Accession Number : AD0741744
Title : Determination of the Drag of a Wind Tunnel Model Engine Duct by Application of the Momentum Equation.
Descriptive Note : Master's thesis,
Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
Personal Author(s) : Eggers,James A.
Report Date : MAR 1972
Pagination or Media Count : 137
Abstract : A wing body model of an advanced manned interceptor was tested for subsonic force and moment data in a five-foot wind tunnel. A removable engine package contained twin internal airflow passages. Following the collection of force data both with and without the engine package, the inlets and exits of the ducts were instrumented with pressure rakes in order to determine the momentum loss and hence the drag on the model due to the internal flow. (Author)
Descriptors : (*JET ENGINE INLETS, *DRAG), WIND TUNNEL MODELS, MOMENTUM, EQUATIONS OF MOTION, WING BODY CONFIGURATIONS, JET FIGHTERS, THESES, MODEL TESTS
Subject Categories : Aerodynamics
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE