Author: John D. BirdPublisher:
ISBN:
Category :
Languages : en
Pages : 58
Book Description
An Analysis of the Stability and Control of Ballistic Supersonic Impact Reentry Bodies
Author: John D. BirdAn Investigation to Determine the Stability Characteristics of Three Supersonic-impact Ballistic Reentry Shapes at Mach Numbers from 1.2 to 4.2
Author: Static Stability Investigation of Supersonic-impact Ballistic Reentry Shapes at Mach Numbers of 2.55 and 3.05
Author: John M. SwihartExperimental Investigation of Pressure Distribution and Static Aerodynamic Characteristics for Three Supersonic Impact Ballistic Reentry Shapes at Mach Numbers of 1.93, 2.55, and 3.05
Author: An Exploratory Investigation in a Ballistic Range of the Stability Derivatives of a Simple Airplane Configuration at Low Supersonic Speeds
Author: Charles E. DeRosePublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 30
Book Description
Some Effects of Jet Pluming on the Static Stability of Ballistic Bodies at a Mach Number of 6.00
Author: Robert J. McGheePublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
Book Description
Experimental Investigation of Pressure Distribution and Static Aerodynamic Characteristics for Three Supersonic Impact Ballistic Reentry Shapes at Mach Number of 1.93, 2.55 and 3.05
Author: Odell A. MorrisThe Aerodynamic Damping and Oscillatory Stability in Pitch of Two High-drag Bodies of Revolution at Transonic Speeds
Author: Three-degree-of-freedom Evaluation of the Longitudinal Transfer Functions of a Supersonic Canard Missile Configuration Including Changes in Forward Speed
Author: Ernest C. SeabergPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
Book Description
A reevaluation of existing flight data obtained for a supersonic canard missile configuration of the boost-glide type has been made to determine derivatives not previously evaluated. These derivatives, together with those previously evaluated and published, have been utilized to determine some typical airframe frequency responses based on the three-degree-of-freedom longitudinal equations of motion.
Author: