An Experimental Investigation of a Laminar, Hypersonic Flow Over a Three-dimensional Cone Cavity with Mass Injection PDF Download
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Author: James E. Shifflett
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Category :
Languages : en
Pages :
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Author: James E. Shifflett
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Category :
Languages : en
Pages :
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Author: Kenneth M. Nicoll
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Category : Aerodynamics, Supersonic
Languages : en
Pages : 44
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An experimental investigation was made of the recovery factor and heat-transfer distributions on a set of cone-models incorporating annular cavities. This study is the second part of a two-part program. The first section contained measurements of the pressure distributions. The results show that the recovery factor in laminar, hypersonic cavity flow is almost constant within the cavity and downstream of reattachment, and is very close to the laminar attached-flow value. In the immediate vicinity of reattachment, the recovery factor is slightly higher than this value (less than 5%). The lowest values of the heat-transfer coefficient are found on the cavity floors, where a minimum of about 10 to 20% of the attached-flow value is reached. The highest values of the heat-transfer coefficient are in the immediate vicinity of reattachment. An average reattachment heattransfer coefficient of about three times the basic cone heat-transfer coefficient was measured on one cavity model. (Author).
Author: Kenneth M. Nicoll
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Category :
Languages : en
Pages : 80
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The present report describes an experimental investigation of a hypersonic cavity flow with mass-injection into the separated-flow region. The experiments were carried out in a helium wind-tunnel at a free-stream Mach number of eleven. The injected gas was helium. Two parameters were varied during the study -- the mass injection rate and the height of the separation shoulder relative to the reattachment shoulder. The effects of these parameters on the distributions of pressure and heat transfer rate were investigated. Mass injection appeared to have no drastic effect on transition Reynolds number, and the cavity flow is believed to have been laminar throughout the present investigation. The effect on the cavity floor pressure of raising the separation shoulder relative to the reattachment shoulder was of the same order as the effect of mass injection, the two effects being virtually independent of one another. However, the flow in the immediate vicinity of the reattachment shoulder and downstream was primarily controlled by mass injection rate. Small amounts of mass injection were capable of completely removing the pressure peak at reattachment, and could produce a flow with almost constant pressure within and downstream of the cavity. Mass injection had a pronounced effect on the heat transfer rate in the vicinity of reattachment, and reductions of as much as a factor of six were obtained in the heat transfer peak in this region. Furthermore, the heat transfer rates up to about one cavity length downstream of the reattachment shoulder were reduced by as much as a factor of three by mass injection within the cavity. (Author).
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Category : Aeronautics
Languages : en
Pages : 704
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Author: William F. Hinson
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Category : Aerodynamics, Hypersonic
Languages : en
Pages : 50
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Author: Michael Holden
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Category :
Languages : en
Pages : 58
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An experimental study has been performed to examine the three-dimensional characteristics of laminar, transitional and turbulent flow over an elliptic cone lifting body configuration. The experimental studies were performed at Mach numbers between 8 and 12 at Reynolds numbers, based on model length from 5 x 10(exp 5) to 5 x 10(exp 6). Detailed measurements of the distribution of heating and pressure were made along the leading edges and on the windward and leeward surfaces of the model with over 200 high-frequency, thin-film heat transfer gages and piezoelectric high-frequency pressure transducers. Measurements were also performed using temperature sensitive paints to further delineate the properties of the three-dimensional transitional flow. Schlieren photographs were also obtained of the transitional flow field over the models. Flowfield calibration measurements were made in the LENS facility with intrusive pitot and total heating transducers and nonintrusive electron beam, and infrared radiometer techniques. These data have been incorporated into the CUBRC/AFOSR Hypersonic Database which has been modified to run on the Windows platform.
Author:
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Category : Science
Languages : en
Pages : 684
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ISBN:
Category :
Languages : en
Pages : 570
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Category : Military research
Languages : en
Pages : 572
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Author: Michael F. Martino
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Category :
Languages : en
Pages :
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