Propeller and Engine Testing for a Mini-Remote Piloted Research Vehicle.
Abstract
An experimental investigation was made to determine propeller and engine characteristics for a propulsion system to power the Air Force Institute of Technology's mini-remote piloted vehicle. An engine test stand for engine calibration and an engine nacelle for wind tunnel operation were designed and constructed. Engine data collected from two engines indicated that the Webra .61 had a power output of 1.09 brake horsepower at 14,620 RPM, and the O.S. Max .80 had a power output of 1.24 brake horsepower at 10,330 RPM. Also noted was a noticeably higher vibration level in the O.S. Max .80. Six propellers were tested in the wind tunnel giving complete sets of characteristics for four propeller families. From these characteristic curves and the power required curve for the design vehicle, a 12.78 inch diameter Top Flite Regular chord distribution seven inch pitch propeller was selected as the best propeller for this design when powered by two O.S. Max .80 engines.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1975
- Accession Number
- ADA023358
Entities
People
- Milton R. Sanders
Organizations
- Air Force Institute of Technology