NDLI: Experimental aerodynamic characteristics of two v/stol fighter/attack aircraft configurations at mach numbers from 0.4 to 1.4

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Experimental aerodynamic characteristics of two v/stol fighter/attack aircraft configurations at mach numbers from 0.4 to 1.4

Content Provider	NASA Technical Reports Server (NTRS)
Author	Lummus, J. R. Nelms, W. P. Durston, D. A.
Copyright Year	1980
Description	A wind tunnel test was conducted to measure the aerodynamic characteristics of two horizontal attitude takeoff and landing V/STOL fighter/attack aircraft concepts. In one concept, a jet diffuser ejector was used for the vertical lift system; the other used a remote augmentation lift system (RALS). Wind tunnel tests to investigate the aerodynamic uncertainties and to establish a data base for these types of concepts were conducted over a Mach number range from 0.2 to 2.0. The present report covers tests, conducted in the 11 foot transonic wind tunnel, for Mach numbers from 0.4 to 1.4. Detailed effects of varying the angle of attack (up to 27 deg), angle of sideslip (-4 deg to +8 deg), Mach number, Reynolds number, and configuration buildup were investigated. In addition, the effects of wing trailing edge flap deflections, canard incidence, and vertical tail deflections were explored. Variable canard longitudinal location and different shapes of the inboard nacelle body strakes were also investigated.
File Size	51735054
Page Count	532
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19810006466
Archival Resource Key	ark:/13960/t6256f70k
Language	English
Publisher Date	1980-12-01
Access Restriction	Open
Subject Keyword	Aerodynamics Tables Data V/stol Aircraft Reynolds Number Wind Tunnel Tests Attack Aircraft Aerodynamic Characteristics Aircraft Configurations Sideslip Graphs Charts Data Bases Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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