Results 191 to 200 of about 2,387,085 (259)
Some of the next articles are maybe not open access.

Blunt-Body Heat Transfer at Hypersonic Speed and Low Reynolds Numbers

, 1961
with the computed value given by the analysis of Fay and Riddell using the actual measured pressure gradient which, in turn, agrees with the modified Newtonian formula; therefore, the analytical results are made nondimensional with respect to the value ...
A. Ferri
semanticscholar   +1 more source

On the Flow Past a Sphere at Hypersonic Speed with a Magnetic Field

, 1959
Heat Transfer and Recovery Factor in a Laminar Boundary Layer With Arbitrary Pressure Gradient and Wall Temperature Distribution BERNARD L E F U R 682 An Alternative Formulation of the Problem of Flutter in Real Fluids. W E N H W A C H U AND H.
N. C. Freeman
semanticscholar   +1 more source

Unsteady Boundary‐Layer Induced Pressures at Hypersonic Speed

, 1971
The first‐order transient contribution to the strong‐interaction induced pressure has been obtained for a suddenly accelerated semi‐infinite flat plate moving at hypersonic speed and zero angle of attack. The unsteady compressible laminar two‐dimensional
R. Gupta, C. M. Rodkiewicz
semanticscholar   +1 more source

Terminal Adaptive Guidance for Autonomous Hypersonic Strike Weapons via Reinforcement Learning

Journal of Spacecraft and Rockets, 2021
An adaptive guidance system suitable for the terminal phase trajectory of a hypersonic strike weapon is optimized using reinforcement meta learning. The guidance system maps observations directly to commanded bank angle, angle of attack, and sideslip ...
B. Gaudet, R. Furfaro
semanticscholar   +1 more source

High Speed and Hypersonic Science and Technology

41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2005
Throughout modern history, aviation and, most recently, space have been pivotal to this nation’s ability to defend freedom and democracy. Over the years our foundational science and technology efforts have focused upon building strong aeronautics and space capability independently.
Ronald Sega   +2 more
openaire   +2 more sources

Incipient separation on flared bodies at hypersonic speeds

The Aeronautical Journal, 1999
AbstractThe aerodynamic effectiveness of a cylinder-flare body at zero incidence under laminar and turbulent boundary-layer conditions has been studied experimentally. Two nose geometries, namely a 10° half-angle sharp cone and a hemisphere, were used.
Kontis, Konstantinos, Stollery, JL
openaire   +3 more sources

Simulation of an orbiter separation maneuver at hypersonic speed [PDF]

open access: possible10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference, 2001
The separation maneuver of an idealized twostage hypersonic vehicle is aerodynamical ly investigated. This paper gives a contribution to the calculation of unsteady flowfields arising from a realistic separation maneuver. The aerodynamic calculations are based on a finite-volume-method for solutions of the two-dimensional unsteady Eulerand Navier ...
Thomas Cvrlje, Boris Laschka
openaire   +1 more source

Technology Development for High Speed/Hypersonic Applications

AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference, 2005
The United States Air Force (USAF) and National Aeronautics and Space Administration (NASA) have jointly sponsored a study of technology development requirements for high speed/hypersonic airbreathing systems in preparation for initiating a National Aerospace Initiative (NAI) program.
Brian Zuchowski   +3 more
openaire   +2 more sources

Control effectiveness of a jet-slender body combination at hypersonic speeds

14th Applied Aerodynamics Conference, 1996
The effects of jet control on the aerodynamic characteristics, performance, and stability of a 5-deg semiangle slender conemissilecone guration arestudied. Tests were made in theCrane eld University College of Aeronautics hypersonicgun tunnelusingboth sharp and blunted cones. Thestudywasconducted at a Mach number of 8.2and a Reynolds number of 392 700,
Kontis, Konstantinos, Stollery, JL
openaire   +6 more sources

Pitch-damping coefficients at hypersonic speeds.

AIAA Journal, 1968
Equation (A6) may be recognized as the Mathieu equation; two of the zones of parametric resonance determined by this equation are shown in Fig. 6 (zones A and B in the figure). Such zones define regions where the solutions of Eq. (A6) exhibit an exponential growth of the form e^. The iso-ju lines shown in the figure connect points of equal growth rate,
openaire   +2 more sources

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