Author: Leslie F. Lawrence
Publisher:
ISBN:
Category :
Languages : en
Pages : 56
Book Description
Wind-tunnel Investigation of a Tailless Triangular-wing Fighter Aircraft at Mach Numbers from 0.5 to 1.5
Index of NACA Technical Publications
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
Book Description
Wind-Tunnel Investigation at a Mach Number of 1.53 of an Airplane with a Triangular Wing
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).
Research Abstracts and Reclassification Notice
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 508
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 508
Book Description
Index of NASA Technical Publications
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 448
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 448
Book Description
A Selected Listing of NASA Scientific and Technical Reports for ...
Large-scale Wind-tunnel Investigation of a Model with an External Jet-augmented Flap
Author: Jerry V. Kirk
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 44
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 44
Book Description
Scientific and Technical Aerospace Reports
Supercritical Maneuvering Fighter Configuration
Author: Michael J. Mann
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 80
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 80
Book Description