SUCTION ANALOGY 8
APPARATUS 11
Results and Procedures 11
Experimental data 12
Example of calculations 15
Discussion 24
Conclusion 32
References 33
Appendix 35
Introduction
The aim of this experiment is to understand the non-linear aerodynamic characteristic of a slender wing-body (rocket shaped) by installing the slender wing-body inside the wing tunnel and run the wing tunnel at subsonic speed and changing the incidence angle of the slender from -14 to 28 degrees over period of time and record the lift and induced drag readings from a computer which is connected to the wind tunnel.
Then the readings obtained from the computer attached to the wind tunnel will be converted from M volts to Newtons (force)
Another set of results will be obtained from the FOTRAN application for vortex-lattice computational method. This application are been used for sometimes now and it will predicted the Lift and induced drag for the slender
A comparison between both sets of results will be made and a graph will be plotted for the both of them the predicted results and the experimental results.
This experiment will elaborate further study on vortex separation flow over highly-swept sharp leading-edge wing and the results obtained from this experiment will then be compared using the FOTRAN application for vortex-lattice computational method.
In the discussion section we will discuss the ability of the vortex-lattice method to predict the aerodynamic characteristics of the slender wing-body configuration. Furthermore we will Investigate and discuss the sensitivity of the vortex-lattice method predictions to the number of span-wise and chord-wise panels used in the calculations.
We will also discuss how vortex-separated flows can be exploited in aircraft manoeuvring performance.
Theory
LIFT COEFFICIENT
The lift
Introduction 2
Theory 3
LIFT COEFFICIENT 3
DRAG COEFFICIENT 4
VORTEX 6
SLENDER WING-BODY 6
VORTEX-LATTICE METHOD (VORLATM1) 7
POLHAMUS LEADING EDGE SUCTION ANALOGY 8
APPARATUS 11
Results and Procedures 11
Experimental data 12
Example of calculations 15
Discussion 24
Conclusion 32
References 33
Appendix 35
Introduction
The aim of this experiment is to understand the non-linear aerodynamic characteristic of a slender wing-body (rocket shaped) by installing the slender wing-body inside the wing tunnel and run the wing tunnel at subsonic speed and changing the incidence angle of the slender from -14 to 28 degrees over period of time and record the lift and induced drag readings from a computer which is connected to the wind tunnel.
Then the readings obtained from the computer attached to the wind tunnel will be converted from M volts to Newtons (force)
Another set of results will be obtained from the FOTRAN application for vortex-lattice computational method. This application are been used for sometimes now and it will predicted the Lift and induced drag for the slender
A comparison between both sets of results will be made and a graph will be plotted for the both of them the predicted results and the experimental results.
This experiment will elaborate further study on vortex separation flow over highly-swept sharp leading-edge wing and the results obtained from this experiment will then be compared using the FOTRAN application for vortex-lattice computational method.
In the discussion section we will discuss the ability of the vortex-lattice method to predict the aerodynamic characteristics of the slender wing-body configuration. Furthermore we will Investigate and discuss the sensitivity of the vortex-lattice method predictions to the number of span-wise and chord-wise panels used in the calculations.
We will also discuss how vortex-separated flows can be exploited in aircraft manoeuvring performance.
Theory
LIFT COEFFICIENT
The lift
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