Author: Jesse L. MitchellPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 32
Book Description
The Static and Dynamic Longitudinal Stability Characteristics of Some Supersonic Aircraft Configurations
Author: Jesse L. MitchellPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 32
Book Description
Some Effects of Aircraft Configuration on Static Longitudinal and Directional Stability Characteristics at Supersonic Mach Numbers Below 3
Author: M. Leroy SpearmanPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 22
Book Description
Some Factors Affecting the Static Longitudinal and Directional Stability Characteristics of Supersonic Aircraft Configurations
Author: M. Leroy SpearmanPublisher:
ISBN:
Category :
Languages : en
Pages : 41
Book Description
Some Effects of Aircraft Configuration on Static Longitudinal and Directional Stability Characteristics at Supersonic Mach Numbers Below 3
Author: M. Leroy SpearmanPublisher:
ISBN:
Category :
Languages : en
Pages : 15
Book Description
Supersonic Aerodynamic Characteristics of a Low-Drag Aircraft Configuration Having an Arrow Wing of Aspect Ratio 1.86 and a Body of Fineness Ratio 20
Author: Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 80
Book Description
A free-flight rocket-propelled-model investigation was conducted at Mach numbers of 1.2 to 1.9 to determine the longitudinal and lateral aero-dynamic characteristics of a low-drag aircraft configuration. The model consisted of an aspect-ratio -1.86 arrow wing with 67.5 deg. leading-edge sweep and NACA 65A004 airfoil section and a triangular vertical tail with 60 deg. sweep and NACA 65A003 section in combination with a body of fineness ratio 20. Aerodynamic data in pitch, yaw, and roll were obtained from transient motions induced by small pulse rockets firing at intervals in the pitch and yaw directions. From the results of this brief aerodynamic investigation, it is observed that very slender body shapes can provide increased volumetric capacity with little or no increase in zero-lift drag and that body fineness ratios of the order of 20 should be considered in the design of long-range supersonic aircraft. The zero-lift drag and the drag-due-to-lift parameter of the test configuration varied linearly with Mach number. The maximum lift-drag ratio was 7.0 at a Mach number of 1.25 and decreased slightly to a value of 6.6 at a Mach number of 1.81. The optimum lift coefficient, normal-force-curve slope, lateral-force-curve slope, static stability in pitch and yaw, time to damp to one-half amplitude in pitch and yaw, the sum of the rotary damping derivatives in pitch and also in yaw, and the static rolling derivatives all decreased with an increase in Mach number. Values of certain rolling derivatives were obtained by application of the least-squares method to the differential equation of rolling motion. A comparison of the experimental and calculated total rolling-moment-coefficient variation during transient oscillations of the model indicated good agreement when the damping-in-roll contribution was included with the static rolling-moment terms.
Introduction to Aircraft Flight Mechanics
Author: Thomas R. YechoutPublisher: AIAA
ISBN: 9781600860782
Category : Aerodynamics
Languages : en
Pages : 666
Book Description
Based on a 15-year successful approach to teaching aircraft flight mechanics at the US Air Force Academy, this text explains the concepts and derivations of equations for aircraft flight mechanics. It covers aircraft performance, static stability, aircraft dynamics stability and feedback control.
Control of Supersonic Aircraft
Author: Feliko Iosifovich SklianskiiPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 402
Book Description
Contents: General information, equations of motion, definitions; Stability and controllability characteristics of aircraft, formation of forces on control levers of aircraft with non-power-assisted (boosterless) control systems; Change of characteristics of stability and controllability of aircraft at transonic and supersonic speeds of flight; Improvement of stability and controllability characteristics by methods of aerodynamic design and selection of shapes of supersonic aircraft; Power control formation of forces on aircraft control levers with power control; Application of automatic devices for improvement of characteristics of dynamic stability and controllability of present-day aircraft; Certain questions of the further development of control systems; The influence of deformation of the aircraft structure on its stability and controllability; Increase of safety of flight and emergency control.
Low-speed Static and Dynamic Force Tests of a Generic Supersonic Cruise Fighter Configuration
Author: David Edgar HahnePublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 40
Book Description
Index of NACA Technical Publications
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
Book Description
Low-speed Longitudinal Stability Characteristics of a Supersonic Transport Configuration with Variable-sweep Wings Employing a Double Inboard Pivot
Author: William P. HendersonPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 56
Book Description
