Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 124
Book Description
Supersonic Stability and Control Characteristics of a Cruciform Missile Model with Delta Wings and Aft Tail Fin Control
Author: Supersonic Stability and Control Characteristics of a Cruciform Missile Model with Delta Wings and Aft Tail Fin Controls
Author: William A. CorlettPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 124
Book Description
Supersonic Stability and Control Characteristics of a Cruciform Missile Model with Delta Wings and Aft Tail Fin Controls
Author: William A. CorlettPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 124
Book Description
NASA Technical Memorandum
Author: Scientific and Technical Aerospace Reports
Author: Technical Abstract Bulletin
Author: A Study of Panel Loads and Centers of Pressure of Three Different Cruciform Aft-tail Control Surfaces of a Wingless Missile from Mach 1.60 to 3.70
Author: Milton LambMonthly Catalog of United States Government Publications
Author: Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1388
Book Description
R & D Abstracts
Author: Technology Reports Centre (Great Britain)Publisher:
ISBN:
Category :
Languages : en
Pages : 620
Book Description
Analysis and Compilation of Missile Aerodynamic Data: Data presentation and analysis
Author: James O. NicholsPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 132
Book Description
This summary document was prepared in order to facilitate dissemination of a large amount of missile aerodynamic data which has recently been declassified. Only summary data are presented in this report, but a list of reference documents provides sources of detailed data. Most of the configurations considered are suitable for highly maneuverable air-to-air or surface to air missiles; however, data for a few air-to-surface, cruise missile, and one projectile configuration are also presented. The Mach number range of the data is from about 0.2 to 4.63; however, data for most configurations cover only a portion of this range. The following aerodynamic characteristics at various Mach numbers and zero angle of attack are presented.