Free-flight Investigation at Mach Numbers Between 0.5 and 1.7 of the Zero-lift Rolling Effectiveness and Drag of Various Surface, Spoiler, and Jet Controls on an 80° Delta-wing Missile PDF Download
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Author: Eugene D. Schult
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 52
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Book Description
Author: Eugene D. Schult
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 52
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Book Description
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 500
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 860
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 218
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Book Description
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category :
Languages : en
Pages : 208
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Book Description
Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 2106
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Book Description
February issue includes Appendix entitled Directory of United States Government periodicals and subscription publications; September issue includes List of depository libraries; June and December issues include semiannual index.
Author: Joseph Adams Shortal
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 808
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Book Description
Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 540
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 494
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Book Description
Author: Eugene D. Schult
Publisher:
ISBN:
Category : Fins (Anatomy)
Languages : en
Pages : 32
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Book Description
This paper discusses the rolling effectiveness of deflected fins, flaps, spoilers, and jet devices which may be employed on fin-stabilized vehicles. The possible applications and some of the significant factors affecting the performance of each device are described. The experimental information has been published previously and was obtained chiefly from free-flight tests of fin-stabilized vehicles at Mach numbers up to approximately 2.0. Comparisons are made in some cases with existing theory, which is also relied upon to indicate trends where data are not available.
