Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 50
Book Description
Supersonic Aerodynamic Characteristics of a Space Shutter Orbiter Model at Angles of Attack from 20 Deg to 90 Deg
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 50
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 50
Book Description
Supersonic longitudinal aerodynamic characteristics of two space shuttle orbiter configurations
Author: James C. Ellison
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 34
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 34
Book Description
Supersonic Longitudinal Aerodynamic Characteristics of Two Space Shuttle Orbiter Configurations. [conducted in the Langley Unitary Plan Wind Tunnel]
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781724991676
Category :
Languages : en
Pages : 34
Book Description
An investigation was conducted to determine the supersonic longitudinal aerodynamic characteristics of 0.015 scale models of the Rockwell International 089B and 139B space shuttle orbiter configurations and the 139B orbiter with a modifier forebody. The models each had a 45 deg swept delta wing that was blended into the body with an 81 deg swept fillet to form a double delta planform. The vertical tail had a split rudder deflected 27.5 deg on each side to form a speed brake. Tests were conducted at Mach numbers of 2.5, 3.9, and 4.6 at a Reynolds number, based on the body length of the 089B model, of 4,150,000. Angles of attack varied from -4 deg to 44 deg at 0 deg sideslip. Ellison, J. C. Langley Research Center NASA-TM-74074, L-11787 RTOP 506-26-30-04...
Publisher: Createspace Independent Publishing Platform
ISBN: 9781724991676
Category :
Languages : en
Pages : 34
Book Description
An investigation was conducted to determine the supersonic longitudinal aerodynamic characteristics of 0.015 scale models of the Rockwell International 089B and 139B space shuttle orbiter configurations and the 139B orbiter with a modifier forebody. The models each had a 45 deg swept delta wing that was blended into the body with an 81 deg swept fillet to form a double delta planform. The vertical tail had a split rudder deflected 27.5 deg on each side to form a speed brake. Tests were conducted at Mach numbers of 2.5, 3.9, and 4.6 at a Reynolds number, based on the body length of the 089B model, of 4,150,000. Angles of attack varied from -4 deg to 44 deg at 0 deg sideslip. Ellison, J. C. Langley Research Center NASA-TM-74074, L-11787 RTOP 506-26-30-04...
Aerodynamic Characteristics of the 140A/B Space Shuttle Orbiter at Mach 10.3
Author: Peter T. Bernot
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 52
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 52
Book Description
Interference Effects of Aft Reaction-control Yaw Jets on the Aerodynamic Characteristics of a Space Shuttle Orbiter Model at Supersonic Speeds
Author: Peter F. Covell
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 58
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 58
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 376
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 376
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Influence of Configuration Details on the Subsonic Characteristics of a Space Shuttle Orbiter Design
Author: John P. Decker
Publisher:
ISBN:
Category : Space shuttles
Languages : en
Pages : 40
Book Description
Publisher:
ISBN:
Category : Space shuttles
Languages : en
Pages : 40
Book Description
Supersonic Aerodynamic Characteristics of Some Reentry Concepts for Angles of Attack to 90 Deg
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Supersonic Aerodynamic Characteristics of a Low-Drag Aircraft Configuration Having an Arrow Wing of Aspect Ratio 1.86 and a Body of Fineness Ratio 20
Author:
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 80
Book Description
A free-flight rocket-propelled-model investigation was conducted at Mach numbers of 1.2 to 1.9 to determine the longitudinal and lateral aero-dynamic characteristics of a low-drag aircraft configuration. The model consisted of an aspect-ratio -1.86 arrow wing with 67.5 deg. leading-edge sweep and NACA 65A004 airfoil section and a triangular vertical tail with 60 deg. sweep and NACA 65A003 section in combination with a body of fineness ratio 20. Aerodynamic data in pitch, yaw, and roll were obtained from transient motions induced by small pulse rockets firing at intervals in the pitch and yaw directions. From the results of this brief aerodynamic investigation, it is observed that very slender body shapes can provide increased volumetric capacity with little or no increase in zero-lift drag and that body fineness ratios of the order of 20 should be considered in the design of long-range supersonic aircraft. The zero-lift drag and the drag-due-to-lift parameter of the test configuration varied linearly with Mach number. The maximum lift-drag ratio was 7.0 at a Mach number of 1.25 and decreased slightly to a value of 6.6 at a Mach number of 1.81. The optimum lift coefficient, normal-force-curve slope, lateral-force-curve slope, static stability in pitch and yaw, time to damp to one-half amplitude in pitch and yaw, the sum of the rotary damping derivatives in pitch and also in yaw, and the static rolling derivatives all decreased with an increase in Mach number. Values of certain rolling derivatives were obtained by application of the least-squares method to the differential equation of rolling motion. A comparison of the experimental and calculated total rolling-moment-coefficient variation during transient oscillations of the model indicated good agreement when the damping-in-roll contribution was included with the static rolling-moment terms.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 80
Book Description
A free-flight rocket-propelled-model investigation was conducted at Mach numbers of 1.2 to 1.9 to determine the longitudinal and lateral aero-dynamic characteristics of a low-drag aircraft configuration. The model consisted of an aspect-ratio -1.86 arrow wing with 67.5 deg. leading-edge sweep and NACA 65A004 airfoil section and a triangular vertical tail with 60 deg. sweep and NACA 65A003 section in combination with a body of fineness ratio 20. Aerodynamic data in pitch, yaw, and roll were obtained from transient motions induced by small pulse rockets firing at intervals in the pitch and yaw directions. From the results of this brief aerodynamic investigation, it is observed that very slender body shapes can provide increased volumetric capacity with little or no increase in zero-lift drag and that body fineness ratios of the order of 20 should be considered in the design of long-range supersonic aircraft. The zero-lift drag and the drag-due-to-lift parameter of the test configuration varied linearly with Mach number. The maximum lift-drag ratio was 7.0 at a Mach number of 1.25 and decreased slightly to a value of 6.6 at a Mach number of 1.81. The optimum lift coefficient, normal-force-curve slope, lateral-force-curve slope, static stability in pitch and yaw, time to damp to one-half amplitude in pitch and yaw, the sum of the rotary damping derivatives in pitch and also in yaw, and the static rolling derivatives all decreased with an increase in Mach number. Values of certain rolling derivatives were obtained by application of the least-squares method to the differential equation of rolling motion. A comparison of the experimental and calculated total rolling-moment-coefficient variation during transient oscillations of the model indicated good agreement when the damping-in-roll contribution was included with the static rolling-moment terms.
Supersonic Aerodynamic Characteristics of a Saturn IB Launch Vehicle Model with Third-stage Modifications
Author: Roger H. Fournier
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
Book Description