Rocket-model Investigation of Longitudinal Stability and Drag Characteristics of an Airplane Configuration Have a 60© Delta Wing and a High Unwept Horizontal Tail PDF Download

Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Rocket-model Investigation of Longitudinal Stability and Drag Characteristics of an Airplane Configuration Have a 60© Delta Wing and a High Unwept Horizontal Tail PDF full book. Access full book title Rocket-model Investigation of Longitudinal Stability and Drag Characteristics of an Airplane Configuration Have a 60© Delta Wing and a High Unwept Horizontal Tail by Robert F. Peck. Download full books in PDF and EPUB format.

Rocket-model Investigation of Longitudinal Stability and Drag Characteristics of an Airplane Configuration Have a 60© Delta Wing and a High Unwept Horizontal Tail

Rocket-model Investigation of Longitudinal Stability and Drag Characteristics of an Airplane Configuration Have a 60© Delta Wing and a High Unwept Horizontal Tail PDF Author: Robert F. Peck
Publisher:
ISBN:
Category : Delta wing airplanes
Languages : en
Pages : 32

Get Book Here

Book Description

Flight Determination of the Drag and Longitudinal Stability and Control Characteristics of a Rocket-powered Model of a 60 Degrees Delta-wing Airplane from Mach Numbers of 0.75 to 1.70

Flight Determination of the Drag and Longitudinal Stability and Control Characteristics of a Rocket-powered Model of a 60 Degrees Delta-wing Airplane from Mach Numbers of 0.75 to 1.70 PDF Author: Grady L. Mitcham
Publisher:
ISBN:
Category :
Languages : en
Pages : 44

Get Book Here

Book Description

Rocket-model Investigation of Longitudinal Stability and Drag Characteristics of an Airplane Configuration Have a 60© Delta Wing and a High Unwept Horizontal Tail

Rocket-model Investigation of Longitudinal Stability and Drag Characteristics of an Airplane Configuration Have a 60© Delta Wing and a High Unwept Horizontal Tail PDF Author: Robert F. Peck
Publisher:
ISBN:
Category : Delta wing airplanes
Languages : en
Pages : 32

Get Book Here

Book Description

Longitudinal Stability and Drag Characteristics at Mach Numbers from 0.75 to 1.5 of an Airplane Configuration Having a 60 Degrees Swept Wing of Aspect Ratio 2.24 as Obtained from Rocket-propelled Model

Longitudinal Stability and Drag Characteristics at Mach Numbers from 0.75 to 1.5 of an Airplane Configuration Having a 60 Degrees Swept Wing of Aspect Ratio 2.24 as Obtained from Rocket-propelled Model PDF Author: A. James Vitale
Publisher:
ISBN:
Category :
Languages : en
Pages : 43

Get Book Here

Book Description

Effect of External Stores on the Stability and Control Characteristics of a Delta Wing Fighter Model at Mach Numbers from 0.60 to 2.01

Effect of External Stores on the Stability and Control Characteristics of a Delta Wing Fighter Model at Mach Numbers from 0.60 to 2.01 PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 40

Get Book Here

Book Description

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

Get Book Here

Book Description

Results of Flight Tests to Determine the Zero-lift Drag Characteristics of a 60 Degree Delta Wing with NACA 65-006 Airfoil Section and Various Double-wedge Sections at Mach Numbers from 0.7 to 1.6

Results of Flight Tests to Determine the Zero-lift Drag Characteristics of a 60 Degree Delta Wing with NACA 65-006 Airfoil Section and Various Double-wedge Sections at Mach Numbers from 0.7 to 1.6 PDF Author: Clement J. Welsh
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 15

Get Book Here

Book Description
Results of an exploratory free-flight investigation at zero-lift of several rocket-powered drag research models equipped with 60 degree swept-back delta wings are presented for a Mach number range from about 0.70 to 1.60. The airfoil sections tested included the NACA 65-006 and a series of double-wedge sections with various thicknesses and positions of maximum thickness.

The Aerodynamic Characteristics of Several Thick Delta Wings at Mach Numbers to 6 and Angles of Attack 50°

The Aerodynamic Characteristics of Several Thick Delta Wings at Mach Numbers to 6 and Angles of Attack 50° PDF Author: John B. McDevitt
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 114

Get Book Here

Book Description

Rocket-model Investigation of Longitudinal Stability and Drag Characteristics of an Airplane Configuration Having a 60 Degree Delta Wing and a High Unswept Horizontal Tail

Rocket-model Investigation of Longitudinal Stability and Drag Characteristics of an Airplane Configuration Having a 60 Degree Delta Wing and a High Unswept Horizontal Tail PDF Author: Robert F. Peck
Publisher:
ISBN:
Category :
Languages : en
Pages : 28

Get Book Here

Book Description

Importants manuscrits et documents relatifs à la Bastille et au Faubourg Saint-Antoine

Importants manuscrits et documents relatifs à la Bastille et au Faubourg Saint-Antoine PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 28

Get Book Here

Book Description

Effects of Wing Position and Vertical-tail Configuration on Stability and Control Characteristics of a Jet-powered Delta-wing Vertically Rising Airplane Model

Effects of Wing Position and Vertical-tail Configuration on Stability and Control Characteristics of a Jet-powered Delta-wing Vertically Rising Airplane Model PDF Author: Powell M. Lovell
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 42

Get Book Here

Book Description
An investigation has been conducted to determine the effects of wing position and vertical tail configuration on the stability and control characteristics of a jet-powered delta-wing vertically rising airplane model. A ducted-fan powerplant was used because there was no hot-jet powerplant of sufficiently small size and adequate reliability available. In addition to conventional flap-type control surfaces on the wings and vertical tails, the model had jet-reaction controls provided by movable eyelids at the rear of the tail pipe and by air bled from the main duct and exhausted through movable nozzles near the wing tips. The investigation consisted of flight and force tests of three model configurations: a high wing with a top-mounted vertical tail, a high wing with top- and bottom-mounted vertical tails, and a low wing with the top-mounted vertical tail. The flight tests, which were made in the Langley full-scale tunnel, represented slow constant-altitude transitions from hovering to normal unstalled forward flight.