Results 241 to 250 of about 82,587 (286)
Investigation of the leeward side of a delta wing at hypersonic speeds [PDF]
Fluid and Plasma Dynamics Conference, 1968 A series of experiments were performed at Mm — 10 using a delta wing with sharp leading edges swept to 75°. Surface oil-flow measurements and impact pressure data were acquired in the lee-side region. Analysis of the results led to a description of the principal features of the flowfield.
W. L. Hankey, E. J. Cross
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On the optimum cruise speed of a hypersonic aircraft
IEEE Aerospace and Electronic Systems Magazine, 1989Some preliminary results that have been obtained in the frame of the SANGER system studies are presented. SANGER is a West German study project and technology reference system for a future advanced space transportation system. The first stage of this vehicle is a hypersonic aircraft from which a passenger version could be derived. The analyses indicate
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Pitch-damping coefficients at hypersonic speeds.
AIAA Journal, 1968Equation (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,
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Base Flow of Circular Cylinder at Hypersonic Speeds
AIAA Journal, 2016The paper presents a computational and an experimental investigation of base flow of a circular cylinder at hypersonic speeds. Effects of chemistry and wall temperature on the flow in the base region, at low to high enthalpies, are discussed. The experiments were conducted in a shock tunnel at a nominal Mach number of 10.
Andrew J. Neely +2 more
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THE SUBLIMATION OF GRAPHITE AT HYPERSONIC SPEEDS [PDF]
Entry Technology Conference, 1964 S.M. Scala, L.M. Gilbert
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Drag reduction on a spiked body at hypersonic speed
The Aeronautical Journal, 2010AbstractFitting a spike on a blunt body provides a drag reduction at supersonic and hypersonic speeds. In this study, the laminar flow over a spiked, conical body terminated by a spherical cap, inspired by the Apollo re-entry capsule design, was investigated using a hypersonic wind tunnel.
J. L. Stollery, G. d’Humières
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Boundary layer transition on swept cylinders at hypersonic speeds
Fluid Dynamics Conference, 1995We present boundary-layer transition data on swept cylinders in hypersonic flow that were obtained in the hypersonic Ludwieg-tube wind tunnel of DLR. Experiments were conducted at M∞ = 5.0 and 6.9 for three swept cylinders with and without end plates and sweep angles of 30, 45, and 60 deg, respectively.
Akira Murakami +2 more
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Aerothermodynamic analysis of projectiles at hypersonic speeds [PDF]
7th Applied Aerodynamics Conference, 1989 Klaus A. Hoffmann +2 more
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Toward High Speed: Supersonic and Hypersonic Flight
1991Just like that of trains and automobiles, the speed of aircraft has increased with time. Indeed, aircraft have raced ahead to make the most substantial progress in the shortest time. This is shown in Figure 10.1, where an exponential increase of cruising speed with time up to about 1960 is apparent.
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Aerodynamics of delta wings with flaps at hypersonic speeds
The Aeronautical Journal, 2002AbstractControl surface effectiveness is an important parameter for any aeroplane. For a hypersonic aircraft, though the power required to operate the flaps is determined by low speed flying conditions, it is imperative to know the effect of flaps at hypersonic speeds. Hence, studies have been done on this topic by aerodynamicists for over 40 years. In
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