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Multi-objective optimization of supersonic-supersonic ejector
High Power Laser and Particle Beams, 2012For supersonic-supersonic ejector, the design model and corresponding analysis were presented, and the relation of design parameters and the performance was partly revealed. The results revealed the confliction of two performance objectives and the complexity of the design problem.
陈钦 Chen Qin +3 more
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Journal of Spacecraft and Rockets, 1971
An analytical method is presented for the design of axisymmetric annular nozzles to yield uniform and axial flow. Computed results are used to display typical matched inner and outer contours, the effects of major initial flow variables, and the resulting wall forces.
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An analytical method is presented for the design of axisymmetric annular nozzles to yield uniform and axial flow. Computed results are used to display typical matched inner and outer contours, the effects of major initial flow variables, and the resulting wall forces.
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Journal of the Aerospace Sciences, 1960
An approximation of the differential equation for compressible duct flow is presented. The equation is linear and of the second order. The duct transfer function and response characteristics are obtained by applying small-perturbation theory to the differential equation.
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An approximation of the differential equation for compressible duct flow is presented. The equation is linear and of the second order. The duct transfer function and response characteristics are obtained by applying small-perturbation theory to the differential equation.
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Journal of Engineering for Power, 1964
The design of supersonic turbine nozzles and rotors is discussed and a series of four supersonic turbine nozzles, which is believed to be of a new type, was built and tested. The ratio A/A* between the outlet flow area and the throat area varied between 3.64 and 1.
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The design of supersonic turbine nozzles and rotors is discussed and a series of four supersonic turbine nozzles, which is believed to be of a new type, was built and tested. The ratio A/A* between the outlet flow area and the throat area varied between 3.64 and 1.
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ACM SIGGRAPH 2010 Computer Animation Festival, 2010
The NVIDIA Supersonic Sled is a full physics simulation of a mechanical assembly subjected to heavy loads. Using PhysX, CUDA, and DirectX 11, this demonstration uses real-time simulation and graphics techniques to produce a realistic and exhilarating experience of driving a powerful machine on the edge of control.
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The NVIDIA Supersonic Sled is a full physics simulation of a mechanical assembly subjected to heavy loads. Using PhysX, CUDA, and DirectX 11, this demonstration uses real-time simulation and graphics techniques to produce a realistic and exhilarating experience of driving a powerful machine on the edge of control.
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The Journal of the Royal Aeronautical Society, 1951
A start is made by considering why the subsonic propeller was abandoned when aircraft speeds approached the shock stall. It is true that the shock stall also occurs on the propeller blades under these conditions, causing a loss of lift and an increase of drag, but this is not the predominant effect which produces the marked decrease of propeller ...
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A start is made by considering why the subsonic propeller was abandoned when aircraft speeds approached the shock stall. It is true that the shock stall also occurs on the propeller blades under these conditions, causing a loss of lift and an increase of drag, but this is not the predominant effect which produces the marked decrease of propeller ...
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The Physics Teacher, 2012
On October 14,2012, Felix Baumgartner, an Austrian sky-diver, set some new world records for his discipline. Jumping from a height of about 39 km, he reached a top speed of 1342 km/h, becoming the first human being to break the sound barrier in free fall.
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On October 14,2012, Felix Baumgartner, an Austrian sky-diver, set some new world records for his discipline. Jumping from a height of about 39 km, he reached a top speed of 1342 km/h, becoming the first human being to break the sound barrier in free fall.
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Aeronautical Quarterly, 1956
SummaryThe non-linear theory of supersonic bangs, obtained in Part 1 for a body accelerating along a straight path, is extended to include curved paths. The basic theory remains the same. The important parameter, which appears in the theory, is the acceleration component along the ray, the rays being lines drawn from points on the flight path at an ...
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SummaryThe non-linear theory of supersonic bangs, obtained in Part 1 for a body accelerating along a straight path, is extended to include curved paths. The basic theory remains the same. The important parameter, which appears in the theory, is the acceleration component along the ray, the rays being lines drawn from points on the flight path at an ...
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