Experimental aerodynamic characteristics for slender bodies with thin wings and tail at angles of attack from 0 ̊to 58 ̊and Mach from 0.6 to 2.0 PDF Download

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Experimental aerodynamic characteristics for slender bodies with thin wings and tail at angles of attack from 0 ̊to 58 ̊and Mach from 0.6 to 2.0

Experimental aerodynamic characteristics for slender bodies with thin wings and tail at angles of attack from 0 ̊to 58 ̊and Mach from 0.6 to 2.0 PDF Author: Leland H. Jorgensen
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 164

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Book Description

Experimental aerodynamic characteristics for slender bodies with thin wings and tail at angles of attack from 0 ̊to 58 ̊and Mach from 0.6 to 2.0

Experimental aerodynamic characteristics for slender bodies with thin wings and tail at angles of attack from 0 ̊to 58 ̊and Mach from 0.6 to 2.0 PDF Author: Leland H. Jorgensen
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 164

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Book Description

Experimental Aerodynamic Characteristics for Slender Bodies with Thin Wings and Tail at Angles of Attack from 0° to 58° and Mach Numbers from 0.6 to 2.0

Experimental Aerodynamic Characteristics for Slender Bodies with Thin Wings and Tail at Angles of Attack from 0° to 58° and Mach Numbers from 0.6 to 2.0 PDF Author: Leland Howard Jorgensen
Publisher:
ISBN:
Category :
Languages : en
Pages : 154

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Book Description

Experimental Aerodynamic Characteristics for Slender Bodies with Thin Wings at Angles of Attack from 0 ̊to 58 ̊and Mach Numbers from 0.6 to 2.0

Experimental Aerodynamic Characteristics for Slender Bodies with Thin Wings at Angles of Attack from 0 ̊to 58 ̊and Mach Numbers from 0.6 to 2.0 PDF Author: Leland Howard Jorgensen
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 132

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Book Description

Experimental Aerodynamic Characteristics for Slender Bodies with Thin Wings at Angles of Attack from 0° to 58° and Mach Numbers from 0.6 to 2.0

Experimental Aerodynamic Characteristics for Slender Bodies with Thin Wings at Angles of Attack from 0° to 58° and Mach Numbers from 0.6 to 2.0 PDF Author: Leland H. Jorgensen
Publisher:
ISBN:
Category :
Languages : en
Pages : 121

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Book Description

Experimental Aerodynamic Characteristics for Slender Bodies with Thin Wings and Tail at Angles of Attack from 0 ̊to 58 ̊and Mach from 0.6 to 2.0

Experimental Aerodynamic Characteristics for Slender Bodies with Thin Wings and Tail at Angles of Attack from 0 ̊to 58 ̊and Mach from 0.6 to 2.0 PDF Author: Leland H. Jorgensen
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 236

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Book Description

Scientific and Technical Aerospace Reports

Scientific and Technical Aerospace Reports PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 978

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Book Description

NASA Technical Memorandum

NASA Technical Memorandum PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 732

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Book Description

Static Aerodynamic Characteristics of a Series of Generalized Slender Bodies with and Without Fins at Mach Numbers Form 0.6 to 3.0 and Angles of Attack from 0 to 180 Deg

Static Aerodynamic Characteristics of a Series of Generalized Slender Bodies with and Without Fins at Mach Numbers Form 0.6 to 3.0 and Angles of Attack from 0 to 180 Deg PDF Author: William B. Baker (Jr.)
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 450

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Book Description

Monthly Catalog of United States Government Publications

Monthly Catalog of United States Government Publications PDF Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1194

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Book Description

Aerodynamic Configured Missile Development

Aerodynamic Configured Missile Development PDF Author: Robert J. Krieger
Publisher:
ISBN:
Category : Cruise missiles
Languages : en
Pages : 136

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Book Description
This report presents the results of a program that investigated aerodynamic configuring as a method of improving long range supersonic cruise and maneuvering missile performance. Non-circular body, lifting body, blended wing body, wing-body and favorable interference concepts were developed and wind tunnel tested. Substantial improvements in cruise range were shown to result from aero configuring.