Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 24
Book Description
Static Longitudinal Aerodynamic Characteristics of a Right Triangular Pyramidal Lifting Reentry Configuration at Mach Numbers of 3.00, 4.50, and 6.00 for Angles of Attack Up to 56 Deg
Author: Static Longitudinal and Lateral Stability Control Characteristics of a Right Triangular Pyramidal Lifting Reentry Configuration at Mach Numbers from 2.36 to 4.65
Author: Aerodynamic Characteristics at Low Speed of a Reentry Configuration Having Rigid Retractable Conical Lifting Surfaces
Author: Paul G. FournierPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 30
Book Description
Aerodynamic Characteristics at Mach Numbers from 1.50 to 4.63 of a Variable-geometry Lifting Reentry Concept Employing Elevator and Body Base Flaps for Control
Author: Roger H. FournierPublisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 76
Book Description
An investigation of a lifting body configuration has been conducted in the Langley Unitary Plan wind tunnel through a Mach number range from 1.50 to 4.63 to determine the control effectiveness characteristics of body base flaps with and without anhedral tail elevator controls.
THE LONGITUDINAL AERODYNAMIC CHARACTERISTICS OF A RE-ENTRY CONFIGURATION BASED ON A BLUNT 13 DEG HALF-CONE AT MACH NUMBERS TO 0.92
Author: Aerodynamic Characteristics of Three Axismmetric Low-fitness-ratio Reentry Shapes at Mach 6.9
Author: Jim A. PenlandPublisher:
ISBN:
Category : Flight control
Languages : en
Pages : 44
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.
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Author: 
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