Transonic Wind Tunnel Investigation of Thrust Effects on the Longitudinal Stability Characteristics of Several Body-fin Configurations PDF Download
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Author: James H. Henderson
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 872
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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.
Author: James H. Henderson
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 872
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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.
Author: James H. Henderson
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 100
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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).
Author: George Batiuk
Publisher:
ISBN:
Category : Guided missiles
Languages : en
Pages : 194
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Book Description
This report summarizes the studies made to date by the Army Missile Command on the effects of the rocket jet plume on the Stability characteristics of a body of revolution with various fin configurations and at various fin positions on the body. The Mach numbers ranged from 0.2 to 2.3. A normal jet plume simulator was used to obtain the desired plume effects. This report concerns itself with those tests conducted on a 5-in. diameter, 52-in. long model, with a 3 caliber tangent ogive nose.
Author: James H Henderson
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 356
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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).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
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Book Description
Author: James H Henderson
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 148
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Book Description
Experimental aerodynamic investigations were conducted at the AEDC 16-foot Transonic Wind Tunnel to determine longitudinal stability characteristics of a long slender rocket configuration with simulated jet plume. The effect of jet plume on rocket aerodynamics is given over an angle of attack range from -11 to 11 degrees at Mach numbers from 0.2 to 1.5. Plume simulator chamber pressure varied from 0 to 600 psia. Individual cruciform fin aerodynamic loads are also shown over the same ranges. (Author).
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1274
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1338
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Book Description
Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1284
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Book Description
Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : United States
Languages : en
Pages : 1250
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Book Description
