Results 251 to 260 of about 365,625 (308)

Large Angle of Attack Wheel Climb

Volume 7B: 9th International Conference on Multibody Systems, Nonlinear Dynamics, and Control, 2013
It is shown in this paper that wheel climb can be initiated as the result of kinematic conditions that can be described using algebraic equations that do not depend explicitly on time. These algebraic kinematic conditions can lead to instantaneous wheel climb that is independent of the motion history.
Ahmed A. Shabana, James J. O’Shea
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Missile Loads at High Angles of Attack

Journal of Spacecraft and Rockets, 1991
study, side forces were presented for various conditions over a range of angles of attack up to 90 deg. Presented here is a comparison of the experimental data with Missile DATCOM predictions for the normal forces.
Richard M. Howard, Archibald S. Dunn
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High angle of attack hypersonic aerodynamics

5th Applied Aerodynamics Conference, 1987
A new aerodynamics force model is presented which is based on modified Newtonian theory and empirical correlations. The algebraic model was developed for complete vehicles from take off to orbital speeds and for large angles of attack. Predictions are compared to results for a wind tunnel model at a Mach number of 20, and the full scale Shuttle Orbiter
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An optical angle of attack sensor

International Congress on Instrumentation in Aerospace Simulation Facilitie, 1990
A major source of transonic and supersonic wind-tunnel test data uncertainty are angle-of-attack-measurement errors caused by unknown sting and balance deflections under load. Since dynamic loads in pressurized or cryogenic wind tunnels generally exceed those in conventional low-speed atmospheric wind tunnels, the need to account for these distortions ...
T.K. McDevitt, F.K. Owen
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Angle of Attack Indicator

Aircraft Engineering and Aerospace Technology, 1960
THE main criterion for controlling the flight path of an aircraft should, of course, be the angle of attack. However, it is only recently that instruments have become available which could provide pilots with continuous angle of attack information. The demand for an instrument which could provide this information accurately has now been met by the ...
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Angle of attack guidance via robust approximate inversion

Guidance, Navigation, and Control Conference and Exhibit, 1998
A guidance law based on estimated angle of attack is presented. The basic structure of the proposed method uses proportional navigation to generate angle of attack commands to the autopilot. The guidance allows for variable speed, and incorporates turn rate directly in order to take advantage of agility and maneuverability requirements.
INNOCENTI, MARIO, NASUTI F, CARNASCIALI G.   +2 more
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Turbulent flow over vehicles at angle of attack

20th Aerospace Sciences Meeting, 1982
I recent years the parabolized Navier-Stokes (PNS) equations have frequently been used to calculate steady viscous supersonic flows about a variety of three-dimensional geometries at angle of attack. Some results have also been obtained for turbulent flows where an algebraic turbulent eddy-viscosity model has been incorporated in the PNS equations ...
W. S. Helliwell, I. E. Alber, R. P. Dickinson, S. C. Lubard   +3 more
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Angle-of-attack control of spinning missiles

Mechanics and Control of Flight Conference, 1974
The application of controlled wind-fixed pitch and yaw moments to control the coning angle of a spinning missile is described. The open-loop response to applied pitch and yaw moments is derived, and the closed-loop behavior of an angle-of-attack control system is analyzed.
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High Angle-of-Attack Aerodynamics

Annual Review of Fluid Mechanics, 1995
High angle-of-attack (high-IX) aerodynamics has been a key element in airplane design beginning with the first attempts at unpowered manned flight using gliders in the 1 800s and extending to the present day with civil and military airplanes. High-IX aerodynamics is commonly perceived as arising on an airplane at a physically large angle of attack with
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Effect of Angle of Attack on Hypersonic

AIAA Journal, 1997
An experimental investigation of the effects of angle of attack on hypersonic boundary-layer stability on a ared-cone model was conducted in the low-disturbance Mach-6 Nozzle-Test-Chamber Facility at NASA Langley Research Center. Hot-wire anemometry diagnostics were applied to identify the boundary-layer instability mechanisms that lead to transition.
Glen P. Doggett, Ndaona Chokani, Stephen P. Wilkinson   +2 more
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