NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Propulsion Induced Effects Test ProgramThe objective of this milestone is to assess the propulsion/airframe integration characteristics of the Technology Concept Airplane and design variations through computational analysis and experimental subsonic through supersonic wind tunnel testing. The Milestone will generate a comprehensive CFD and wind tunnel data base of the baseline, and design variations. Emphasis will be placed on establishing the propulsion induced effects on the flight performance of the Technology Concept Airplane with all appropriate wind tunnel corrections.
Document ID
20000057267
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Cappuccio, Gelsomina (NASA Ames Research Center Moffett Field, CA United States)
Won, Mark (NASA Ames Research Center Moffett Field, CA United States)
Bencze, Dan (NASA Ames Research Center Moffett Field, CA United States)
Date Acquired
August 19, 2013
Publication Date
December 1, 1999
Publication Information
Publication: 1997 NASA High-Speed Research Program Aerodynamic Performance
Volume: 1
Issue: Part 2
Subject Category
Aerodynamics
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Document Inquiry

Available Downloads

There are no available downloads for this record.

Related Records

IDRelationTitle20000057252Collected Works1997 NASA High-Speed Research Program Aerodynamic Performance Workshop
No Preview Available