Experimental investigation of aerodynamic characteristics of NACA23015 under different angles of attack and comparison with available package

الملخص EN

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.