3 edition of Description and calibration of the Langley hypersonic CF found in the catalog.
Description and calibration of the Langley hypersonic CF
Raymond E. Midden
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||Raymond E. Midden and Charles G. Miller III.|
|Series||NASA technical paper -- 2384.|
|Contributions||Miller, Charles G. 1940-, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.|
|The Physical Object|
This is the conversion factor that, when multiplied by P, yields the future amount F of an initial amount P after n years at interest rate i Reverse the situation to determine the P value for a . The delta wings were derived from a subsonic airfoil modified to meet hypersonic, thermodynamic, and aerodystability requirements. Even though the configuration favors the subsonic flying regime, the primary design factors were introduced by the low hypersonic heating environment.
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Analysis of Buzz in a Supersonic Inlet Rodrick V. Chima National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio Abstract A dual-stream, low-boom supersonic inlet designed for use on a small, Mach aircraft was tested. The editor and the authors are to be congratulated for tackling this project with professionalism and dedication, and bringing to all of us a terrific book on an important subject. Richard H. Lyon Belmont, Massachusetts PREFACE This book is designed to fill the need for a comprehensive resource on noise and vibration control.
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Get this from a library. Description and calibration of the Langley hypersonic CF₄ tunnel: a facility for simulating low [gamma] flow as occurs for a real gas. [Raymond E Midden; Charles G Miller; United States.
National Aeronautics and Space Administration. Scientific and Technical Information Branch.]. Experimental Hypersonic Aerodynamic Characteristics of the Mars Surveyor Precision Lander with Flap.
A detailed description of. and Calibration of the Langley Hypersonic CF 4. Midden, Raymond E., and Miller, Charles G., III.
Description and Calibration of the Langley Hypersonic CF 4 Tunnel--A Facility for Simulating Low @ Flow as Occurs for a Real Gas. NASA TP Google ScholarCited by: 1.
Sh / Sv represents the horizontal and vertical pixel spacing ratio for the camera sensor. 6 An optimization method, originally proposed by Liu7 utilizes a single-image camera calibration routine that provides easy on-the-job camera calibrations.
This eliminates the need for multiple-image or special laboratory calibrations that are not very well suited for wind tunnel Size: KB. REVIEW OF X HYPERSONIC AERODYNAMIC AND AEROTHERMODYNAMIC DEVELOPMENT Richard A.
Thompson NASA Langley Research Center Abstract A review of the experimental and computational studies performed at NASA Langley Research Center (LaRC) to support the optimization and benchmarking of the hypersonic aerodynamic and aerothermodynamic databases for.
A review of the experimental and computational studies performed at NASA Langley Research Center (LaRC) to support the optimization and benchmarking of the hypersonic aerodynamic and. Becker, "Results of Recent Hypersonic and Unsteady Flow Research at the Langley Aeronautical Laboratory," Journal of Applied Physics 21 (July ): The journal Aviation Week mentioned Becker's article in its 31 July issue, pp.
22 and R.E. Midden and C.G. Miller, "Description and Calibration of the Langley Hypersonic CF 4 Tunnel," NASA TP, March 9. R.A. Jones and J.L. Hunt, "Use of Tetrafluoromethane to Simulate Real-Gas Effects on the Hypersonic Aerodynamics of Blunt Vehicles," NASA TR R, June Work with us at the frontier of innovation to build a brighter future and a safer world.
By clicking, you agree to our privacy notice. If the engineer were interested only in the overall properties of the flow field, (such as the time-averaged drag coefficient, the mean velocity, and pressure fields) a time-averaged description like that of Fig.
1–19b, time-averaged experimental measurements, or an analytical or numerical calculation of the time-averaged flow field would be.
OTHER SOURCES OF INFO: "Description of a 2-Foot Hypersonic Facility at the Langley Research Center, TND, September ". COGNIZANT ORGANIZATIONAL COMPONENT: Full-ScaleResearch Division LOCAL OFFICE TO CONTACT FOR FURTHER INFO: Chief, Research Models and Facilities Division (Code ) Phone: (Area Code ) File Size: 37MB.
An experimental study of the pressure and heat-transfer distribution on a 70° sweep slab delta wing in hypersonic flow / (Washington, D.C.: National Aeronautics and Space Administration ; Springfield, VA: For sale by the Clearinghouse for Federal Scientific and Technical Information, ), by Mitchel H.
Bertram, Philip E. Everhart, Langley. Full text of "NASA Langley Scientific and Technical Information Output" See other formats. PhD Thesis Avallone 1. UNIVERSITÀ DEGLI STUDI DI NAPOLI “FEDERICO II” DIPARTIMENTO DI INGEGNERIA INDUSTRIALE DOTTORATO DI RICERCA IN INGEGNERIA AEROSPAZIALE, NAVALE E DELLA QUALITÀ XXVII CICLO TESI DI DOTTORATO Application of non-intrusive experimental techniques to roughness-induced transition in hypersonic flows Francesco.
The plaque pictured above was recently presented to the Langley Research Center by the Hampton Roads Chapter of the Red Cross. Langley employees donated 1, pints of blood in and 1, pints in The largest number donated during a single visit of the Bloodmobile was pints, a record set in June File Size: 36MB.
Stainback et al.: The experimental results were obtained in the NASA Langley 20 in hypersonic wind tunnel in air. The authors obtained the Stanton number along the surface of a 10 ∘ sharp cone at Mach 6 and 8.
The Mach 6 results are given in their Figs. 3 and The study was also concerned with boundary-layer transition to turbulent flow Cited by: Aerodynamic tests in support of the Columbia acci dent investigation were conducted in two hypersonic wind tunnels at the NASA Langley Rese arch Center.
The primary purpose of these tests was to measure A temperature calibration of CFD cases were run at wind tunnel conditions for both the Langley Mach 6 air and CF 4File Size: 11MB. Full text of "NASA Technical Reports Server (NTRS) Scientific and technical information output of the Langley Research Center for Calendar Year " See other formats.
Use of Preston Tubes for Measuring Hypersonic Turbulent Skin Friction Box 1 A Klein and Margozzi, figs. (orig. figs. to author ()). Fig. 3 shows the wall temperature distributions measured on the sharp cone, at the time of various mean-profile measurement runs.
The coordinate s is the arclength along the surface. The x locations in the legend are the axial locations of the respective mean-profile measurements, and T w is the surface wall temperature. The forward portion of the model heats up with time, and the aft portion Cited by:.
DESCRIPTION: Hypersonic vehicle technology is quickly approaching the point where a small-unmanned glider, flying at 13, mph and at an altitude of 30 to 50 km, could fly to any location in the world in under 60 minutes. The Army aerospace vehicle will need to have similar speed but will likely require significantly enhanced maneuver.This book is for engineers, technical managers, and consultants in the aerospace, automotive, civil, and shipbuilding engineering industries who want to use, or are already using, reliability methods for product design.
Professors and students who work on reliability methods will ﬁnd this book useful, too. The book consists of 11 chapters.CODE OF FEDERAL REGULATIONS 14 Part to end Revised as of January 1, Aeronautics and Space Containing a Codification of documents of general applicability and future effect As of January 1, With Ancillaries.
Published by. Office of the Federal Register. National Archives and Records. Administration. A Special Edition of the Federal Register U.S. GOVERNMENT PRINTING OFFICE.