Last edited by Dolkis
Wednesday, August 5, 2020 | History

2 edition of Results of aerothermodynamic and boundary layer transition testing of 0.0362-Scale X-38 (Rev 3.1) vehicle in NASA Langley 20-inch Mach 6 tunnel found in the catalog.

Results of aerothermodynamic and boundary layer transition testing of 0.0362-Scale X-38 (Rev 3.1) vehicle in NASA Langley 20-inch Mach 6 tunnel

Results of aerothermodynamic and boundary layer transition testing of 0.0362-Scale X-38 (Rev 3.1) vehicle in NASA Langley 20-inch Mach 6 tunnel

  • 157 Want to read
  • 32 Currently reading

Published by National Aeronautics and Space Administration, Langley Research Center, National Technical Information Service, distributor in Hampton, Va, Springfield, VA .
Written in English

    Subjects:
  • Boundary layer transition.,
  • Aerodynamic heating.,
  • Wind tunnel tests.,
  • Angle of attack.,
  • Reynolds number.,
  • Aerothermodynamics.,
  • Flow visualization.

  • Edition Notes

    StatementScott A. Berry ... [et al.].
    SeriesNASA technical memorandum -- 112857.
    ContributionsBerry, Scott A., Langley Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15553995M

    FD Aero-Optics and Other Fundamental Topics • Thursday, 25 June • hrs   The results of the Mach case with the fully catalytic wall boundary condition (i.e., the atomic oxygen and nitrogen species in the stock layer recombine completely at the wall to give molecular oxygen and nitrogen, respectively) are shown in Fig. 9. The grid is clustered near the wall, with a wall spacing of 10 μm at the nose and 30 μm

    The final wavelength ranges in UV radiation between ± nm for xenon and ± nm for atomic oxygen with a step width of ~ pm for both studies. The energy of the UV radiation is varied by means of a variable attenuator (VA), which is installed through the optical path at the laser :// Proc. SPIE , 14th International Workshop on Breast Imaging (IWBI ), (6 July ); doi: /

    while strong positive R s are found at lower levels in the boundary layer. In addition, Note that the scale and intervals in x axis are different from Figure Figure Open in figure viewer PowerPoint. Same as   Berry S.A., Horvath T.J., Roback V.E., Williams G.B. Results of Aerothermodynamic and boundary layer transition testing of Scale X vehicle in NASA Langley 20 inch Mach 6 Tunnel. NASA TM - Sept


Share this book
You might also like
Workbook for language skills

Workbook for language skills

Bergsma Natural History of Specific Birth Defects

Bergsma Natural History of Specific Birth Defects

200 acre choice farm for sale, in Toronto Township, county of Peel

200 acre choice farm for sale, in Toronto Township, county of Peel

Awesome Jokes

Awesome Jokes

Omoo

Omoo

Migration and urbanisation in South Africa.

Migration and urbanisation in South Africa.

The Summer Olympics

The Summer Olympics

Keep cheery.

Keep cheery.

Lectionary for Weekday Mass (Lectionary for Mass)

Lectionary for Weekday Mass (Lectionary for Mass)

Portuguese missionary grammars in Asia, Africa and Brazil, 1550-1800

Portuguese missionary grammars in Asia, Africa and Brazil, 1550-1800

Remembering the Future

Remembering the Future

G-7 countries

G-7 countries

Official report (unrevised).

Official report (unrevised).

Giants and the Dodgers

Giants and the Dodgers

Financing metropolitan government

Financing metropolitan government

Results of aerothermodynamic and boundary layer transition testing of 0.0362-Scale X-38 (Rev 3.1) vehicle in NASA Langley 20-inch Mach 6 tunnel Download PDF EPUB FB2

Results of Aerothermodynamic and Boundary Layer Transition Testing of Scale X (Rev ) Vehicle in NASA Langley Inch Mach 6 Tunnel Article (PDF Available) November with 76 Reads BibTeX @INPROCEEDINGS{Tunnel97resultsof, author = {Nasa Langley -inch Mach Tunnel and Scott A. Berry and Thomas J. Horvath and V.

Eric Roback and George B. Williams and Nasa Langley -inch Mach Tunnel and Scott A. Berry and Thomas J. Horvath and V. Eric Roback and George B. Williams}, title = {Results of Aerothermodynamic and boundary layer transition testing of Scale X vehicle ?doi= BibTeX @MISC{Tunnel97resultsof, author = {Nasa Langley -inch Mach Tunnel and Scott A.

Berry and Scott A. Berry and Thomas J. Horvath and Jr. and Thomas J. Horvath and V. Eric Roback and V. Eric Roback and George B. Williams and George B. Williams}, title = {Results of Aerothermodynamic and Boundary Layer Transition Testing of Scale X (Rev ) Vehicle in NASA Langley Inch ?doi= Get this from a library.

Results of aerothermodynamic and boundary layer transition testing of Scale X (Rev ) vehicle in NASA Langley inch Mach Results of Aerothermodynamic and Boundary Layer Transition Testing of Scale X (Rev ) Vehicle in NASA Langley Inch Mach 6 Tunnel By Nasa Langley -inch Mach Tunnel, Scott A. Berry, Scott A.

Berry, Thomas J. Horvath, Jr., Thomas J. Horvath, V. Eric Roback, V. Eric Roback and George B. Williams and George B. Williams Results of Aerothermodynamic and boundary layer transition testing of Scale X vehicle. By Nasa Langley -inch Mach Tunnel, Scott A.

Berry, Thomas J. Horvath, V. Eric Roback and George B. WilliamsNasa Langley -inch Mach Tunnel, Scott A. Berry, Thomas J.

Horvath,   Results of Aerothermodynamic and Boundary-Layer Transition Testing of Scale X (Rev. ) Vehicle in NASA Langley Inch Mach 6 Tunnel.

NASA TM Berry SA, Bouslog SA, Brauckmann GJ, Caram JM. Shuttle Orbiter  › 百度文库 › 行业资料. Forced Boundary-Layer Transition on X (Hyper-X) in NASA LaRC Inch Mach 6 Air Tunnel_专业资料。 Since its founding, NASA has been dedicated to   Results & Analysis of Large Scale Article Testing in the Ames 60 MW Interaction Heating Arc Jet Facility.

Aerothermodynamic Testing of the Crew Exploration Vehicle in the LaRC Inch Mach 6 and Inch Mach 10 Tunnels. Shuttle Orbiter Experimental Boundary-Layer Transition Results with Isolated ://   21st Century Collection of NASA and NACA Dryden Technical Reports: X-Plane, SR, Space Shuttle, Hypersonic Research, Fighter Planes (Two CD-ROM Set) [News, World Spaceflight] on *FREE* shipping on qualifying offers.

21st Century Collection of NASA and NACA Dryden Technical Reports: X-Plane, SR, Space Shuttle, Hypersonic Research CONTENTSPreface vii Chapter 1 Design, Execution and Numerical Rebuilding of Shock Wave Boundary Layer Interaction Experiment in a Plasma Wind Tunnel 1 M. Di Clemente, E.

Trifoni, A. Martucci, S. Di Benedetto and M. Marini Chapter 2 The Mainz Vertical Wind Tunnel Facility– A Review of 25 Years of Laboratory Experiments on Cloud Physics and   data book occurs when experimental and computational results are in full agreement. (Recent overviews of aerothermodynamic computational capabilities are provided by Kumar et al., and Gnoffo et al., ) Flight experiments represent the third source of aerothermodynamic information (Fig.

These experi- Global surface heat transfer distributions were measured on and scale models of the proposed X configuration at Mach 10 in air. Aerothermodynamic and Boundary-Layer   A series of investigations of boundary-layer transition on a scale representation of the Mars Science Laboratory (MSL) vehicle were performed in the Langley Inch Mach-6 Air Tunnel.

To testify the applicability, the experiment results of the 70° sphere-cone model are used to validate the codes of k-ω-γ transition model. The base   The Reentry F flight provided boundary-layer transition data at Mach numbers up to 20 and altitudes down to km ( kft) (Wright & Zoby ).

CONCLUSIONS In spite of the decades of research into hypersonic flow, there are still many challenges to   boundary-layer transition correlation for X is described. Computational results used to complement the experimental program and to assess the vehicle aerodynamic and aerother-modynamic characteristics in flight are pre-sented.

The technical findings, impacts, and lessons learned from the studies are discussed. 1 Overview of the X Program X Slip Cast Ceramic Models The effect of surface roughness on hypersonic boundary layer transition was also investigated.

A method for simulating raised shuttle like tiles has been documented in Ref. The same technique was used to simulate model surface roughness in Mach 6 testing on the X AIAA PaperJanuary Berry, S.

A., et al., "Results of the Scale X (Rev ) Vehicle Aerothermodynamic and Boundary Layer Transition Test in the NASA Langley Inch Mach 6 Tunnel." NASA TMBerry, S.

A., et al., "X Experimental Aeroheating at Mach 6 and " AIAA Buck, G. M.,   The effects of boundary layer transition on the skin friction coefficient and the shear stress are incorporated in equations (6 - 13). Boundary layer transition is predicted using the correlation given by Bowcutt [2].

This relationship is expressed as a function of the edge Mach number, M e, in the following manner: logRe 6 exp Boundary layer height is another important PBL property that lends itself to remote sensing (e.g., Luo et al.

Many of these techniques are discussed in Wilczak et al. () and radar and lidar techniques are discussed in section ://. And one article by Berry et al. (b) related to objective 5: “Obtain data that can be used to develop empirical correlations for phenomena that resist analytical and/or numerical modeling, such as boundary-layer transition and turbulence modeling.” “In NASA initiated the Hyper-X program as part of an initiative to mature the   () Numerical prediction of turbulent boundary layer noise from a sharp‐edged flat plate.

International Journal for Numerical Methods in Fluids() Finite difference model of a four-electrode conductivity measurement ://CRITICAL HYPERSONIC AEROTHERMODYNAMIC PHENOMENA* CRITICAL HYPERSONIC AEROTHERMODYNAMIC PHENOMENA* Bertin, John J.; Cummings, Russell M.

The challenges in understanding hypersonic ï¬ ight are discussed and critical hypersonic aerothermodynamics issues are reviewed. The ability of current analytical methods, numerical methods, ground testing