Static Aerodynamic Characteristics of a Two-stage and a Three-stage Rocket Vehicle at Mach Numbers from 1.47 to 4.63 PDF Download

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Static Aerodynamic Characteristics of a Two-stage and a Three-stage Rocket Vehicle at Mach Numbers from 1.47 to 4.63

Static Aerodynamic Characteristics of a Two-stage and a Three-stage Rocket Vehicle at Mach Numbers from 1.47 to 4.63 PDF Author: Clarence A. Brown
Publisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 86

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Book Description

Static Aerodynamic Characteristics of a Two-stage and a Three-stage Rocket Vehicle at Mach Numbers from 1.47 to 4.63

Static Aerodynamic Characteristics of a Two-stage and a Three-stage Rocket Vehicle at Mach Numbers from 1.47 to 4.63 PDF Author: Clarence A. Brown
Publisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 86

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Book Description

Static Aerodynamic Characteristics of Three Rocket-vehicle Configurations at Mach Numbers from 1.80 to 4.63 Including Some Effects of Fin Size, Fin Cant, and Auxiliary Rocket Motors

Static Aerodynamic Characteristics of Three Rocket-vehicle Configurations at Mach Numbers from 1.80 to 4.63 Including Some Effects of Fin Size, Fin Cant, and Auxiliary Rocket Motors PDF Author: Dennis E. Fuller
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 64

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Book Description

Aerodynamic Characteristics in Pitch of a 1/7-scale Model of a Two- and Three-stage Rocket Configuration at Mach Numbers of 0.4 to 4.63

Aerodynamic Characteristics in Pitch of a 1/7-scale Model of a Two- and Three-stage Rocket Configuration at Mach Numbers of 0.4 to 4.63 PDF Author: William F. Hinson
Publisher:
ISBN:
Category : Pitching (Aerodynamics)
Languages : en
Pages : 52

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Book Description
Aerodynamic characteristics in pitch of scale model of two and three stage rocket configuration at Mach numbers of 0.4 to 4.63.

Scientific and Technical Aerospace Reports

Scientific and Technical Aerospace Reports PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1492

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Book Description

Technical Abstract Bulletin

Technical Abstract Bulletin PDF Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 812

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Supersonic Aerodynamic Characteristics of a 1/6-scale Model of the Final Two Stages of the Argo D-4 Four-stage Rocket Vehicle

Supersonic Aerodynamic Characteristics of a 1/6-scale Model of the Final Two Stages of the Argo D-4 Four-stage Rocket Vehicle PDF Author: Clyde Hayes
Publisher:
ISBN:
Category :
Languages : en
Pages : 28

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Aerodynamic Loading Characteristics of a 1/10-scale Model of the Three-stage Scout Vehicle at Mach Numbers 1.57 to 4.65

Aerodynamic Loading Characteristics of a 1/10-scale Model of the Three-stage Scout Vehicle at Mach Numbers 1.57 to 4.65 PDF Author: Lloyd S. Jernell
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 52

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Book Description

Investigation of the Aerodynamic Characteristics of Two Preliminary Designs of Scout Research Vehicle at Mach Numbers from 1.77 to 4.65

Investigation of the Aerodynamic Characteristics of Two Preliminary Designs of Scout Research Vehicle at Mach Numbers from 1.77 to 4.65 PDF Author: Robert J. Keynton
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 64

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Book Description

Wind-tunnel Investigation at Mach Numbers from 0.30 to 1.20 of the Static Aerodynamic Characteristics of a Two-stage Saturn Launch Vehicle

Wind-tunnel Investigation at Mach Numbers from 0.30 to 1.20 of the Static Aerodynamic Characteristics of a Two-stage Saturn Launch Vehicle PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 36

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Aerodynamic Loading Characteristics at Mach Numbers from 0.80 to 1.20 of a 1/10-scale Three-stage Scout Model

Aerodynamic Loading Characteristics at Mach Numbers from 0.80 to 1.20 of a 1/10-scale Three-stage Scout Model PDF Author: Thomas C. Kelly
Publisher:
ISBN:
Category : Launch vehicles (Astronautics)
Languages : en
Pages : 68

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Book Description
Aerodynamic loads results have been obtained in the Langley 8-foot transonic pressure tunnel at Mach numbers from 0.80 to 1.20 for a 1/10-scale model of the upper three stages of the Scout vehicle. Tests were conducted through an angle-of-attack range from -8° to 8° at an average test Reynolds number per foot of about 4.0 x 106. Results indicated that the peak negative pressures associated with expansion corners at the nose and transition flare exhibit sizeable variations which occur over a relatively small Mach number range. The magnitude of the variations may cause the critical local loading condition for the full-scale vehicle to occur at a Mach number considerably lower than that at which the maximum dynamic pressure occurs in flight. The addition of protuberances simulating antennas and wiring conduits had slight, localized effects. The lift carryover from the nose and transition flare on the cylindrical portions of the model generally increased with an increase in Mach number.