Explore: Boundary Layer Thickness

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Source: The Open Library

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1High-area-ratio rocket nozzle at high combustion chamber pressure--experimental and analytical validation

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“High-area-ratio rocket nozzle at high combustion chamber pressure--experimental and analytical validation” Metadata:

  • Title: ➤  High-area-ratio rocket nozzle at high combustion chamber pressure--experimental and analytical validation
  • Author:
  • Language: English
  • Number of Pages: Median: 51
  • Publisher: ➤  National Technical Information Service, distributor - National Aeronautics and Space Administration, Glenn Research Center
  • Publish Date:
  • Publish Location: ➤  [Springfield, Va - [Cleveland, Ohio]

“High-area-ratio rocket nozzle at high combustion chamber pressure--experimental and analytical validation” Subjects and Themes:

Edition Identifiers:

Access and General Info:

  • First Year Published: 1999
  • Is Full Text Available: No
  • Is The Book Public: No
  • Access Status: No_ebook

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    2Analysis of gas turbine rotor blade tip and shroud heat transfer

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    “Analysis of gas turbine rotor blade tip and shroud heat transfer” Metadata:

    • Title: ➤  Analysis of gas turbine rotor blade tip and shroud heat transfer
    • Author:
    • Language: English
    • Publisher: ➤  National Aeronautics and Space Administration - National Technical Information Service, distributor
    • Publish Date:
    • Publish Location: ➤  [Washington, DC - Springfield, Va

    “Analysis of gas turbine rotor blade tip and shroud heat transfer” Subjects and Themes:

    Edition Identifiers:

    Access and General Info:

    • First Year Published: 1996
    • Is Full Text Available: No
    • Is The Book Public: No
    • Access Status: No_ebook

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    3Effect of pressure gradients on plate response and radiation in a supersonic turbulent boundary layer

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    “Effect of pressure gradients on plate response and radiation in a supersonic turbulent boundary layer” Metadata:

    • Title: ➤  Effect of pressure gradients on plate response and radiation in a supersonic turbulent boundary layer
    • Author:
    • Language: English
    • Publisher: ➤  National Aeronautics and Space Administration, Langley Research Center - National Technical Information Service, distributor
    • Publish Date:
    • Publish Location: Hampton, Va - [Springfield, Va

    “Effect of pressure gradients on plate response and radiation in a supersonic turbulent boundary layer” Subjects and Themes:

    Edition Identifiers:

    Access and General Info:

    • First Year Published: 1997
    • Is Full Text Available: No
    • Is The Book Public: No
    • Access Status: No_ebook

    Online Access

    Downloads Are Not Available:

    The book is not public therefore the download links will not allow the download of the entire book, however, borrowing the book online is available.

    Online Borrowing:

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      Find Effect of pressure gradients on plate response and radiation in a supersonic turbulent boundary layer at online marketplaces:



      Wiki

      Source: Wikipedia

      Wikipedia Results

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      Boundary layer thickness

      characterize the thickness and shape of boundary layers formed by fluid flowing along a solid surface. The defining characteristic of boundary layer flow is that

      Boundary layer

      Boundary layer separation Boundary-layer thickness Thermal boundary layer thickness and shape Boundary layer suction Boundary layer control Boundary microphone

      Thermal boundary layer thickness and shape

      the boundary layer of the fluid that is the driving force determining thermal boundary layer thickness. Thus the thermal boundary layer thickness for

      Blasius boundary layer

      mechanics, a Blasius boundary layer (named after Paul Richard Heinrich Blasius) describes the steady two-dimensional laminar boundary layer that forms on a

      Stokes problem

      Stokes second problem or sometimes referred to as Stokes boundary layer or Oscillating boundary layer is a problem of determining the flow created by an oscillating

      Dynamic similarity (Reynolds and Womersley numbers)

      convective inertial boundary layer thickness that can form, and the Womersley number is used to calculate the transient inertial boundary thickness that can form

      Falkner–Skan boundary layer

      Falkner–Skan boundary layer (named after Victor Montague Falkner and Sylvia W. Skan) describes the steady two-dimensional laminar boundary layer that forms

      Prandtl number

      \delta _{t}} is the thermal boundary layer thickness and δ {\displaystyle \delta } is the momentum boundary layer thickness. For incompressible flow over

      Vortex

      boundary layer does grow beyond this critical boundary layer thickness then separation will occur which will generate vortices. This boundary layer separation

      Active layer

      the active layer, with the result that permafrost environments tend to be very poorly drained and boggy. The thickness of the active layer is the average