Author: Warren Jr GillespiePublisher:
ISBN:
Category :
Languages : en
Pages : 42
Book Description
Rocket-powered Model Investigation of Lift, Drag, and Stability of a Body-tail Configuration at Mach Numbers from 0.8 to 2.3 and Angles of Attack Between Plus Or Minus 6.5 Degrees
Author: Warren Jr GillespieRocket-model Investigation of Lateral Stability Characteristics and Power Effects of a Jet-engine Airplane Configuration with Tail Boom at Mach Numbers from 1.15 to 1.37
Author: T. Bradley CurryPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 34
Book Description
Lift, Drag, and Longitudinal Stability at Mach Numbers from 1.4 to 2.3 of a Rocket-powered Model Having a 52.5 Degree Sweptback Wing of Aspect Ratio 3 and Inline Tail Surfaces
Author: Warren Jr GillespieStability of Two Rocket-propelled Models Having Aspect-ratio-5 Unswept Tails on a Long Body for the Mach Number Range of 1.7 to 2.4
Author: Reginald R. LundstromPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 48
Book Description
Two rocket models having cruciform, aspect-ratio-5, unwswept tails and a fineness-ratio-20 fuselage were flight tested over a Mach number range of approximately 1.7 to 2.4. One of the models had cruciform, aspect-ratio-3.4 forward surfaces in line with the tails. The models were given step disturbances by pulse rockets at intervals throughout the Mach number range and stability derivatives were obtained from the measured responses. The roll rates of the models varied from 10 radians per second to 5 radians per second.
Static Stability Investigation of a Sounding-rocket Vehicle at Mach Numbers from 1.50 to 4.63
Author: C. Donald BabbPublisher:
ISBN:
Category : Sounding rockets
Languages : en
Pages : 82
Book Description
Lift, Drag, and Longitudinal Stability at Mach Numbers from 0.8 to 2.1 of a Rocket-powered Model Having a Tapered Unswept Wing of Aspect Ratio 3 and Inline Tail Surfaces
Author: Warren Jr GillespieAerodynamic Characteristics in Pitch of Several Triple-body Missile Configurations at Mach Numbers 0.6 to 1.4
Author: Earl D. KnechtelPublisher:
ISBN:
Category : Charts, diagrams, etc
Languages : en
Pages : 36
Book Description
An experimental investigation was conducted to determine the longitudinal aerodynamic characteristics at transonic speeds of missile configurations having three blunted cone-cylinder bodies. Modifications of the basic model were tested to indicate the effects of (a) relative lengths of coplanar bodies, (b) seals between the cylindrical portions of the bodies, (c) horizontal connecting surfaces near the rear of the bodies, and (d) triangular rather than coplanar body grouping. Lift, drag, and pitching-moment data were obtained at angles of attack from -4 to 12 degrees and Mach numbers from 0.6 to 1.4 for a constant Reynolds number of 5,500,000, based on average body length.
Results of Rocket Model Test of an Airplane Configuration Having an Arrow Wing and Slender Flat-sided Fuselage
Author: Robert F. PeckPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 26
Book Description
A rocket-propelled model of an airplane configuration having an arrow wing with 55 degree leading-edge sweep and a flat-sided fuselage mounting swept horizontal and vertical tails has been tested through use of the pulse-control technique at Mach numbers between 1.0 and 2.3. Results are presented from an investigation of longitudinal trim, lift, stability, drag, lateral force, thrust, and jet effects.
Effects of Body and Fin Deflections on the Aerodynamic Characteristics in Pitch of a 0.065-scale Model of a Four-stage Rocket Configuration at Mach Numbers of 1.41 and 1.82
Author: Ross B. RobinsonPublisher:
ISBN:
Category : Mach number
Languages : en
Pages : 38
Book Description
Flight Stability and Automatic Control
Author: Robert C. NelsonPublisher: WCB/McGraw-Hill
ISBN: 9780071158381
Category : Aerodynamique / Aeronautique / Aerospatial / Automatique / Avion / Commande / Conception / Controle / Navigation / Stabilite
Languages : en
Pages : 441
Book Description
The second edition of Flight Stability and Automatic Control presents an organized introduction to the useful and relevant topics necessary for a flight stability and controls course. Not only is this text presented at the appropriate mathematical level, it also features standard terminology and nomenclature, along with expanded coverage of classical control theory, autopilot designs, and modern control theory. Through the use of extensive examples, problems, and historical notes, author Robert Nelson develops a concise and vital text for aircraft flight stability and control or flight dynamics courses.