Effect of Nozzle Inlet Geometry on Performance of a Swiveled Convergent-divergent Nozzle PDF Download
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Author: Albert J. Pavli
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 44
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Book Description
Author: Albert J. Pavli
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 44
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
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Book Description
Author: Gerald M. Mulenburg
Publisher:
ISBN:
Category :
Languages : en
Pages : 66
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Book Description
This study is an experimental evaluation of the performance of 12 two-dimensional, converging-diverging, cold flow, supersonic nozzles, each with the same throat and divergent section. The relative efficiency of each nozzle was evaluated by a comparison of total pressure measurements taken in the exit plane, schlieren photographs of the flow, and heat transfer characteristics using moire' patterns. The nozzle with the highest efficiency had an inlet which was an ellipse faired to a 45 degree ramp. Its performance was closely followed by that of a nozzle with a circular arc inlet having a radius of three times the throat height. The three nozzles with the lowest efficiencies were those with 30, 45, and 60 degrees linear ramp inlets, respectively. The results of this study indicate that, in nozzle design, a region of immense importance is the curvature just prior to the throat and how this curvature is joined to the throat section. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1582
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Author: United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 428
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Author: Gerald M. Mulenberg (1LT, USAF.)
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 436
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Book Description
Author: Jeffery A. Yetter
Publisher:
ISBN:
Category : Aerodynames
Languages : en
Pages : 122
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Book Description
Author: Bobby L. Berrier
Publisher:
ISBN:
Category : Jet nozzles
Languages : en
Pages : 182
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781720483830
Category :
Languages : en
Pages : 76
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Book Description
An investigation was conducted in the model preparation area of the Langley 16-Foot Transonic Tunnel to determine the effects of convoluted divergent-flap contouring on the internal performance of a fixed-geometry, nonaxisymmetric, convergent-divergent exhaust nozzle. Testing was conducted at static conditions using a sub-scale nozzle model with one baseline and four convoluted configurations. All tests were conducted with no external flow at nozzle pressure ratios from 1.25 to approximately 9.50. Results indicate that baseline nozzle performance was dominated by unstable, shock-induced, boundary-layer separation at overexpanded conditions. Convoluted configurations were found to significantly reduce, and in some cases totally alleviate separation at overexpanded conditions. This result was attributed to the ability of convoluted contouring to energize and improve the condition of the nozzle boundary layer. Separation alleviation offers potential for installed nozzle aeropropulsive (thrust-minus-drag) performance benefits by reducing drag at forward flight speeds, even though this may reduce nozzle thrust ratio as much as 6.4% at off-design conditions. At on-design conditions, nozzle thrust ratio for the convoluted configurations ranged from 1% to 2.9% below the baseline configuration; this was a result of increased skin friction and oblique shock losses inside the nozzle.Asbury, Scott C. and Hunter, Craig A.Langley Research CenterCONVERGENT-DIVERGENT NOZZLES; BOUNDARY LAYER SEPARATION; WIND TUNNEL NOZZLES; WIND TUNNEL TESTS; NOZZLE FLOW; OBLIQUE SHOCK WAVES; FLOW VISUALIZATION; NOZZLE GEOMETRY; AERODYNAMIC DRAG; SKIN FRICTION; PRESSURE RATIO; FLAPS (CONTROL SURFACES)
