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 Download
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Author: Dennis E. Fuller
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 64
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Book Description
Author: Dennis E. Fuller
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 64
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Book Description
Author: Dennis E. Fuller
Publisher:
ISBN:
Category :
Languages : en
Pages : 51
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Author: Clarence A. Brown
Publisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 86
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Author: CLARENCE A. JR. BROWN
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
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An investigation was conducted in the Langley Unitary Plan wind tunnel to determine the effects of fin cant and size on the static aerodynamic characteristics of a 0.081-scale model of a three-stage and a two-stage Trailblazer II configuration. Tests were performed at Mach numbers from 1.47 to 4.63 and at a Reynolds number per foot of 3.0 x 10 to the 6th power. he angleof-attack range varied from approximately -5 to 5 degrees and angle of sideslip varied from approximately -4 to 4 degrees. All first-stage fins tested gave adequate static stability when the center-of-gravity travel of the flight model was taken into account. The presence of the auxiliary rocket motors in the lateral plane decreased the effectiveness of the fins in the pitch plane at the lower Mach number and increased the fin effectiveness at the higher Mach numbers. Removal of the auxiliary rocket motors from the first stage of the two-stage configuration reduced the axial force about 25% at the low Mach numbers and about 15% at the high Mach numbers. (Author).
Author: Joseph A. Yuska
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 20
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The longitudinal static stability characteristics of three one-fifth scale models of the second stage of a sounding rocket were calculated and compared with the measured values at Mach numbers of 1.79 to 3.47. All three models had fins of trapezoidal planform with sweptback leading and trailing edges, small aspect ratio, and thick wedge sections, but differed in fin area and overall model length. Calculation of center of pressure and normal-force coefficient slope at zero normal force were in good agreement with experimental data.
Author: John T. Suttles
Publisher:
ISBN:
Category : Noses (Space vehicles)
Languages : en
Pages : 70
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Author: William F. Hinson
Publisher:
ISBN:
Category : Pitching (Aerodynamics)
Languages : en
Pages : 52
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Aerodynamic characteristics in pitch of scale model of two and three stage rocket configuration at Mach numbers of 0.4 to 4.63.
Author: Ross B. Robinson
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 38
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Author: Clyde Hayes
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
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Author: William J. Monta
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
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