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Institution

Vaughn College of Aeronautics and Technology

EducationNew York, New York, United States
About: Vaughn College of Aeronautics and Technology is a education organization based out in New York, New York, United States. It is known for research contribution in the topics: Gravitational microlensing & Planetary system. The organization has 727 authors who have published 708 publications receiving 14082 citations. The organization is also known as: College of Aeronautics.


Papers
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Journal ArticleDOI
TL;DR: In this article, an RUL prediction method based on the consistency test of a Wiener process is proposed, and the validity of the presented method is verified by accurate computation results of real data, which provides a theoretical and practical guidance for engineers to predict the RUL of equipment after maintenance.

12 citations

Journal ArticleDOI
TL;DR: In this paper, the effects of flap deflection, configuration incidence and leading edge bluntness on boundary layer separation and transition have been studied experimentally using a quasi two-dimensional flat plate equipped with a full span trailing edge control flap.
Abstract: The effects of flap deflection, configuration incidence and leading edge bluntness on boundary layer separation and transition have been studied experimentally. A quasi two-dimensional flat plate equipped with a full span trailing edge control flap has been employed for these tests. The studies have been carried out in a hypersonic gun tunnel at M∞ = 8·2 and Re∞/cm = 9·0 × 104. The flap deflection angles studied were in the range 0° ≤ β ≤ 30°. The incidence range was from zero to α = 10° (positive α is nose down). Leading edge bluntness effects were simulated by the introduction of a hemi-cylindrical leading edge. The flow structure was studied using high speed Schlieren photography as well as surface pressure and heat transfer measurements. Liquid crystals were employed to study the threedimensionality of the flow structure for selected configurations. Analytical theories have been developed to estimate the flap pressure and heat transfer levels for the sharp and blunt configurations. These are compared against experimental measurements.

12 citations

Journal ArticleDOI
TL;DR: In this article, a number of stochastic models of fatigue crack growth under constant amplitude cyclic loading are assessed in the light of experimental data, and the predictive performance of the models under a change in the initial crack length is found to provide a poor estimate of the standard deviation of the number of cycles to failure.

12 citations

Journal ArticleDOI
TL;DR: In this article, the effects of surface roughness on the Mach 8·2 hypersonic turbulent shockwave boundary layer interaction characteristics of a deflected control flap configuration were investigated. And the authors found that roughness significantly increased the extent of the interaction, while increasing the magnitude of the peak pressure and heat flux just aft of reattachment.
Abstract: An experimental investigation was performed to study the effects of surface roughness on the Mach 8·2 hypersonic turbulent shockwave–boundary-layer interaction characteristics of a deflected control flap configuration. In particular, the surface pressure and heat transfer distribution along a quasi-2D ramp compression corner model was measured for flap angles between 0° and 38°, along with a Schlieren flow visualisation study. It was found that surface roughness, of scale 10% of the hinge-line boundary layer thickness, significantly increased the extent of the interaction, while increasing the magnitude of the peak pressure and heat flux just aft of reattachment. The incipient separation angle for a fully turbulent, Mach 8·2 boundary layer with a hinge line Reynolds number of 1·44 × 106, was estimated at 28-29°, reducing to between 19-22° with the introduction of laminar sub-layer scale surface roughness.

12 citations

01 Oct 1965
TL;DR: In this article, the attachment line of a swept wing was studied in a low speed wind tunnel with particular reference to this problem of turbulent contamination, and a device was developed to act as a barrier to the turbulent root flow so that a clean laminar flow could exist outboard.
Abstract: Flight tests on the Handley Page suction wing showed that turbulence at the wing root can propagate along the leading edge and cause the whole flow to be turbulent. The flow on the attachment line of a swept wing was studied in a low speed wind tunnel with particular reference to this problem of turbulent contamination. The critical Reynolds number, RθL , of the attachment-line boundary layer for the spanwise spread of turbulence was found to be about 100 for sweep angles in the range 40°–60°. A device was developed to act as a barrier to the turbulent root flow so that a clean laminar flow could exist outboard. This device was shown to be effective up to an Rθ of at least 170, so that experiments were possible on a laminar boundary layer at Reynolds numbers above the lower critical value. A spark was used to introduce spots of turbulence into the attachment-line boundary layer and the propagation speeds of the leading and trailing edges were measured. The spots expanded, the leading edge moving faster than the trailing edge, at high Reynolds numbers, and contracted at low values. The behaviour of Tollmien-Schlichting waves was also investigated by exciting the flow with sound emanating from a small hole on the attachment line. Measurements of the perturbation phase and amplitude were made downstream of the source and, although accurate values of wave length and propagation speed could be found, difficulties were experienced in evaluating the amplification ratio. Nevertheless, all small disturbances decayed at a sufficient distance from the source hole up to the highest available Reynolds number of 170.

12 citations


Authors

Showing all 732 results

NameH-indexPapersCitations
Xiang Zhang1541733117576
Denis J. Sullivan6133214092
To. Saito511839392
Arthur H. Lefebvre411234896
Michele Meo402235557
Robin S. Langley402635601
Ning Qin372835011
Holger Babinsky332424068
B. S. Gaudi31642560
Philip J. Longhurst29802578
Michael Gaster27663998
Don Harris261292537
To. Saito25562362
John F. O'Connell22891763
Rade Vignjevic21841563
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Performance
Metrics
No. of papers from the Institution in previous years
YearPapers
20236
20223
202145
202033
201934
201841