Development of Flow Distortions in a Full-scale Nacelle Inlet at Mach Numbers 0.63 and 1.6 to 2.0 PDF Download
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Author: Thomas G. Piercy
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 72
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Book Description
Author: Thomas G. Piercy
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 72
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Book Description
Author: Owen H. Davis
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 34
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Book Description
Author: L. Stewart Rolls
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 22
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Book Description
The pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 have been measured in the Mach number range 0.60 to 1.08 by the wing-flow method. The variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722851736
Category :
Languages : en
Pages : 74
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Book Description
A flow-through inlet test program was conducted to evaluate inlet test methods and determine the impact of the fan on inlet separation when operating at large angles of attack. A total of 16 model configurations of approximately 1/6 scale were tested. A comparison of these flow-through results with powered data indicates the presence of the fan increased separation operation 3 degrees to 4 degrees over the flow through inlet. Rods and screens located at the fan face station, that redistribute the flow, achieved simulation of the powered-fan results for separation angle of attack. Concepts to reduce inlet distortion and increase angle of attack capability were also evaluated. Vortex generators located on the inlet surface increased inlet angle of attack capability up to 2 degrees and reduced inlet distortion in the separated region. Finally, a method of simulating the fan/inlet aerodynamic interaction using blockage sizing method has been defined. With this method, a static blockage device used with a flow-through model will approximate the same inlet onset of separation angle of attack and distortion pattern that would be obtained with an inlet model containing a powered fan. Larkin, Michael J. and Schweiger, Paul S. Unspecified Center...
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 562
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Book Description
Author: W. F. Kinzey
Publisher:
ISBN:
Category : Eagle (Jet fighter plane)
Languages : en
Pages : 612
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Author: S-16 Turbine Engine Inlet Flow Distortion Committee
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
This Aerospace Information Report (AIR) addresses the subject of aircraft inlet-swirl distortion. A structured methodology for characterizing steady-state swirl distortion in terms of swirl descriptors and for correlating the swirl descriptors with loss in stability pressure ratio is presented. The methodology is to be considered in conjunction with other SAE inlet distortion methodologies. In particular, the combined effects of swirl and total-pressure distortion on stability margin are considered. However, dynamic swirl, i.e., time-variant swirl, is not considered. The implementation of the swirl assessment methodology is shown through both computational and experimental examples. Different types of swirl distortion encountered in various engine installations and operations are described, and case studies which highlight the impact of swirl on engine stability are provided. Supplemental material is included in the appendices.This AIR is issued to bring together information and ideas required to address the inlet-swirl problem for which common industry practice has yet to be established. This document should foster the tests and analyses necessary to mature the ideas proposed by the committee to a recommended practice. These tests and analyses must include information that justifies three main features of the proposed swirl methodology: (1) swirl descriptors for correlating inlet swirl and stability pressure ratio loss, (2) computational techniques for analyzing compression systems (inlets, fans, compressors), and (3) test protocols (instrumentation and test techniques). The committee anticipates serving the industry by using such information to establish the consensus necessary for issuance of an SAE recommended practice. AIR5686 has been reaffirmed to comply with the SAE Five-Year Review policy.
Author: W. F. Lindsey
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 18
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Book Description
Schlieren photographs were used in an investigation to determine the effects of changing the aspect ratio from infinity to two on the air flow past a wing at high subsonic Mach numbers. The results indicated that the decreased effects of compressibility on drag coefficients for the finite wing are produced by a reduction in the compression shock and flow separation.
Author: Michael A. Boles
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
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Book Description
Author: William G. Schweikhard
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 156
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Book Description
Publications prior to March 1981 were surveyed to determine inlet flow dynamic distortion prediction methods and to catalog experimental and analytical information concerning inlet flow dynamic distortion prediction methods and to catalog experimental and analytical information concerning inlet flow dynamics at the engine-inlet interface of conventional aircraft (excluding V/STOL). The sixty-five publications found are briefly summarized and tabulated according to topic and are cross-referenced according to content and nature of the investigation (e.g., predictive, experimental, analytical and types of tests). Three appendices include lists of references, authors, organizations and agencies conducting the studies. Also, selected materials summaries, introductions and conclusions - from the reports are included. Few reports were found covering methods for predicting the probable maximum distortion. The three predictive methods found are those of Melick, Jacox and Motycka. The latter two require extensive high response pressure measurements at the compressor face, while the Melick Technique can function with as few as one or two measurements.
