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Development Of Flow Distortions In A Full Scale Nacelle Inlet At Mach Numbers 063 And 16 To 20
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Book Synopsis Development of Flow Distortions in a Full-scale Nacelle Inlet at Mach Numbers 0.63 and 1.6 to 2.0 by : Thomas G. Piercy
Download or read book Development of Flow Distortions in a Full-scale Nacelle Inlet at Mach Numbers 0.63 and 1.6 to 2.0 written by Thomas G. Piercy and published by . This book was released on 1956 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Performance of a Mach Number 3.0 Design Axisymmetric Double-cone External-compression Inlet in the Mach Number Range 1.97 to 0.79 by : Owen H. Davis
Download or read book Performance of a Mach Number 3.0 Design Axisymmetric Double-cone External-compression Inlet in the Mach Number Range 1.97 to 0.79 written by Owen H. Davis and published by . This book was released on 1960 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Tests of a Small-scale NACA Submerged Inlet at Transonic Mach Numbers by : L. Stewart Rolls
Download or read book Tests of a Small-scale NACA Submerged Inlet at Transonic Mach Numbers written by L. Stewart Rolls and published by . This book was released on 1950 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1992 with total page 562 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722851736 Total Pages :74 pages Book Rating :4.8/5 (517 download)
Book Synopsis Ultra High Bypass Nacelle Aerodynamics Inlet Flow-Through High Angle of Attack Distortion Test by : National Aeronautics and Space Administration (NASA)
Download or read book Ultra High Bypass Nacelle Aerodynamics Inlet Flow-Through High Angle of Attack Distortion Test written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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...
Book Synopsis Aerodynamic Calibration and Shakedwon Testing of the Full-scale F-15 Aircraft Inlet Simulator by : W. F. Kinzey
Download or read book Aerodynamic Calibration and Shakedwon Testing of the Full-scale F-15 Aircraft Inlet Simulator written by W. F. Kinzey and published by . This book was released on 1973 with total page 612 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Methodology for Assessing Inlet Swirl Distortion by : S-16 Turbine Engine Inlet Flow Distortion Committee
Download or read book A Methodology for Assessing Inlet Swirl Distortion written by S-16 Turbine Engine Inlet Flow Distortion Committee and published by . This book was released on 2022 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Effects of Aspect Ratio on Air Flow at a High Subsonic Mach Numbers by : W. F. Lindsey
Download or read book Effects of Aspect Ratio on Air Flow at a High Subsonic Mach Numbers written by W. F. Lindsey and published by . This book was released on 1948 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Theoretical Flow Characteristics of Inlets for Tilting-nacelle VTOL Aircraft by : Michael A. Boles
Download or read book Theoretical Flow Characteristics of Inlets for Tilting-nacelle VTOL Aircraft written by Michael A. Boles and published by . This book was released on 1978 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Literature Search of Publications Concerning the Prediction of Dynamic Inlet Flow Distortion and Related Topics by : William G. Schweikhard
Download or read book Literature Search of Publications Concerning the Prediction of Dynamic Inlet Flow Distortion and Related Topics written by William G. Schweikhard and published by . This book was released on 1983 with total page 156 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Comparisons of In-flight F-111A Inlet Performance for On- and Off-scheduled Inlet Geometry at Mach Numbers of 0.68 to 2.18 by : Richard A. Martin
Download or read book Comparisons of In-flight F-111A Inlet Performance for On- and Off-scheduled Inlet Geometry at Mach Numbers of 0.68 to 2.18 written by Richard A. Martin and published by . This book was released on 1971 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: In-flight F-111 data on total and static pressure from left inlet during automatically scheduled and manually controlled off-schedule positioning of spike at Mach 0.68 to 2.18.
Book Synopsis Effect of External Boundary Layer on Performance of Axisymmetric Inlet at Mach Numbers of 3.0 and 2.5 by : N. E. Samanich
Download or read book Effect of External Boundary Layer on Performance of Axisymmetric Inlet at Mach Numbers of 3.0 and 2.5 written by N. E. Samanich and published by . This book was released on 1959 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Some Considerations Concerning Inlets and Ducted Bodies at Mach Numbers from 0.8 to 2.0 by : Richard I. Sears
Download or read book Some Considerations Concerning Inlets and Ducted Bodies at Mach Numbers from 0.8 to 2.0 written by Richard I. Sears and published by . This book was released on 1953 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722226565 Total Pages :24 pages Book Rating :4.2/5 (265 download)
Book Synopsis F/A-18a Inlet Flow Characteristics During Maneuvers with Rapidly Changing Angle of Attack by : National Aeronautics and Space Administration (NASA)
Download or read book F/A-18a Inlet Flow Characteristics During Maneuvers with Rapidly Changing Angle of Attack written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-03 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: The performance and distortion levels of the right inlet of the F/A-18A High Alpha Research Vehicle were assessed during maneuvers with rapidly changing angle-of-attack at the NASA Dryden Flight Research Center, Edwards, California. The distortion levels were compared with those produced by current inlet-engine compatibility evaluation techniques. The objective of these analyses was to determine whether the results obtained for steady aerodynamic conditions were adequate to describe the inlet-generated distortion levels that occur during rapid aircraft maneuvers. The test data were obtained during 46 dynamic maneuvers at Mach numbers of 0.3 and 0.4. Levels of inlet recovery, peak dynamic circumferential distortion, and peak dynamic radial distortion of dynamic maneuvers for a General Electric F404-GE-400 turbofan engine were compared with estimations based on steady aerodynamic conditions. The comparisons were performed at equivalent angle-of-attack, angle-of-sideslip, and Mach number. Results showed no evidence of peak inlet distortion levels being elevated by dynamic maneuver conditions at high angle-of-attack compared with steady aerodynamic estimations. During sweeps into high angle-of-attack, the peak distortion levels of the dynamic maneuvers rarely rose to steady aerodynamic estimations. The dynamic maneuvers were shown to be effective at identifying conditions when discrete changes in inlet behavior occur. Yuhas, Andrew J. and Steenken, William G. and Williams, John G. and Walsh, Kevin R. Armstrong Flight Research Center; Glenn Research Center NAS3-26617; RTOP 505-68-30...
Book Synopsis Aerodynamic and acoustic performance of high Mach number inlets by :
Download or read book Aerodynamic and acoustic performance of high Mach number inlets written by and published by . This book was released on 1977 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight Investigation of Airframe Installation Effects on a Variable Flap Ejector Nozzle of an Underwing Engine Nacelle at Mach Numbers from 0.5 to 1.3 by : Daniel C. Mikkelson
Download or read book Flight Investigation of Airframe Installation Effects on a Variable Flap Ejector Nozzle of an Underwing Engine Nacelle at Mach Numbers from 0.5 to 1.3 written by Daniel C. Mikkelson and published by . This book was released on 1970 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Performance of Vortex Generators in a Mach 2.5 Low-bleed Full-scale 45-percent-internal-contraction Axisymmetric Inlet by : Harvey E. Neumann
Download or read book Performance of Vortex Generators in a Mach 2.5 Low-bleed Full-scale 45-percent-internal-contraction Axisymmetric Inlet written by Harvey E. Neumann and published by . This book was released on 1975 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
