Longitudinal Aerodynamic Performance Of An Aircraft Model

Fong, See Yan (2009) Longitudinal Aerodynamic Performance Of An Aircraft Model. Project Report. UTeM, Melaka, Malaysia. (Submitted)

	PDF (24 Pages) Longitudinal_Aerodynamic_Performance_Of_An_Aircraft_Model_-_24_pages.pdf - Submitted Version Download (212kB)
	PDF (Full Text) Longitudinal_Aerodynamic_Performance_Of_An_Aircraft_Model2.pdf - Submitted Version Restricted to Registered users only Download (1MB)

Abstract

This study carried out to examine the effect of variation angle of attack and angle of elevator deflection on the lift coefficient, drag coefficient and pitching moment coefficient. This project is initial study to obtaining control law of UAV. The stability derivative equation in the longitudinal direction is determined. Test plan, design aircraft model support and templates to fix control surface angle are conducted before implement wind tunnel testing. An aircraft model Piper J-3 Cub 4 is used to test in closed circuit low speed wind tunnel in order to reach the objective of the project. The experiments are conducted at a constant low speed flow field which also called as subsonic. The experiment results of coefficients are applied into stability derivative equation for this aircraft model Piper J-3 Cub 4. The details to derive lift coefficient and pitching moment coefficient and basic of longitudinal aerodynamic characteristics were studies in this study. From the results, it is found that elevator contribute high effectiveness to this aircraft model Piper J-3 Cub 4. This aircraft model Piper J-3 Cub 4 longitudinal direction characteristics had been discovered.

Actions (login required)

View Item