Large Scale Inlet Distortion Investigation.
Abstract
The objectives of this program were to provide an early assessment of inlet performance and distortion characteristics at critical inlet/engine operating points for an inlet design installation representative of advanced tactical aircraft. A fuselage installed, two dimensional, horizontal ramp, external compression, variable geometry, large scale inlet model was tested at both subsonic and supersonic speeds from M = 0.6 to M = 2.2. Inlet recovery, steady-state and dynamic distortion characteristics were experimentally determined over a wide range of angle of attack and yaw from alpha = -5 deg to 20 deg and beta = -10 deg to +10 deg. Constant band width FM multiplexing was used to obtain time phased fluctuating pressure characteristics at the inlet/engine interface. Recently developed computational techniques were used to process selected dynamic distortion data for use in the design of advanced engines for tactical aircraft. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1970
- Accession Number
- AD0510537
Entities
People
- G. A. Burnett
- M. T. Moore
- P. H. Kutschenreuter Jr.
Organizations
- General Electric