Zobrazeno 1 - 10
of 22
pro vyhledávání: '"T. Alan Egolf"'
Autor:
James D. Baeder, Lakshmi N. Sankar, Ritu Marpu, Mark Wasikowski, Stephen M. Makinen, T. Alan Egolf
Publikováno v:
Journal of Aircraft. 51:377-389
A hybrid Navier–Stokes free-wake computational-fluid-dynamics methodology, coupled with a multibody dynamics analysis code, has been applied to the UH-60A rotor to study the loads developed during a severe diving turn maneuver (flight counter 11680
Publikováno v:
54th AIAA Aerospace Sciences Meeting.
Publikováno v:
53rd AIAA Aerospace Sciences Meeting.
A hybrid Navier-Stokes/Free Wake methodology is applied to helicopter rotors in hover. Three tip planforms were analyzed: the S-76 rotor with a swept tip, a rectangular planform, and a swept tip with anhedral. The solidity of the three rotors was mat
Publikováno v:
53rd AIAA Aerospace Sciences Meeting.
Good hover performance is a very important rotorcraft design criteria, but despite advancements in the ability to predict and preserve the tip vortex, the limiting aspect of accurate hover performance prediction, the capability to consistently and re
Autor:
T. Alan Egolf, Edward Reed
Publikováno v:
53rd AIAA Aerospace Sciences Meeting.
An evaluation of the computational toolset HPCMP CREATE-AV Helios, a multidisciplinary set of tools developed by the DOD for rotorcraft analysis and design, was performed by application to the coaxial X2 TechnologyDemonstrator aircraft. The principle
Publikováno v:
52nd Aerospace Sciences Meeting.
Publikováno v:
52nd Aerospace Sciences Meeting.
The AIAA Applied Aerodynamics Technical Committee’s Rotorcraft Simulation Working Group put together standardized evaluation of the S-76 planform in hover. The objective of this paper was to construct a hybrid analysis framework for the baseline S-
Publikováno v:
51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition.
Publikováno v:
50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition.
Multi-scale modeling of synthetic jet devices is em ployed to investigate the effect of active flow control (AFC) on fuselage drag reduction. The flow field in the vicinity of the synthetic jet devices was modeled using a Lattice Boltzmann equation (