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  • 1
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    Numerical study of the effects of reverse sweep on scramjet inlet performance (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 8; 3, Ma; 714-719
    Format: text
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  • 2
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    Analysis and performance prediction of scramjet inlets utilizing a three-dimensional Navier-Stokes code (1986)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A series of inlet analysis codes (2-D, axisymmetric, 3-D) were developed which can analyze complicated flow through complex inlet geometries in a reasonably efficient manner. The codes were verified and are being used extensively to analyze practical inlet geometries both at Langley as well as industries. Newly installed VPS 32 computer will allow more complex configurations to be analyzed. Scalar FORTRAN versions are available to increase transportability of the codes for use on other Scalar computers and on the Cray vector processing computer.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Langley Symposium on Aerodynamics, Volume 1; p 187-208
    Format: application/pdf
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  • 3
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    Three-dimensional simulation of a translating strut inlet (1992)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A three-dimensional Navier-Stokes code is used to numerically simulate the flow through a translating strut scramjet inlet. The inlet has variable geometry for efficient operation over a wide speed range. Overall flow-field features such as the corner flow, topwall separation, shockwave coalescence, cowl pressure increase, and flow distortion at the throat are investigated. Comparisons are made with experimental results to provide for the assessment of the present analysis. Effects of boundary-layer ingestion on the overall flow features are also investigated.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-0270
    Format: text
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  • 4
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    Experimental investigation of inlet-combustor isolators for a dual-mode scramjet at a Mach number of 4 (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report details experimentally derived operational characteristics of numerous two-dimensional planar inlet-combustor isolator configurations at a Mach number of 4. Variations in geometry included (1) inlet cowl length; (2) inlet cowl rotation angle; (3) isolator length; and (4) utilization of a rearward-facing isolator step. To obtain inlet-isolator maximum pressure-rise data relevant to ramjet-engine combustion operation, configurations were mechanically back pressured. Results demonstrated that the combined inlet-isolator maximum back-pressure capability increases as a function of isolator length and contraction ratio, and that the initiation of unstart is nearly independent of inlet cowl length, inlet cowl contraction ratio, and mass capture. Additionally, data are presented quantifying the initiation of inlet unstarts and the corresponding unstart pressure levels.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-3502 , L-17422 , NAS 1.60:3502
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  • 5
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    Operating characteristics at Mach 4 of an inlet having forward-swept, sidewall-compression surfaces (1992)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A three-dimensional, forward-swept sidewall-compression inlet has been tested in the Mach 4 Blowdown Facility at the NASA Langley Research Center to examine parameters that affect inlet starting, operability, and performance. The inlet was designed to simultaneously provide good starting and mass capture characteristics through the combination of forward-swept sidewalls and the aft placement of the downstream cowl. Parametrics examined included top surface compression, geometric contraction ratio, sidewall compression angle, boundary-layer thickness on the vehicle undersurface, and cowl position. To simulate combustion effects on inlet operation, the inlet was mechanically back pressured to determine maximum achievable combustor-to-inlet pressure ratio prior to inlet unstart. Inlet operability and performance are shown in terms of inlet starting (pulsed and self-starting) and unstarting characteristics, inlet static pressure distributions, combustor back pressure limits, mass capture, and flow uniformity.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-3101
    Format: text
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  • 6
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    Inlet starting predictions for sidewall-compression scramjet inlets (1988)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: While inlet capture, total pressure recovery, and compression are important performance parameters in the design of scramjet inlets, the inlet must be capable of starting. An analytical, inviscid method has been developed that provides first order starting information for sidewall-compression scramjet inlets and trends have been established for some of the parameters that affect inlet starting. These parameters include sidewall contraction ratio, cowl position, Mach number, sweep angle, fuel injection struts, and sidewall and strut compression angles. Results from the parametric study are compared with data from both no-strut and two-strut inlet models.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 88-3257
    Format: text
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  • 7
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    A numerical study of the effects of reverse sweep on a scramjet inlet performance (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A comparative numerical study of performance parameters of a similar and an opposite sweep sidewall compression inlet is made. The focus of the study is the investigation of the impact of alternate backward-forward sweep on the compression sidewalls as opposed to back-ward sweep on all the sidewalls. Two equivalent scramjet inlet configurations are designed for this purpose. These inlets have the same wetted areas of compression and expansion and same height and width; but in one inlet all the compression surface are swept back (similar sweep inlet) whereas in the other inlet, alternate surfaces are swept backward and forward (opposite sweep inlet). The cowl closure in both cases begins at the start of the throat region. A three-dimensional Navier-Stokes code is used to calculate the flow through these inlets. Results of these calculations are used to compare the two designs for their performance and flow quality. Effects of boundary- layer ingestion on the performance and overall flow features are also investigated.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 90-2218
    Format: text
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  • 8
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    Propulsion Airframe Integration Test Techniques for Hypersonic Airbreathing Configurations at NASA Langley Research Center (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The scope and significance of propulsion airframe integration (PAI) for hypersonic airbreathing vehicles is presented through a discussion of the PAI test techniques utilized at NASA Langley Research Center. Four primary types of PAI model tests utilized at NASA Langley for hypersonic airbreathing vehicles are discussed. The four types of PAI test models examined are the forebody/inlet test model, the partial-width/truncated propulsion flowpath test model, the powered exhaust simulation test model, and the full-length/width propulsion flowpath test model. The test technique for each of these four types of PAI test models is described, and the relevant PAI issues addressed by each test technique are illustrated through the presentation of recent PAI test data.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 2003-4406 , 39th AIAA/ASME/SEA/ASEE Joint Propulsion Conference; Jul 20, 2003 - Jul 23, 2003; Huntsville, AL; United States
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  • 9
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    Mach 4 Performance of a Fixed-Geometry Hypersonic Inlet with Rectangular-to-Elliptical Shape Transition (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Wind-tunnel testing of a hypersonic inlet with rectangular-to-elliptical shape transition has been conducted at Mach 4.0. These tests were performed to investigate the starting and back-pressure limits of this fixed-geometry inlet at conditions well below the Mach 5.7 design point. Results showed that the inlet required side spillage holes in order to self-start at Mach 4.0. Once started, the inlet generated a compression ratio of 12.6, captured almost 80% of available air and withstood a back-pressure ratio of 30.3 relative to tunnel static pressure. The spillage penalty for self-starting was estimated to be 4% of available air. These experimental results, along with previous experimental results at Mach 6.2 indicate that fixed-geometry inlets with rectangular-to-elliptical shape transition are a viable configuration for airframe-integrated scramjets that operate over a significant Mach number range. Nomenclature
    Keywords: Spacecraft Propulsion and Power
    Type: AIAA Paper 2003-0012 , 41st AIAA Aerospace Sciences Meeting and Exhibit; Jan 06, 2003 - Jan 09, 2003; Reno, NV; United States
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  • 10
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    Mach 4 Test Results of a Dual-Flowpath, Turbine Based Combined Cycle Inlet (2006)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An experimental study was conducted to evaluate the performance of a turbine based combined cycle (TBCC) inlet concept, consisting of a low speed turbojet inlet and high speed dual-mode scramjet inlet. The main objectives of the study were (1) to identify any interactions between the low and the high speed inlets during the mode transition phase in which both inlets are operating simultaneously and (2) to determine the effect of the low speed inlet operation on the performance of the high speed inlet. Tests were conducted at a nominal freestream Mach number of 4 using an 8 percent scale model representing a single module of a TBCC inlet. A flat plate was installed upstream of the model to produce a turbulent boundary layer which simulated the full-scale vehicle forebody boundary layer. A flowmeter/back pressure device, with remote actuation, was attached aft of the high speed inlet isolator to simulate the back pressure resulting from dual-mode scramjet combustion. Results indicate that the inlets did not interact with each other sufficiently to affect inlet operability. Flow spillage resulting from a high speed inlet unstart did not propagate far enough upstream to affect the low speed inlet. Also, a low speed inlet unstart did not cause the high speed inlet to unstart. The low speed inlet improved the performance of the high speed inlet at certain conditions by diverting a portion of the boundary layer generated on the forebody plate.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 2006-8138 , 14th AIAA/AHI International Space Planes and Hypersonics Systems and Technologies Conference; Nov 06, 2006 - Nov 09, 2006; Canberra; Australia
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