Experimental Determination of Lift and Drag for a Coanda Yaw Thruster.
Abstract
Lift and drag forces produced by a 35% scale model of a yaw thruster device employing the Coanda effect were experimentally measured using 'fish type' spring scales. The device tested was a model of a prototype being considered for maneuvering a remotely piloted vehicle equipped with an Air Cushion Landing System while it is on the ground. Tests were conducted using cold air flow at an average pressure ratio of 1.073, a temperature between 35C and 45C, and a mass flow rate of about 3.1 lbm/sec. The effects of changing the mounting position and angle of the yaw thruster were also investigated. The radial position was varied from touching the exhaust nozzle to 0.3 in. and the horizontal position from at the exhaust nozzle exit plane to 0.74 in. The thruster mounting angle was varied from 6 degrees to 14 degrees. The optimum performance position of the yaw thruster was determined to be at a radial distance of 0.2 in., a horizontal distance of 0.23 in., and a mounting angle of 12 degrees. For this position the lift was 0.92 lb and the drag 0.75 lb. Flow visualization testing revealed a complex flow field over the thruster surface and separation of the flow for all positions tested.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1975
- Accession Number
- ADA021873
Entities
People
- Neil R. Cole
Organizations
- Air Force Institute of Technology