Effect of Body-mounted Lateral Controls and Speed Brakes on the Aerodynamic Load Distribution Over a 45 Degree Swept Wing at Mach Numbers from 0.80 to 0.98 PDF Download

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Effect of Body-mounted Lateral Controls and Speed Brakes on the Aerodynamic Load Distribution Over a 45 Degree Swept Wing at Mach Numbers from 0.80 to 0.98

Effect of Body-mounted Lateral Controls and Speed Brakes on the Aerodynamic Load Distribution Over a 45 Degree Swept Wing at Mach Numbers from 0.80 to 0.98 PDF Author: F. E. West
Publisher:
ISBN:
Category :
Languages : en
Pages : 76

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Book Description

Effect of Body-mounted Lateral Controls and Speed Brakes on the Aerodynamic Load Distribution Over a 45 Degree Swept Wing at Mach Numbers from 0.80 to 0.98

Effect of Body-mounted Lateral Controls and Speed Brakes on the Aerodynamic Load Distribution Over a 45 Degree Swept Wing at Mach Numbers from 0.80 to 0.98 PDF Author: F. E. West
Publisher:
ISBN:
Category :
Languages : en
Pages : 76

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Book Description

Effect of Body-mounted Lateral Controls and Speed Brakes on the Aerodynamic Load Distribution Over a 45 Degree Swept Wing at Mach Numbers from 0.80 to 0.98

Effect of Body-mounted Lateral Controls and Speed Brakes on the Aerodynamic Load Distribution Over a 45 Degree Swept Wing at Mach Numbers from 0.80 to 0.98 PDF Author: F. E. West
Publisher:
ISBN:
Category :
Languages : en
Pages : 0

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Book Description

Effect of Body-Mounted Lateral Controls and Speed Brakes on the Aerodynamic Load Distribution Over a 45 Deg Swept Wing at Mach Numbers from 0.80 to 0.98

Effect of Body-Mounted Lateral Controls and Speed Brakes on the Aerodynamic Load Distribution Over a 45 Deg Swept Wing at Mach Numbers from 0.80 to 0.98 PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 80

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Book Description

Effect of Body-mounted Lateral Controls and Speed Brakes on the Aerodynamic Load Distribution Over a 45° Swept Wing at Mach Numbers from 0.80 to 0.98

Effect of Body-mounted Lateral Controls and Speed Brakes on the Aerodynamic Load Distribution Over a 45° Swept Wing at Mach Numbers from 0.80 to 0.98 PDF Author: F. E. West
Publisher:
ISBN:
Category :
Languages : en
Pages : 72

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Book Description

Force Tests Results for Body-mounted Lateral Controls and Speed Brakes on a 45 Degree Swept-wing Model at Mach Numbers from 0.80 to 0.98

Force Tests Results for Body-mounted Lateral Controls and Speed Brakes on a 45 Degree Swept-wing Model at Mach Numbers from 0.80 to 0.98 PDF Author: F. E. West
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32

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Book Description
An investigation has been made in the Langley 16-foot transonic tunnel to determine the aerodynamic characteristics of several body-mounted lateral-control and speed-brake configurations. The basic model had a 45 degree swept wing with an aspect ratio of 3. Six-component balance data were obtained at Mach numbers of 0.80, 0.94, and 0.98 for angles of attack that usually ranged from about zero to 21 degrees.

Force Test Results for Body-mounted Lateral Controls and Speed Brakes on a 45° Swept-wing Model at Mach Numbers from 0.80 to 0.98

Force Test Results for Body-mounted Lateral Controls and Speed Brakes on a 45° Swept-wing Model at Mach Numbers from 0.80 to 0.98 PDF Author: F. E. West
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 32

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Book Description

The Effects of Mass Distribution on the Low-speed Dynamic Lateral Stability and Control Characteristics of a Model with a 45° Sweptback Wing

The Effects of Mass Distribution on the Low-speed Dynamic Lateral Stability and Control Characteristics of a Model with a 45° Sweptback Wing PDF Author: Donald E. Hewes
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36

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Book Description
The trends in lateral stability and control produced variations of the mass distribution were determined for a model with a 45 degree sweptback wing. Calculations were made to correlate the trends determined by theory with those determined from tests of a free-flying dynamic model in the Langley free-flight tunnel.

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

Stability and Control Characteristics at Mach Numbers of 2.50, 3.00, and 3.71 of a Variable- Wing-sweep Configuration with Outboard Wing Panels Swept Back 75°

Stability and Control Characteristics at Mach Numbers of 2.50, 3.00, and 3.71 of a Variable- Wing-sweep Configuration with Outboard Wing Panels Swept Back 75° PDF Author: Gerald V. Foster
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 38

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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.