Authors
Abstract
A Model of wing section of type (NACA 23015) had been built to be investigated and
study the aerodynamic characteristics in a subsonic wind tunnel at different angles of
attack in order to calculate the aerodynamic coefficients such as lift, drag, moment and
pressure coefficients. The effect of changing the angle of attack on the aerodynamic
coefficients was investigated. Then a virtual model of the wing section and wind tunnel
had been programmed and tested by available standard packages such as the (Design
Foil) Program which uses Panel Method to calculate the aerodynamic coefficients, and
the finite element package (Ansys Ver.9). A comparison was made to the arrived results
with the experimental data to check the accuracy of the results, and both experimental
and theoretical results were convergent. The percentage of similarity between the
experimental and theoretical was 83% for the Aerodynamic characteristics.
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