Author: Macon C. Ellis
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 104
Book Description
An investigation at Mach number 1.92 in the Langley 9-inch supersonic tunnel of a variable body-wing-tail configuration has been made in order to determine and to isolate the aerodynamic effects on each other of the components of the configuration.
Aerodynamic Investigation at Mach Number 1.92 of a Rectangular Wing and Tail and Body Configuration and Its Components
Author: Macon C. Ellis
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 104
Book Description
An investigation at Mach number 1.92 in the Langley 9-inch supersonic tunnel of a variable body-wing-tail configuration has been made in order to determine and to isolate the aerodynamic effects on each other of the components of the configuration.
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 104
Book Description
An investigation at Mach number 1.92 in the Langley 9-inch supersonic tunnel of a variable body-wing-tail configuration has been made in order to determine and to isolate the aerodynamic effects on each other of the components of the configuration.
A Flight Investigation of the Transonic Area Rule for a 52.5© Sweptback Wind-body Configuration at Mach Numbers Between 0.8 and 1.6
Author: Sherwood Hoffman
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 30
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 30
Book Description
An Experimental Investigation at a Mach Number of 2.01 of the Effects of Body Cross-section Shape on the Aerodynamic Characteristics of Bodies and Wing-body Combinations
Author: Harry W. Carlson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
Book Description
Abstract: An experimental investigation has been performed to determine the effect of changes in body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations. A series of 13 bodies having a given length and given longitudinal distribution of cross-sectional area but various cross-section shapes were tested at a Mach number of 2.01. The bodies were tested alone and in combination with a 47° sweptback wing having a 6-percent-thick hexagonal section.
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
Book Description
Abstract: An experimental investigation has been performed to determine the effect of changes in body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations. A series of 13 bodies having a given length and given longitudinal distribution of cross-sectional area but various cross-section shapes were tested at a Mach number of 2.01. The bodies were tested alone and in combination with a 47° sweptback wing having a 6-percent-thick hexagonal section.
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 and Tail Location on the Aerodynamic Characteristics of an Airplane for Mach Numbers from 0. 25 To 4. 63
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781725184299
Category :
Languages : en
Pages : 34
Book Description
Experimental investigations have been conducted to determine the effect of wing vertical position and horizontal-tail vertical and axial position on the static aerodynamic characteristics of a wing-body horizontal-tail configuration. The configurations investigated included the wing in a high, mid, or low position on the body with the horizontal tail in each of these vertical positions as well as in three axial positions. The closest position of the horizontal tail to the wing essentially provided on all-wing configuration. In addition, tests were made for the three wing positions with the horizontal tail removed. The tests were made in three different wind tunnels to provide data for a Mach number range from 0.25 to 4.63. The purpose of the investigation was to illustrate the strong effects of interference flow fields as a function of geometry and flight regime. An analysis of the results indicate some arrangements that might lead to aerodynamic problems and others in which the interference flow fields might be favorably exploited. The results suggest that a coplanar concept with a translating horizontal tail could potentially minimize the aerodynamic changes with Mach number and provide more optimum performance over the Mach number range. Spearman, M. L. Langley Research Center NASA-TM-84643, NAS 1.15:84643 RTOP 505-43-43-01...
Publisher: Createspace Independent Publishing Platform
ISBN: 9781725184299
Category :
Languages : en
Pages : 34
Book Description
Experimental investigations have been conducted to determine the effect of wing vertical position and horizontal-tail vertical and axial position on the static aerodynamic characteristics of a wing-body horizontal-tail configuration. The configurations investigated included the wing in a high, mid, or low position on the body with the horizontal tail in each of these vertical positions as well as in three axial positions. The closest position of the horizontal tail to the wing essentially provided on all-wing configuration. In addition, tests were made for the three wing positions with the horizontal tail removed. The tests were made in three different wind tunnels to provide data for a Mach number range from 0.25 to 4.63. The purpose of the investigation was to illustrate the strong effects of interference flow fields as a function of geometry and flight regime. An analysis of the results indicate some arrangements that might lead to aerodynamic problems and others in which the interference flow fields might be favorably exploited. The results suggest that a coplanar concept with a translating horizontal tail could potentially minimize the aerodynamic changes with Mach number and provide more optimum performance over the Mach number range. Spearman, M. L. Langley Research Center NASA-TM-84643, NAS 1.15:84643 RTOP 505-43-43-01...
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. Fournier
Publisher:
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.
Publisher:
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.
Experimental Pressure Distributions Over Two Wing-body Combinations at Mach Number 1.9
Author: Barry Moskowitz
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 40
Book Description
Abstract: Pressure distributions on two wing-body combinations were obtained at Mach number of 1.9 to investigate wing-body interference. A rectangular wing, a triangular wing, and a cylindrical body having an ogive nose were investigated alone and in combination. Pressure distributions over the wing body combination compared favorable with theoretical calculations based primarily on a generalization of the method of Nielsen and Matteson, except at the root section of wings where boundary layer of body modified the flow.
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 40
Book Description
Abstract: Pressure distributions on two wing-body combinations were obtained at Mach number of 1.9 to investigate wing-body interference. A rectangular wing, a triangular wing, and a cylindrical body having an ogive nose were investigated alone and in combination. Pressure distributions over the wing body combination compared favorable with theoretical calculations based primarily on a generalization of the method of Nielsen and Matteson, except at the root section of wings where boundary layer of body modified the flow.
Longitudinal Aerodynamic Characteristics at Mach Numbers from 0.50 to 1.19 of a Supersonic Transport Model with a Modified M Wing
Longitudinal Aerodynamic Characteristics at Mach Number 2.02 of a Series of Wing-body Configurations Employing a Cambered and Twisted Arrow Wing
The Flow Past a Straight- and a Swept-wing-body Combination and Their Equivalent Bodies of Revolution at Mach Numbers Near 1.0
Author: W. F. Lindsey
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 24
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.
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 24
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.