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Thursday, May 7, 2020 | History

4 edition of Wind-tunnel development of an SR-71 aerospike rocket flight test configuration found in the catalog.

Wind-tunnel development of an SR-71 aerospike rocket flight test configuration

Wind-tunnel development of an SR-71 aerospike rocket flight test configuration

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Published by National Aeronautics and Space Administration, Dryden Flight Research Center, National Technical Information Service, distributor] in Edwards, Calif, [Springfield, Va .
Written in English


Edition Notes

Other titlesWind tunnel development of an SR-71 aerospike rocket flight test configuration.
StatementTimothy R. Moes ... [et al.].
SeriesNASA technical memorandum -- 4749.
ContributionsMoes, Timothy R., Dryden Flight Research Facility.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL17593997M
OCLC/WorldCa40450892

Library of Congress Cataloging-in-Publication Data (Revised for vol. 8) NASA historical data book. (NASA SP- ) Vol. 1 is a republication of NASA historical data book, –/ Jane Van Nimmen and Leonard C. Bruno. Vol. 8 in series: The NASA historical data book series. Includes bibliographical references and indexes. Development problems also began, with the two static test vehicles, B-4 and B-3 exploding on 15 May and 3 July, respectively. Following this, during the first planned full power flight on

NASA SR Blackbird Challenges and Lessons Learned - Free download as PDF File .pdf), Text File .txt) or read online for free. NASA report on the SR / YF / A Design and Development of the Blackbird: Challenges and Lessons Learned. Published by NASA in /5(3). /02/24 - Pinterest で swift さんのボード「ヒコーキ」を見てみましょう。。「ヒコーキ、飛行機、航空機」のアイデアをもっと見てみましょう。.

Aerospace Inventics Visual Guide - Free ebook download as PDF File .pdf), Text File .txt) or read book online for free. A colection of my early engine 5/5(1). Development Launch and Flight Performance of ESRO Sounding Rocket Payloads VOL I Payloads Launched in /65 Development Launch and Inflight Performance of ESRO Sounding Rocket Payloads VOL IV Payloads Launched Development of a Lunar Escape System Development of a Prototype Plastic Space Erectable Satellite.


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Wind-tunnel development of an SR-71 aerospike rocket flight test configuration Download PDF EPUB FB2

Wind-tunnel development of an SR aerospike rocket flight test configuration. [Timothy R Moes; Dryden Flight Research Facility,] -- A flight experiment has been proposed to investigate the performance of an aerospike rocket motor installed in a lifting body configuration.

An SR airplane would be used to carry the aerospike. in a lifting body configuration. An SR airplane would be used to carry the aerospike configuration to the CL lift coefficient desired flight test conditions. Wind-tunnel tests were completed on a 4-percent scale SR airplane with the Cl rolling moment coefficient (stability axis) aerospike pod mounted in various locations on the upper File Size: 3MB.

Get this from a library. Wind-tunnel development of an SR aerospike rocket flight test configuration. [Timothy R Moes; Dryden Flight Research Facility.;]. LASRE was NASA's Linear Aerospike SR Experiment which took place at the Dryden Flight Research Center at Edwards Air Force Base, California, until November The experiment sought to provide flight data to help Lockheed Martin validate and tune the computational predictive tools used to determine the aerodynamic performance of the Lockheed Martin X.

Flight Testing the Linear Aerospike SR Experiment (LASRE) Stephen Corda, Bradford A. Neal, Flight Testing the Linear Aerospike SR Experiment (LASRE) Stephen Corda, Bradford A.

Neal, this question is to test the aerospike engine in a wind tunnel, which has been done to a limited extent. TheseCited by: 9. Martin was initiated.

The project approach was to flight test an aerospike rocket using an SR aircraft as the carrier vehicle in a project known as the Linear Aerospike SR Experiment (LASRE).

The primary goal of the project was to gather installed rocket engine performance data at flight conditions approximating the X trajectory.

To provide some of these data before flying on the X vehicle and the RLV, a spacecraft rocket engine has been flight-tested atop the NASA SR aircraft as. SR wind tunnel scale model with LASRE pod Additional Information The LASRE experiment was designed to provide in-flight data to help Lockheed Martin evaluate the aerodynamic characteristics and the handling of the SR linear aerospike experiment configuration.

Wind-tunnel development of an SR aerospike rocket flight test configuration. Optimization of 2D Adaptive Wall Test Section for 3D wind tunnel testing.

Ground to flight extrapolation of reentry aircraft aerodynamics - An experimental and computational approach. The Lockheed Martin X was an uncrewed, sub-scale technology demonstrator suborbital spaceplane developed in the s under the U.S. government–funded Space Launch Initiative program.

The X was a technology demonstrator for the VentureStar orbital spaceplane, which was planned to be a next-generation, commercially operated reusable launch on: Uncrewed re-usable. A combination of politics, historical accident, the stagnation of rocket propulsion in the US since the s, and some lingering doubts about aerodynamics at low supersonic speeds.

The latter may be resolved soon -- LockMart, which wants to use an aerospike on its X design, is about to fly a test model on the back of a NASA SR). The Linear Aerospike SR experiment flight tested a 20% scale model of an X forebody with a linear-aerospike engine mounted at the rear of the Author: Hidemi Takahashi.

SR flight flow evaluation These test results, combined with wind tunnel tests and computational fluid dynamics, will be used as design criteria for one contractor's X flight design. If selected, the advanced Aerospike systems are projected for RLV implementation.

Washington, DC: The National Academies Press. doi: / This photo was taken during the fit-check of the pod on Feb. 15,at Lockheed Martin Skunkworks in Palmdale, California. The LASRE experiment was designed to provide in-flight data to help Lockheed Martin evaluate the aerodynamic characteristics and the handling of the SR linear aerospike experiment configuration.

A Pratt & Whitney J58 (JT11D) engine on open display at Evergreen Aviation Museum A preserved AG start cart. The SR was powered by two Pratt & Whitney J58 (company designation JT11D) axial-flow turbojet engines. The J58 was a considerable innovation of the era, capable of producing a static thrust of 32, lbf ( kN).

[54] [55] The engine was most. The airframe-integrated linear-spike nozzle concept applied to an external nozzle for high-speed aircraft was evaluated with regard to the thrust augmentation capability and the trim balance. The main focus was on the vehicle aftbody. The baseline airframe geometry was first premised to be a hypersonic waverider design.

The baseline aftbody case had an external nozzle comprised of Cited by: 1. Technical documents from NASA. This banner text can have markup. WIND-TUNNEL DEVELOPMENT OF AN SR AEROSPIKE ROCKET FLIGHT TEST CONFIGURATION Timothy R. Moes,* Brent R. Cobleigh,* Timothy R. Conners,* and Timothy H.

Cox NASA Dryden Flight Research Center Edwards, California Stephen C. Smith,* NASA Ames Research Center Moffett Field, California Norm Shirakata Lockheed-Martin Skunk Works. Development of a thrust chamber kerosene/oxygen primary rocket subsystem for an early () air-augmented rocket ground test system W.

Escher, D. Pryor and. The LEA hypersonic demonstrator is being developed by Onera Corporation in France. Full scale wind tunnel tests were supposed to start in Septemberwith plans to flight test in cooperation with the Russian TsAGI in – There has been no word from the project since (Fig.

40). Download: Download full-size image; Fig. Cited by:. The L/COPPER COAST flight test program was run by NASA-Dryden, and in the later flight test phase the NASA referred to the vehicle as SYNCON (Synergetic Configuration).

NASA also planned waverider designs as follow-on projects to the L The photo below is said to show a wind tunnel model of such a design. Photo: NASA via FAS .This provides a cost advantage because it avoids costly flight tests and enables substantial development time on the engine’s core components on the test rig.

The pre-cooler testing is an example of the benefits of ground based demonstrations with over tests undertaken to date.Flight Demonstration Program (Office of Space Systems Development), 76 Flight Integration division (Office of Space Access and Technology), 29 Flight operations upgrades, 92, Flight Systems (Office of Space Flight division), 24–25, 26, Flight Systems Office (Office of Life and Microgravity Sciences and Applications),Flight.