Author: James H. Henderson
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 100
Book Description
Transonic wind tunnel tests were conducted on a body of revolution with various fin configurations to investigate jet plume effects on missile longitudinal stability. A series of cold air normal jets located downstream of the base were utilized to simulate the jet plume. Fins of various planform geometry were tested at a forward longitudinal location only. The angle of attack range was -4 to 11 degrees at Mach numbers of from 0.2 to 2.3. The test was run at the Arnold Engineering Development Center Transonic (16T) and Supersonic (16S) wind tunnels and was designated AEDC SF172/TF360. (Author).
Investigation of Jet Plume Effects on the Longitudinal Stability Characteristics of a Body of Revolution with Various Fin Configurations at Mach Numbers from 0.2 to 2.3
Author: James H. Henderson
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 100
Book Description
Transonic wind tunnel tests were conducted on a body of revolution with various fin configurations to investigate jet plume effects on missile longitudinal stability. A series of cold air normal jets located downstream of the base were utilized to simulate the jet plume. Fins of various planform geometry were tested at a forward longitudinal location only. The angle of attack range was -4 to 11 degrees at Mach numbers of from 0.2 to 2.3. The test was run at the Arnold Engineering Development Center Transonic (16T) and Supersonic (16S) wind tunnels and was designated AEDC SF172/TF360. (Author).
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 100
Book Description
Transonic wind tunnel tests were conducted on a body of revolution with various fin configurations to investigate jet plume effects on missile longitudinal stability. A series of cold air normal jets located downstream of the base were utilized to simulate the jet plume. Fins of various planform geometry were tested at a forward longitudinal location only. The angle of attack range was -4 to 11 degrees at Mach numbers of from 0.2 to 2.3. The test was run at the Arnold Engineering Development Center Transonic (16T) and Supersonic (16S) wind tunnels and was designated AEDC SF172/TF360. (Author).
Scientific and Technical Aerospace Reports
An Investigation of Jet Plume Effects on the Stability Characteristics of a Body of Revolution in Conjunction with Fins of Various Geometry and Longitudinal Positions at Transonic Speeds (sting-mounted Model with Normal Jet Plume Simulator)
Author: James H Henderson
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 356
Book Description
The main purpose of the report is to discuss some known available transonic flow approximate treatments and their applicabilities, including their limitations. This may suggest the possible future improvement of efforts in this renewed field. (Author).
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 356
Book Description
The main purpose of the report is to discuss some known available transonic flow approximate treatments and their applicabilities, including their limitations. This may suggest the possible future improvement of efforts in this renewed field. (Author).
Transonic Wind Tunnel Investigation of Thrust Effects on the Longitudinal Stability Characteristics of Several Body-fin Configurations
Author: James H. Henderson
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 872
Book Description
Transonic wind tunnel tests were conducted on a sting-mounted model to determine thrust effects on longitudinal stability characteristics of several body-fin combinations. The plume was simulated by cold air ejected from a series of sonic jets normal to the missile axis. One fin configuration was tested at several longitudinal positions. Adverse plume effects on stability were reduced by location of fins a distance forward of the base. The test was conducted at the Calspan Corporations' 8 foot Transonic Wind Tunnel at Mach numbers ranging from 0.4 to 1.25. Angles of attack ranged from -4 degrees to 12 degrees. Data were also obtained at roll angles of 22.5 degrees and 45 degrees for one configuration.
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 872
Book Description
Transonic wind tunnel tests were conducted on a sting-mounted model to determine thrust effects on longitudinal stability characteristics of several body-fin combinations. The plume was simulated by cold air ejected from a series of sonic jets normal to the missile axis. One fin configuration was tested at several longitudinal positions. Adverse plume effects on stability were reduced by location of fins a distance forward of the base. The test was conducted at the Calspan Corporations' 8 foot Transonic Wind Tunnel at Mach numbers ranging from 0.4 to 1.25. Angles of attack ranged from -4 degrees to 12 degrees. Data were also obtained at roll angles of 22.5 degrees and 45 degrees for one configuration.
Aeronautical Engineering
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 226
Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 226
Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).
NASA SP.
Government reports annual index
Some Effects of Fin Plan Form on the Static Stability of Fin-body Combinations at Mach Number 4.06
Author: Edward F. Ulmann
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28
Book Description