Author: William T. Lauten
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 26
Get Book Here
Book Description
An analysis of the flight time-history records of a record-propelled 60 degree delta-wing airplane configuration indicate that wing flutter started during the accelerating portion of the flight at a Mach number of approximately 1.7 and continued through the peak Mach number of the test (M = 2.08) and during deceleration at least until telemeter failure at M = 1.4 and probably to an even lower speed. CW Doppler velocimeter data indicated that the wings did not fail during the flight.
Author: Joseph H. Judd
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 30
Get Book Here
Book Description
Author: Jr. William T. Lauten
Publisher:
ISBN:
Category :
Languages : en
Pages :
Get Book Here
Book Description
Author: William T. Jr Lauten
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
Get Book Here
Book Description
Author: William T. Lauten
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 21
Get Book Here
Book Description
An analysis of the flight time history of a rocket-propelled model of a 60 degrees delta-wing airplane configuration, fired for the purpose of obtaining zero-lift drag data, indicated wing flutter and subsequent failure at low-supersonic Mach numbers. This flutter occurred during the unpowered decelerating portion of the flight. The behavior of the model during flight is discussed and the mass and stiffness characteristics of a duplicate wing are presented.
Author: Joseph H. Judd
Publisher:
ISBN:
Category :
Languages : en
Pages : 14
Get Book Here
Book Description
Author: Charles Harold Wilts
Publisher:
ISBN:
Category : Aeroelasticity
Languages : en
Pages : 74
Get Book Here
Book Description
Author: OFFICE OF NAVAL RESEARCH WASHINGTON D C.
Publisher:
ISBN:
Category :
Languages : en
Pages : 746
Get Book Here
Book Description
Contents: Concepts for aeroelastic system approximations; static aerodynamics for flutter analyses; flutter at high mach numbers; an indicial flutter analysis for hypersonic delta wings; a theory for aeroelastic studies of delta lifting surfaces; flutter of flat panels in a low supersonic flow; flutter of rectangular panels; model flight testing on high-speed tracks; liquid behavior in rocket propellant tanks; dynamics of LP vehicles; aero-inertial control system; dynamic loads of missile configurations; wind loads on a vertically rising vehicle; random gust and taxi response calculations for delta wing aircraft; blast-loading on airfoils; stall buffeting loads; a method for analyzing heated wings; deformational response of heated wing structures; thermal stiffness; acoustic fatigue tests for elevated temperatures structural design; structural vibration in space vehicles; structural response in noise inputs; captive missile response to random pressures; structural response to the noise input of the Saturn engines; the environmental vibration problem.
Author: Norman D. Malmuth
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 66
Get Book Here
Book Description
For the case of very supersonic leading edges, the inviscid hypersonic flow over the windward side of a symmetrical flat-plate delta wing at incidence is analyzed. The limit selected is that the incidence is of higher order than the aspect ratio as the incidence tends to zero at infinite Mach number. In this framework, the flow regions consist of a two-dimensional domain adjacent to the leading edges and a central conefield. The flow quantities in the central region represent small linear, rotational perturbations about the zero sweep flow. A Riemann-Poincare boundary value problem for the pressure perturbation is formulated. An additional condition involving the sidewash at the shock is found to be required to resolve the indeterminacy of the foregoing boundary value problem. Series solutions and numerical results are presented for the shock shape and the pressure. The behavior of the latter quantity is found to be similar to that given by the irrotational linear solution for the supersonic leading edge case. Finally, the relationship between the present application and others involving diffraction problems and corner flows is indicated.
Author: John W. Paulson
Publisher:
ISBN:
Category :
Languages : en
Pages : 38
Get Book Here
Book Description
