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Saturday, May 16, 2020 | History

3 edition of Aerodynamic measurements on a large splitter plate for the Langley Transonic Dynamics Tunnel found in the catalog.

Aerodynamic measurements on a large splitter plate for the Langley Transonic Dynamics Tunnel

D. M. Schuster

Aerodynamic measurements on a large splitter plate for the Langley Transonic Dynamics Tunnel

by D. M. Schuster

  • 15 Want to read
  • 17 Currently reading

Published by National Aeronautics and Space Administration, Langley Research Center, Available from NASA Center for AeroSpace Information (CASI) in Hampton, Va, Hanover, MD .
Written in English

    Subjects:
  • Transonic wind tunnels.,
  • Aerodynamic characteristics.,
  • Dynamic pressure.,
  • Static pressure.,
  • Viscous flow.,
  • Wind tunnel tests.

  • Edition Notes

    StatementDavid M. Schuster.
    Series[NASA technical memorandum] -- NASA/TM-2001-210828., NASA technical memorandum -- 210828.
    ContributionsLangley Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL16028983M

    The Book Review Index, page , lists the books reviewed during , the author, publisher, and reviewer, and the volume, issue number, and page on which the review appeared. sition with Large Leading-Edge Roughness J Velocit y Measurements over a Pitching Airfoil sional Testing with Splitter Plates J Design and Testing. Introduction to Aircraft Design Why study aerodynamics? •!Anything can fly, as long as you put a big enough rocket engine under it. But: •!For a flat plate, the lift coefficient can be obtained from c l = l 1 2!U2c c l = 2!" of large aircraft can cause serious problems in airports. Introduction to Aircraft Design.

    This is a concern because large patterns are associated with lower dart density, resulting in reduced effectiveness in clearing mines. Aside from numerous store-interference studies of weapons released from aircraft,2,3 experimental results are lacking on transonic aerodynamic loads of multiple bodies in close proximity. facility was the conversion of the Langley ft Pressure Tunnel to the Transonic Dynamics Tunnel (TDT). The new wind tunnel would have all the features proposed by Regier: a by ft test section that could operate at Mach numbers up to with variable pressure conditions in either air or a heavy gas with the chemical.

    Full text of "Transonic Shock-Wave/Boundary-Layer Interactions on an Oscillating Airfoil" See other formats NASA/TM- _ ^ _ >/.,,.j - ; - c- / 2r?- ^ -> / AIAA R Transonic Shock-Wave/Boundary-Layer Interactions on an Oscillating Airfoil S. S. Davis and G. N. Malcolm Reprinted from AIM Journal Vol Num November , Page This paper is . Aerodynamic Flow Characteristics of Utilizing Delta Wing Configurations in Supersonic and Subsonic Flight Regimes been effectively used to demonstrate these. 2. CFD Analysis The following is the entire process utilized to analyze the delta wing models on CFD. Two delta wing models have been produced, one representing aFile Size: 1MB.


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Aerodynamic measurements on a large splitter plate for the Langley Transonic Dynamics Tunnel by D. M. Schuster Download PDF EPUB FB2

Tests conducted in the NASA Langley Research Center Transonic Dynamics Tunnel (TDT) assess the aerodynamic characterqstics of a splitter plate used to test some semispan models in this facilio. Aerodynamic clam are analyzed to determine the effect of the splitter plate on the operating characteristics of the TDT, as well as to define the.

The NASA Langley Transonic Dynamics Tunnel (TDT) recently completed a substantial Construction of Facility (CofF) project that converted the heavy gas operating medium for the tunnel from R to the more environmentally safe Ra. The TDT is a large-scale, closed-return, continuous flow tunnel.

Aerodynamic Measurements on a Large Splitter Plate for the NASA Langley Transonic Dynamics Tunnel Article (PDF Available) April with Reads How we measure 'reads'Author: David Schuster. Overview of Supersonic Aerodynamics Measurement Techniques in the NASA Langley Unitary Plan Wind Tunnel [Erickson, Gary E., Nasa Technical Reports Server (Ntrs)] on *FREE* shipping on qualifying offers.

Overview of Supersonic Aerodynamics Measurement Techniques in the NASA Langley Unitary Plan Wind TunnelCited by: 2. Aerodynamic Measurements: From Physical Principles to Turnkey Instrumentation (Woodhead Publishing in Mechanical Engineering) [Russo, G P] on *FREE* shipping on qualifying offers.

Aerodynamic Measurements: From Physical Principles to Turnkey Instrumentation (Woodhead Publishing in Mechanical Engineering)2/5(1). History. The Foot Transonic Dynamics Tunnel (TDT) was not always ft. When constructed inthe tunnel was known as the Foot Pressure tunnel was made form approximately 5, tons of steel.

An 8,horsepower electric motor and a ft propeller were : Langley Research Center. The test data was acquired in the NASA Langley Transonic Dynamics Tunnel at Mach numbers of and [Show full abstract] at Reynolds numbers per foot of x. Foot Transonic Tunnel.

The Langley Foot Transonic Tunnel (Ft TT) is an atmospheric, closed-circuit tunnel with a Mach number range of to and a Reynolds number range from 1 x 10 6 to 4 x 10 6 per foot. The test section of the tunnel is octagonal with a distance of ft across the flats.

Abstract. The capacity of vertical splitter plates placed at the front or the rear of a simplified car geometry to reduce drag, with and without skew angle, is investigated for Reynolds numbers between × 10 6 and × 10 geometry used is a simplified geometry to represent estate-type vehicles, for the rear section, and MPV-type by: Configuration Aerodynamics 7/31/16 Figure The SR The XB The XB is shown in Figures and The airplane was intended to be a Mach 3 intercontinental bomber.

However, the successful development of ICBMs meant there was no longer a need for the plane, instead it became a research airplane. Two were built. Aerodynamic measurements were taken over models of the Boeing high fidelity isolated landing gear at a free-stream Mach number of Noise control devices (NCD) were developed at Virginia Tech to reduce noise by shielding gear components, reducing wake interactions and by streamlining the flow around certain landing gear : Aditya Ringshia.

Wind tunnel measurements and calculations of the aerodynamic interactions between two tiltrotor aircraft in helicopter mode are presented. The measured results include the roll moment and thrust change on the downwind aircraft, as a function of the upwind aircraft position (longitudinal, lateral, and vertical).Cited by: The Transonic Dynamics Tunnel (TDT) at the National Aeronautics and Space Administration's (NASA) Langley Research Center began research op-erations in early Since that time, over tests have been conducted, primarily in the discipline of aeroelasticity.

This paper presents a bibliog. Boundary layer measurements on the splitter plate showed the flow on the splitter was relatively insensitive to the tunnel floor boundary layer.

Full text of "Two-dimensional aerodynamic characteristics of the NACA airfoil in the Langley 8 foot transonic pressure tunnel" See other formats Nei 1^ m m 13 2 Li Z 1^ iZO il.4 il.6 NASA Technical Memorandum {NASA-TM) TWO-DIMENSIOHAL AERODYKAMIC CHARACTERISTICS OF THE NACA AIBFOIL IN THE LANGLEY 8.

19 Schuster, David M., “Aerodynamic measureme nts on a lar ge splitter plate for the NASA Langley Transonic Dynamics Tunnel,” NASA TM -March The NASA Langley Transonic Dynamics Tunnel (TDT) is a continuous-flow, closed circuit, slotted-throat wind tunnel that has a test section that is feet square with filleted corners.

This wind tunnel was originally constructed as a foot diameter subsonic pressure tunnel in (ref.1). During the s, the. Sahoo N Simultaneous measurement of aerodynamic forces and convective surface heat transfer rates for large angle blunt cones in hypersonic shock tunnel, Ph D thesis, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, by: AERODYNAMIC LOADS MEASUREMENT OF A SOUNDING ROCKET VEHICLE TESTED IN WIND TUNNEL Maria Luísa Reis 1, João Batista Falcão 2, Giuliano Paulino 3, Cláudio Truyts 4 1 Institute of Aeronautics and Space, São José dos Campos, Brazil, [email protected] 2 Institute of Aeronautics and Space, São José dos Campos, Brazil, @ splitter plate, C D changes from when the velocity changes from m/s to m/s.

From the above figures we can say that forward splitter plate is more efficient when compared to the backward splitter plate because forward splitter plate gives less coefficient of drag than the backward splitter plate.

CONCLUSION. A limited amount of data is presented near zero and maximum lift for a Reynolds number of x 10 to the sixth power with transition fixed. In addition, transition free data is presented through the Mach number range from to for near zero lift and a Reynolds number of x 10 to the sixth power.This work includes characterizing both the aerodynamic [1, 2, 3] and aero-optic [4,5,6] performance of the flow around the turrets at subsonic and transonic.

The M Transonic Cryogenic Tunnel (TCT) became a new asset to Langley in The small size of the tunnel was the result of the astronomical construction price a full-scale transonic tunnel entails. From tests conducted in the TCT, researchers discovered that decreasing air temperatures decreased the viscosity factor in the denominator of Center: Langley Research Center.