Effect of Fin-flare Combinations on the Aerodynamic Characteristics of a Body at Mach Numbers 1.61 and 2.20 PDF Download

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Effect of Fin-flare Combinations on the Aerodynamic Characteristics of a Body at Mach Numbers 1.61 and 2.20

Effect of Fin-flare Combinations on the Aerodynamic Characteristics of a Body at Mach Numbers 1.61 and 2.20 PDF Author: Clyde Hayes
Publisher:
ISBN:
Category : Lift (Aerodynamics)
Languages : en
Pages : 44

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Effect of Fin-flare Combinations on the Aerodynamic Characteristics of a Body at Mach Numbers 1.61 and 2.20

Effect of Fin-flare Combinations on the Aerodynamic Characteristics of a Body at Mach Numbers 1.61 and 2.20 PDF Author: Clyde Hayes
Publisher:
ISBN:
Category : Lift (Aerodynamics)
Languages : en
Pages : 44

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Book Description

Effect Opf Fin-flare Combinations on the Aerodynamic Characteristics of a Body at Mach Numbers 1.61 and 2.20

Effect Opf Fin-flare Combinations on the Aerodynamic Characteristics of a Body at Mach Numbers 1.61 and 2.20 PDF Author: Clyde Hayes
Publisher:
ISBN:
Category :
Languages : en
Pages : 38

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Book Description

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

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 PDF Author: Ross B. Robinson
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 42

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Book Description

Some Effects of Fin Plan Form on the Static Stability of Fin-body Combinations at Mach Number 4.06

Some Effects of Fin Plan Form on the Static Stability of Fin-body Combinations at Mach Number 4.06 PDF Author: Edward F. Ulmann
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28

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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

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 PDF Author: Roger H. Fournier
Publisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 76

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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.

A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0

A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0 PDF Author: Robert S. Osborne
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 20

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Book Description

A Transonic Investigation of Changing Indentation Design Mach Number on the Aerodynamic Characteristics of a 45 Degree Sweptback-wing-body Combination Designed for High Performance

A Transonic Investigation of Changing Indentation Design Mach Number on the Aerodynamic Characteristics of a 45 Degree Sweptback-wing-body Combination Designed for High Performance PDF Author: Donald L. Loving
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 92

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Book Description

Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 3.96 and 4.63

Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 3.96 and 4.63 PDF Author: Maurice O. Feryn
Publisher:
ISBN:
Category :
Languages : en
Pages : 36

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Book Description

The Flow Past a Straight- and a Swept-wing-body Combination and Their Equivalent Bodies of Revolution at Mach Numbers Near 1.0

The Flow Past a Straight- and a Swept-wing-body Combination and Their Equivalent Bodies of Revolution at Mach Numbers Near 1.0 PDF Author: W. F. Lindsey
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 24

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Book Description
Abstract: The complete flow fields past a straight and a swept wing-body combination and their equivalent bodies of revolution at Mach numbers around 1.0 have been observed by means of motion-picture schlieren photography. The results of these observations indicate that the shock growth and positions on the wing-body combinations are closely reproduced in the flow past their respective equivalent bodies.

Normal Force on Fin-Flare Combinations at Mach Numbers from 1.1 to 4.5

Normal Force on Fin-Flare Combinations at Mach Numbers from 1.1 to 4.5 PDF Author: James Robert Burt (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 25

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Book Description
A study of normal force on several slender fin-flare combinations is presented. The configurations were tested at Mach numbers of 1.1, 1.2, 1.3, 1.4, 1.5, 1.75, 2.5, 3.5, and 4.5. Angle of attack was carried from about -6.5 to 8.5 degrees. The effects due to varying Mach number on total model normal force and normal force due to the fins plus fin-body flow field interference are shown. Estimates of normal force of the fins plus fin-body interference are made from linearized small perturbation theory and compared to the test results. (Author).