Wind-tunnel Investigation at Mach Numbers from 1.90 to 2.86 of a Canard-controlled Missile with Ram-air-jet Spoiler Roll Control PDF Download

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Wind-tunnel Investigation at Mach Numbers from 1.90 to 2.86 of a Canard-controlled Missile with Ram-air-jet Spoiler Roll Control

Wind-tunnel Investigation at Mach Numbers from 1.90 to 2.86 of a Canard-controlled Missile with Ram-air-jet Spoiler Roll Control PDF Author: A. B. Blair
Publisher:
ISBN:
Category :
Languages : en
Pages : 106

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Book Description

Wind-tunnel Investigation at Mach Numbers from 1.90 to 2.86 of a Canard-controlled Missile with Ram-air-jet Spoiler Roll Control

Wind-tunnel Investigation at Mach Numbers from 1.90 to 2.86 of a Canard-controlled Missile with Ram-air-jet Spoiler Roll Control PDF Author: A. B. Blair
Publisher:
ISBN:
Category :
Languages : en
Pages : 106

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Book Description

Wind-tunnel Investigation at Mach Numbers of 1.5 and 2.0 of a Canard Missile Configuration

Wind-tunnel Investigation at Mach Numbers of 1.5 and 2.0 of a Canard Missile Configuration PDF Author: J. Richard Spahr
Publisher:
ISBN:
Category :
Languages : en
Pages : 47

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Book Description

Longitudinal Stability and Control Characteristics of a Canard Missile Configuration for Mach Numbers from 1.1 to 1.93 as Determined from Free-flight and Wind-tunnel Investigations

Longitudinal Stability and Control Characteristics of a Canard Missile Configuration for Mach Numbers from 1.1 to 1.93 as Determined from Free-flight and Wind-tunnel Investigations PDF Author: Howard J. Jr Curfman
Publisher:
ISBN:
Category :
Languages : en
Pages : 28

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Book Description

Wind-tunnel Investigations at Mach Numbers from 1.90 to 2.86 of a Canard-controlled Missile with Ram-air-jet Spoiler Roll Control

Wind-tunnel Investigations at Mach Numbers from 1.90 to 2.86 of a Canard-controlled Missile with Ram-air-jet Spoiler Roll Control PDF Author: A. B. Blair
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 101

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Book Description

Wind-tunnel Investigation at Mach Numbers from 3.0 to 6.8 of the Static Aerodynamic Characteristics of Modified Mercury Exit and Escape Capsule Configurations

Wind-tunnel Investigation at Mach Numbers from 3.0 to 6.8 of the Static Aerodynamic Characteristics of Modified Mercury Exit and Escape Capsule Configurations PDF Author: Albin O. Pearson
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 26

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Book Description

Wind-tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls

Wind-tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls PDF Author: Ross B. Robinson
Publisher:
ISBN:
Category :
Languages : en
Pages : 34

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Book Description

Wind-tunnel Investigation at Mach Numbers from 0.30 to 1.14 of the Static Aerodynamic Characteristics of Modified Mercury Escape and Exit Capsule Configurations

Wind-tunnel Investigation at Mach Numbers from 0.30 to 1.14 of the Static Aerodynamic Characteristics of Modified Mercury Escape and Exit Capsule Configurations PDF Author: Albin O. Pearson
Publisher:
ISBN:
Category : Noses (Space vehicles)
Languages : en
Pages : 40

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Book Description

Investigation of a Canard Missile Configuration (NACA RM-4) in the Langley 9-inch Supersonic Tunnel at Mach Numbers of 1.62 and 1.93

Investigation of a Canard Missile Configuration (NACA RM-4) in the Langley 9-inch Supersonic Tunnel at Mach Numbers of 1.62 and 1.93 PDF Author: Carl E. Grigsby
Publisher:
ISBN:
Category :
Languages : en
Pages : 24

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An Experimental Investigation of the Aerodynamic Characteristics of Nose Mounted Canard Configurations at Supersonic Mach Numbers (1.5 Through 4.5)

An Experimental Investigation of the Aerodynamic Characteristics of Nose Mounted Canard Configurations at Supersonic Mach Numbers (1.5 Through 4.5) PDF Author: James R Burt (Jr.)
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 352

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Book Description
Experimental aerodynamic investigations were conducted in a supersonic wind tunnel to determine the aerodynamic characteristics of several nose mounted canard wing configurations. Canard position, geometry, angular orientation, and model nose shape were varied systematically to determine their effects on model aerodynamics. The model was tested at angles of attack of -5 to 13 degrees and Mach numbers of 1.5 to 4.5. Aerodynamic loads were measured separately on four canards and tail panels, and the total model. The vapor screen method was used to trace the paths of the vortices shed from the canards. Roll control effectiveness of canards, both with a planar tail and a ring tail was investigated.

Monthly Catalog of United States Government Publications

Monthly Catalog of United States Government Publications PDF Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 792

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Book Description