2 edition of Expanded operational capabilities of the Langley Mach 7 scramjet test facility found in the catalog.
Expanded operational capabilities of the Langley Mach 7 scramjet test facility
Scott R Thomas
by National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in Washington, D.C, [Springfield, Va
Written in English
|Statement||Scott R. Thomas and Robert W. Guy|
|Series||NASA technical paper -- 2186|
|Contributions||Guy, Robert W, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Langley Research Center|
|The Physical Object|
|Pagination||71 p. :|
|Number of Pages||71|
capabilities for both fuel and overall engine design in lowering the starting Mach number; these results are presented here. The analysis has shown that a scramjet with a starting Mach number of is not currently possible with the fuels researched unless Scramjet Mach Number .. 29 Assessment: Feasibility of Mach StartingFile Size: 2MB. One Dimensional Analysis Program for Scramjet and Ramjet Flowpaths Kathleen Tran Abstract One-Dimensional modeling of dual mode scramjet and ramjet flowpaths is a useful tool for scramjet conceptual design and wind tunnel testing. In this thesis, modeling tools that enable detailed analysis of the flow physics within the combustor are.
Template:Seriesbox aircraft propulsion A scramjet (supersonic combusting ramjet) is a variant of a ramjet airbreathing jet engine in which combustion takes place in supersonic airflow. As in ramjets, a scramjet relies on high vehicle speed to forcefully compress the incoming air before combustion (hence ramjet), but a ramjet decelerates the air to subsonic velocities before combustion, while. This banner text can have markup.. web; books; video; audio; software; images; Toggle navigation.
Mach or capability with hydrogen fuel is highly , hopefully, a fairly straightforward extension of today's tech nology. The scramjet is the only air-breathinG engine capable of operation from Mach to the proposed staging flight speed. Before examining the scramjet further, a . Scramjet programs refers to research and testing programs for the development of supersonic combustion ramjets, known as list provides a short overview of national and international collaborations, and civilian and military programs. The USA, Russia, India, and China (), have succeeded at developing scramjet technologies.
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Get this from a library. Expanded operational capabilities of the Langley Mach 7 scramjet test facility. [Scott R Thomas, (Engineer); Robert W Guy; United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.; Langley Research Center.]. An experimental research program conducted to expand the operational capabilities of the NASA Langley Mach 7 Scramjet Test Facility is described.
Previous scramjet testing in this facility was limited to a single simulated flight condition of Mach at an altitude ofby: Expanded operational capabilities of the Langley Mach 7 scramjet test facility / By Scott R.
Thomas, Robert W. Guy, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch. and Langley Research Center. Abstract "October "buted to depository libraries in microfiche."Langley. An experimental research program conducted to expand the operational capabilities of the NASA Langley Mach 7 Scramjet Test Facility is described.
Previous scramjet testing in this facility was limited to a single simulated flight condition of Mach at an altitude of: S. Thomas and R.
Guy. The NASA Langley Scramjet Test Complex combustor test capability at Mach and During the NASP Program, the HYPULSE test capability was tois the propulsion facility complex at NASA Langley Research Center. This paper describes the current configurations and capabilities of the File Size: KB.
Operating characteristics of the Langley Mach 7 Scramjet Test Facility. Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. Expanded operational capabilities of the Langley Mach 7 scramjet test facility [microform] / Scott R.
T OVRhyp: scramjet test aircraft [microform] / J. Aslan [et al.] Experimental investigation of inlet-combustor isolators for a dual-mode scramjet at a Mach number of 4 [. The NASA Langley Scramjet Test Complex consists of five propulsion facilities which cover a wide spectrum of supersonic combustion ramjet (scramjet) test capabilities.
These facilities permit observation of the effects on scramjet performance of speed and dynamic pressure from Mach to near-orbital speeds, engine size from Mach 4 to 7, and test gas composition from Mach 4 to 7.
The NASA Langley Scramjet Test Complex. Computational and Experimental Characterization of the Mach 6 Facility Nozzle Flow for the Enhanced Injection and Mixing Project at NASA Langley Research Center.
5 January The nominal facility air conditions correspond to a total pressure and total temperature of MPa ( psi) and K (°R), respectively, expanded to a Mach number of The Langley 8-Foot High-Temperature Tunnel (8-ft HTT) is used to test components of hypersonic vehicles for aerothermal loads de nition and structural component veri cation.
The test medium of the 8-ft HTT is obtained by burning a mixture of methane-air under high pressure; the combustion products are expanded through an axisymmetric conical-contoured nozzle to simulate atmospheric ight at Mach 7. A scramjet engine for the vehicle has been fired dozens of times at Langley’s 8-Foot High Temperature Tunnel.
With four test flights over the Pacific Ocean slated to begin inthe XA will ultimately attempt record-breaking engine burns lasting five minutes, which should propel the craft to about Mach : Geoffrey Little. These facilities permit observation of the effects on scramjet performance of speed and dynamic pressure from Mach to near-orbital speeds, engine size from Mach 4 to 7, and test gas.
A complete subscale, boiler-plate-type engine module is presently being installed in the Langley Mach 7 Scramjet Test Facility for performance tests (Fig. Engine/airframe integration An airbreathing hypersonic vehicle, to achieve optimum performance, must be designed with careful attention to the integration of the propulsion system with Cited by: 9.
This facility, which started operations inwas constructed to verify flight-weight structure at Mach 7 flight conditions. The 8' HTT was removed from service in to add an oxygen enrichment system for scramjet testing.
Langley Research Center has long been a major contributor to scramjet development. This facility DAS includes about channels of data, a 6-compo- nent force balance, and pressure probe and gas sampling survey capability.
The AHSTF is the primary Mach 7 work-horse scramjet facility at Langley, and is more fully characterized in ref. Figure 15 shows a Hyper-X scramjet model installed in the AHSTF test cabin.
also shown by a vertical bar in figure 3; the facility is designated the Langley Mach 4 Scramjet Test Facility (Mach 4 STF). The potential of these facilities to simulate a wide range of test conditions is represented by the hatched areas of figure 3. The range of test capabilities of the arc heater has been demonstrated (refs.
31 and 32). Infree-jet testing of a REST scramjet at Mach was performed in the NASA Langley Combustion Heated Scramjet Test Facility, shown in Fig. 14 (d). This REST scramjet, including an elliptical combustor, has a design point of Machand is intended to operate with fixed-geometry between Mach and Cited by: 1.
At a test facility at Arnold Air Force Base in the U.S. state of Tennessee, GASL fired a projectile equipped with a hydrocarbon-powered scramjet engine from a large gun.
On Jthe four inch ( mm) wide projectile covered a distance of feet (79 m) in 30 milliseconds (roughly 5, mph or 9, km/h). (refs. 27 and 28) which has the capability, with ll-in-square exit nozzles installed, as represented by the vertical bars in figure 3; scramjet engine tests have been conducted in this facility at the simulated Mach 7 flight conditions as reported in references 29 and The second facility has a hydrogen-burning, vitiated.
engine. In addition, the ground test program at Mach 10 was expected to provide confidence in the design and analysis computational tools and techniques. Such a database, when combined with the broad scramjet knowledge at and below flight Mach 7 conditions, has provided scramjet operational experience into the hypervelocity by: air mixtures supersonic combustion in scramjet combustion chambers is offered to use a special test-bed on the basis of facility U - 12 modernization.
The test-bed includes the pressure vessel of a variable volume, succeeded hypersonic nozzles on Mach numbers 4, 6, 8, 10, combustion chamber, exit nozzle and exhaust system.duplicating flight speeds from Mach 7 to 18 enabled some testing of scramjet components and engine flow paths.
These tests, although limited in number and scope, did provide the impetus to move forward with enhancing the airbreathing propulsion research capabilities within this Mach number range.
One test facility that came out of.