Determination of the Drag of a Wind Tunnel Model Engine Duct by Application of the Momentum Equation.
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1972
- Accession Number
- AD0741744
Entities
People
- James A. Eggers
Organizations
- Air Force Institute of Technology