Website Search
Find information on spaces, staff, and services.
Catalog Search
Books
Transonic drag of several jet-noise suppressors
- Author / Creator
- Available as
- Online
- Summary
-
An experimental evaluation of the aerodynamic drag of several jet noise suppressors was conducted. The one-fifth scale suppressors were tested over a Mach number range from 0.65 to 1.10 at several ...
An experimental evaluation of the aerodynamic drag of several jet noise suppressors was conducted. The one-fifth scale suppressors were tested over a Mach number range from 0.65 to 1.10 at several nozzle pressure ratios.
The least drag was caused by the lobe-type suppressors. The eight-lobe nozzle with ejector caused the greatest drag.
The cruise propulsive-thrust loss of the tube nozzle and the eight-lobe nozzle tith ejector should be about 6 1/2 percent of the net thrust for the standard nozzle. The lobe nozzles and the standard nozzle with ejector should cause losses equivalent to 3 or 4 percent of the standard-nozzle net thrust.
Details
- Creator
- by Warren J. North
- Format
- Books
- Language
- English
- Contributors
- Publication
-
- Washington, D.C. : National Advisory Committee for Aeronautics, 1958
- Physical Details
-
- 1 online resource (34 pages) : illustrations, photographs
- data file
- OCLC
- on1440237576
- Report numbers NACA-TN-4269.
- Date of issue: April 1958.
- "Lewis Flight Propulsion Laboratory."
- Title from title screen (viewed June, 6, 2024)
- Includes bibliographical references (page 9)
- Electronic reproduction. Denton, Texas : University of North Texas, 2011. Electronic reproduction from print master produced by University of North Texas.