Abstract
Propulsion system development involved aircraft manufacturer and engine or propeller manufacturer to perform test and evaluation. The main 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 was compared with analytical method and computer fluid dynamic simulation. Analytical method in this paper used vortex blade element theory to calculated static thrust meanwhile Computational fluid dynamic was running both 2 dimension and 3 dimension simulation. Vortex blade element theory analysis combined with computational flight dynamic simulation for propeller aerofoil at 70% location. Test result compared with analytical and CFD calculation using non dimensional parameter. Analytical calculation deviated 5.08% from experiment meanwhile CFD calculation give 13.56% but still in error tolerances. Error tolerances considered from friction force, sensor accuracy and air density correction with total 6.33 kgf.
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