Longitudinal Aerodynamic Characteristics of an Aircraft Model with and Without Winglet
The measurement of aerodynamic forces and moments acting on an aircraft model is important for the development of wind tunnel measurement technology. The primary purpose of wind tunnel measurements over the model for the forces and moments is to predict the performance of the full-scale vehicle....
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| Main Author: | |
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| Format: | Thesis |
| Language: | English English |
| Published: |
2005
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| Subjects: | |
| Online Access: | http://psasir.upm.edu.my/id/eprint/6014/1/FK_2005_19.pdf |
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| Summary: | The measurement of aerodynamic forces and moments acting on an aircraft model is
important for the development of wind tunnel measurement technology. The primary
purpose of wind tunnel measurements over the model for the forces and moments is
to predict the performance of the full-scale vehicle. Force measurement techniques
in wind tunnel testing are necessary for determining a variety of aerodynamic
performance parameters. For three-dimensional aircraft models, forces and moments
are usually measured directly using a balance system. The balance mechanically
separates the total aerodynamic load on a model into its six aerodynamic
components. Two fundamental types of balances, external and internal balances, are
used today. External balances carry the loads outside the tunnel before they are
measured and internal balances which fit in the model and are arranged to send data
out through electrical wires.In this research work, six-component external balance is commissioned and the
calibration has been thoroughly checked and the detailed procedure of measurement
of aerodynamic forces is recommended. A set of winglet has been designed for the
existing aircraft model at the Aerodynamics laboratory of the Aerospace
Engineering Department, UPM. Further the aerodynamic forces are measured on the
aircraft model having a rectangular wing with and without winglet attached to the
model. Tests have been carried out on the aircraft model with and without winglet at
the Reynolds numbers 170,000, 210,000 and 250,000. The experimental results
show that lift curve slope increases by 1-6% with the addition of certain winglet
configurations and at the same time the drag decreases by 20-28% as compared to
those for the aircraft model without winglet for the maximum Reynolds number
considered in the present study. |
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