Transonic off-design drag and performance of an axisymmetric inlet with 40 percent internal contraction on design
View
@ University of Illinois
Woollett, Richard R
Description
"NASA TM X-3042."Performing organization report no.: E-7692."August 1974."Cover title.Includes bibliographical references (p. 18).An experimental investigation determined the drag and pressure performance of an axisymmetric supersonic inlet when operated in the transonic speed range. The inlet configuration was derived from a Mach 2.5 mixed compression inlet design with assumed variable geometry. At typical engine airflows the drag coefficient varied from 0.057 to 0.192 when the Mach number changed from 0.80 to 1.27. The presence of a wing simulator resulted in a sizable increase in total drag at Mach 1.2. This interference drag, which is roughly a 0.1 increase in drag coefficient, originates equally from an increase in both additive and cowl pressure drag.Also available online from the NASA Technical Reports Server (http://ntrs.nasa.gov/). Address as of 9/19/16: http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19740023304_1974023304.pdf.Performed by Lewis Research Center, Cleveland, Ohio501-24
Text
Language Material Electronic Resource
Choby, David AMeleason, Edward TLewis Research Center
Public domain. Learn more at http://www.hathitrust.org/access_use
