RTO WG 10: Test Cases for CFD Validation of Hypersonic Flight PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download RTO WG 10: Test Cases for CFD Validation of Hypersonic Flight PDF full book. Access full book title RTO WG 10: Test Cases for CFD Validation of Hypersonic Flight by . Download full books in PDF and EPUB format.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 25
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 25
Get Book Here
Book Description
Author: American Institute of Aeronautics and Astronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 960
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Thermodynamics
Languages : en
Pages : 504
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 778
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 17
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 692
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 46
Get Book Here
Book Description
Between 1997 and 1999, a Working Group on the feasibility of collaborative, multi-facility windtunnel testing for the validation of Computational Fluid Dynamics Codes (CFD) has established the following results: Wintunnel tests are the main source of CFD validation but all have specific bias errors. Testing of the same model in several facilities can better establish the level of uncertainty in windtunnel tests and hence help assess possible differences between CFD and windtunnel tests. The Working Group, after an initial inquiry, established the need for CFD validation for fighter aircraft, transport type aircraft, missiles and helicopters. Effort and cost can be controlled efficiently and would permit the improvement of CFD Codes for considerable cost saving in future developments.
Author:
Publisher:
ISBN:
Category : Air-supported structures
Languages : en
Pages : 24
Get Book Here
Book Description
A small-scale, instrumented research aircraft was flown to investigate the flight characteristics of inflatable wings. Ground tests measured the static structural characteristics of the wing at different inflation pressures, and these results compared favorably with analytical predictions. A research-quality instrumentation system was assembled, largely from commercial off-the-shelf components, and installed in the aircraft. Initial flight operations were conducted with a conventional rigid wing having the same dimensions as the inflatable wing. Subsequent flights were conducted with the inflatable wing. Research maneuvers were executed to identify the trim, aerodynamic performance, and longitudinal stability and control characteristics of the vehicle in its different wing configurations. For the angle-of-attack range spanned in this flight program.
Author: Symposium on Fluid Dynamics Problems of Vehicles Operating Near or in the Air-Sea Interface
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 386
Get Book Here
Book Description
Author: Ernst Heinrich Hirschel
Publisher: Springer Science & Business Media
ISBN: 3540265198
Category : Technology & Engineering
Languages : en
Pages : 419
Get Book Here
Book Description
The last two decades have brought two important developments for aeroth- modynamics. One is that airbreathing hypersonic flight became the topic of technology programmes and extended system studies. The other is the emergence and maturing of the discrete numerical methods of aerodyn- ics/aerothermodynamics complementary to the ground-simulation facilities, with the parallel enormous growth of computer power. Airbreathing hypersonic flight vehicles are, in contrast to aeroassisted re-entry vehicles, drag sensitive. They have, further, highly integrated lift and propulsion systems. This means that viscous eflFects, like boundary-layer development, laminar-turbulent transition, to a certain degree also strong interaction phenomena, are much more important for such vehicles than for re-entry vehicles. This holds also for the thermal state of the surface and thermal surface effects, concerning viscous and thermo-chemical phenomena (more important for re-entry vehicles) at and near the wall. The discrete numerical methods of aerodynamics/aerothermodynamics permit now - what was twenty years ago not imaginable - the simulation of high speed flows past real flight vehicle configurations with thermo-chemical and viscous effects, the description of the latter being still handicapped by in sufficient flow-physics models. The benefits of numerical simulation for flight vehicle design are enormous: much improved aerodynamic shape definition and optimization, provision of accurate and reliable aerodynamic data, and highly accurate determination of thermal and mechanical loads. Truly mul- disciplinary design and optimization methods regarding the layout of thermal protection systems, all kinds of aero-servoelasticity problems of the airframe, et cetera, begin now to emerge.
