NDLI: Calculated performance, stability and maneuverability of high-speed tilting-prop-rotor aircraft

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Calculated performance, stability and maneuverability of high-speed tilting-prop-rotor aircraft

Content Provider	NASA Technical Reports Server (NTRS)
Author	Johnson, Wayne Bowles, Jeffrey V. Lau, Benton H.
Copyright Year	1986
Description	The feasibility of operating tilting-prop-rotor aircraft at high speeds is examined by calculating the performance, stability, and maneuverability of representative configurations. The rotor performance is examined in high-speed cruise and in hover. The whirl-flutter stability of the coupled-wing and rotor motion is calculated in the cruise mode. Maneuverability is examined in terms of the rotor-thrust limit during turns in helicopter configuration. Rotor airfoils, rotor-hub configuration, wing airfoil, and airframe structural weights representing demonstrated advance technology are discussed. Key rotor and airframe parameters are optimized for high-speed performance and stability. The basic aircraft-design parameters are optimized for minimum gross weight. To provide a focus for the calculations, two high-speed tilt-rotor aircraft are considered: a 46-passenger, civil transport and an air-combat/escort fighter, both with design speeds of about 400 knots. It is concluded that such high-speed tilt-rotor aircraft are quite practical.
File Size	3415991
Page Count	45
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19870008262
Archival Resource Key	ark:/13960/t2799284c
Language	English
Publisher Date	1986-09-01
Access Restriction	Open
Subject Keyword	Aircraft Design, Testing And Performance Structural Design Aircraft Stability Performance Tests Tilt Rotor Aircraft Maneuverability Hubs Aeroelasticity Requirements Aerodynamic Loads Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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