DEVELOPMENT TESTING METHOD AND ANALYSIS FOR STATIC THRUST MEASUREMENT

• Main Author: Khasyofi, Mitra
• Format: Theses
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/34917
• Institution: Institut Teknologi Bandung

New aircraft development has to be supported with system development such as avionic, electric, structure and propulsion. Propulsion system is one of importance thing to influence aircraft performance. Propulsion system development either machine or propeller involved aircraft manufacturer and engine or propeller manufacturer that collaborated to perform test and evaluation. The main goal of this research was propulsion testing for unmanned aerial vehicle by evaluating thrust in static condition. Static thrust testing was conducted by force measurement using load cell and data acquisition systems. Thrust measurement result compared with analytic method and computer fluid dynamic simulation. Classical analytical method was vortex blade element theory to calculate static thrust meanwhile computational flight dynamic was running both 2 dimension and 3 dimension simulation. Vortex blade element theory analysis combined with Computational Fluid Dynamic simulation for propeller airfoil at location 70% from hub. This simulation was needed to get aerodynamic characteristic of airfoil to calculated thrust. 3 Dimension simulation performed using propeller geometry from reverse engineering process. Airfoil dimension (chord and pitch) distribution generated by measurement and created dummy propeller in order to produce detail CAD model. The result of this word evaluated to decide the most suitable method for propeller performance prediction and hopefully this research will be used as reference to estimate and analysis aircraft propulsion for the next aircraft development program.