Author: J. C. Donaldson
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 212
Book Description
Exploratory static-stability tests were made on models of the MK-84 weapon and a modular weapon configuration during simulated weapon separation from the wing of the F-4C Tactical Fighter Aircraft at freestream Mach numbers 1.76, 2.0, and 2.5. Data were obtained with the parent aircraft at zero angle of attack and the weapon at the carriage incidence angle of -1 deg. Supplementary data were obtained for weapon angles of attack of + or - deg. Unit Reynolds number ranged from 4.6 million per ft at M free stream mach number = 1.76 to 6.2 million per ft at M free stream mach number = 2.5. Selected results are presented which show the effects on the weapon aerodynamic loads of free-stream Mach number, weapon angle of attack, weapon axial position, and the presence of other stores. Representative shadowgraph and schlieren photographs of the interference flow field are also presented. (Author).
Wind Tunnel Investigation of Aerodynamic Loads on Weapons Separated from Carriage Under the Wing of a Tactical Fighter Aircraft at Supersonic Speeds
Author: J. C. Donaldson
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 212
Book Description
Exploratory static-stability tests were made on models of the MK-84 weapon and a modular weapon configuration during simulated weapon separation from the wing of the F-4C Tactical Fighter Aircraft at freestream Mach numbers 1.76, 2.0, and 2.5. Data were obtained with the parent aircraft at zero angle of attack and the weapon at the carriage incidence angle of -1 deg. Supplementary data were obtained for weapon angles of attack of + or - deg. Unit Reynolds number ranged from 4.6 million per ft at M free stream mach number = 1.76 to 6.2 million per ft at M free stream mach number = 2.5. Selected results are presented which show the effects on the weapon aerodynamic loads of free-stream Mach number, weapon angle of attack, weapon axial position, and the presence of other stores. Representative shadowgraph and schlieren photographs of the interference flow field are also presented. (Author).
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 212
Book Description
Exploratory static-stability tests were made on models of the MK-84 weapon and a modular weapon configuration during simulated weapon separation from the wing of the F-4C Tactical Fighter Aircraft at freestream Mach numbers 1.76, 2.0, and 2.5. Data were obtained with the parent aircraft at zero angle of attack and the weapon at the carriage incidence angle of -1 deg. Supplementary data were obtained for weapon angles of attack of + or - deg. Unit Reynolds number ranged from 4.6 million per ft at M free stream mach number = 1.76 to 6.2 million per ft at M free stream mach number = 2.5. Selected results are presented which show the effects on the weapon aerodynamic loads of free-stream Mach number, weapon angle of attack, weapon axial position, and the presence of other stores. Representative shadowgraph and schlieren photographs of the interference flow field are also presented. (Author).
Wind Tunnel Investigation of Aerodynamic Loads on Weapons Separated from Carriage Under The Wing of a Tactical Fighter Aircraft at Supersonic Speeds
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Exploratory static-stability tests were made on models of the MK-84 weapon and a modular weapon configuration during simulated weapon separation from the wing of the F-4C Tactical Fighter Aircraft at freestream Mach numbers 1.76, 2.0, and 2.5. Data were obtained with the parent aircraft at zero angle of attack and the weapon at the carriage incidence angle of -1 deg. Supplementary data were obtained for weapon angles of attack of + or - deg. Unit Reynolds number ranged from 4.6 million per ft at M free stream mach number = 1.76 to 6.2 million per ft at M free stream mach number = 2.5. Selected results are presented which show the effects on the weapon aerodynamic loads of free-stream Mach number, weapon angle of attack, weapon axial position, and the presence of other stores. Representative shadowgraph and schlieren photographs of the interference flow field are also presented. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Exploratory static-stability tests were made on models of the MK-84 weapon and a modular weapon configuration during simulated weapon separation from the wing of the F-4C Tactical Fighter Aircraft at freestream Mach numbers 1.76, 2.0, and 2.5. Data were obtained with the parent aircraft at zero angle of attack and the weapon at the carriage incidence angle of -1 deg. Supplementary data were obtained for weapon angles of attack of + or - deg. Unit Reynolds number ranged from 4.6 million per ft at M free stream mach number = 1.76 to 6.2 million per ft at M free stream mach number = 2.5. Selected results are presented which show the effects on the weapon aerodynamic loads of free-stream Mach number, weapon angle of attack, weapon axial position, and the presence of other stores. Representative shadowgraph and schlieren photographs of the interference flow field are also presented. (Author).
Wind Tunnel Investigation of Aerodynamic Loads on Weapons Separated from Carriage Under The Wing of a Tactical Fighter Aircraft at Supersonic Speeds
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Exploratory static-stability tests were made on models of the MK-84 weapon and a modular weapon configuration during simulated weapon separation from the wing of the F-4C Tactical Fighter Aircraft at freestream Mach numbers 1.76, 2.0, and 2.5. Data were obtained with the parent aircraft at zero angle of attack and the weapon at the carriage incidence angle of -1 deg. Supplementary data were obtained for weapon angles of attack of + or - deg. Unit Reynolds number ranged from 4.6 million per ft at M free stream mach number = 1.76 to 6.2 million per ft at M free stream mach number = 2.5. Selected results are presented which show the effects on the weapon aerodynamic loads of free-stream Mach number, weapon angle of attack, weapon axial position, and the presence of other stores. Representative shadowgraph and schlieren photographs of the interference flow field are also presented. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Exploratory static-stability tests were made on models of the MK-84 weapon and a modular weapon configuration during simulated weapon separation from the wing of the F-4C Tactical Fighter Aircraft at freestream Mach numbers 1.76, 2.0, and 2.5. Data were obtained with the parent aircraft at zero angle of attack and the weapon at the carriage incidence angle of -1 deg. Supplementary data were obtained for weapon angles of attack of + or - deg. Unit Reynolds number ranged from 4.6 million per ft at M free stream mach number = 1.76 to 6.2 million per ft at M free stream mach number = 2.5. Selected results are presented which show the effects on the weapon aerodynamic loads of free-stream Mach number, weapon angle of attack, weapon axial position, and the presence of other stores. Representative shadowgraph and schlieren photographs of the interference flow field are also presented. (Author).
External Store Airloads Prediction Technique
Author: A. R. Rudnicki (Jr.)
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 170
Book Description
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 170
Book Description
Documentation of a Transonic Wind Tunnel Test to Investigate the Separation Characteriscis of the GBU-10C/B, the CBU-58, and the BL-755 Stores from the F-16 Aircraft
Author: J. M. Wright
Publisher:
ISBN:
Category : Airplanes, Military
Languages : en
Pages : 126
Book Description
Publisher:
ISBN:
Category : Airplanes, Military
Languages : en
Pages : 126
Book Description
Wind Tunnel Investigation of a Supersonic Fan-in-fuselage VTOL Fighter Model at Zero and Low Forward Speeds
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 52
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 52
Book Description
NASA SP.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 544
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 544
Book Description
Wind Tunnel Investigation of the Interaction and Breakdown Characteristics of Slender-wing Vortices at Subsonic, Transonic, and Supersonic Speeds
Author: Gary E. Erickson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 234
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 234
Book Description
Wind Tunnel Investigation at Supersonic Speeds of the Lift, Drag, Static-Stability and Control Characteristics of a 0.03-Scale Model of an Interim Development Version of the B-70 Airplane
Author: James C. Daugherty
Publisher:
ISBN:
Category :
Languages : en
Pages : 310
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 310
Book Description
Technical Abstract Bulletin
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 156
Book Description
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 156
Book Description