Explore: Boundary Layer Thickness
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Books Results
Source: The Open Library
The Open Library Search Results
Search results from The Open Library
1High-area-ratio rocket nozzle at high combustion chamber pressure--experimental and analytical validation
By Robert S. Jankovsky
“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: Robert S. Jankovsky
- Language: English
- Number of Pages: Median: 51
- Publisher: ➤ National Technical Information Service, distributor - National Aeronautics and Space Administration, Glenn Research Center
- Publish Date: 1999
- Publish Location: ➤ [Springfield, Va - [Cleveland, Ohio]
“High-area-ratio rocket nozzle at high combustion chamber pressure--experimental and analytical validation” Subjects and Themes:
- Subjects: ➤ Combustion chambers - Turbulence - Heat transfer - Boundary layer thickness - Heat flux - Rocket nozzles - Flux (Rate) - Pressure distribution - Pressure measurement - Measurement - Transmission - Boundary layer - Rocket engines - Nozzles - Pressure - Heat - Aerodynamic load
Edition Identifiers:
- The Open Library ID: OL17591578M - OL15556459M - OL18137669M - OL20703973M - OL17136005M
- Online Computer Library Center (OCLC) ID: 42885454
Access and General Info:
- First Year Published: 1999
- 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.
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2Analysis of gas turbine rotor blade tip and shroud heat transfer
By A. A. Ameri
“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: A. A. Ameri
- Language: English
- Publisher: ➤ National Aeronautics and Space Administration - National Technical Information Service, distributor
- Publish Date: 1996 - 1998
- Publish Location: ➤ [Washington, DC - Springfield, Va
“Analysis of gas turbine rotor blade tip and shroud heat transfer” Subjects and Themes:
- Subjects: ➤ Gas turbines - Heat transfer - Blade tips - Shrouds - Boundary layer thickness - Navier-Stokes equation
Edition Identifiers:
- The Open Library ID: OL17593523M - OL15505238M
- Online Computer Library Center (OCLC) ID: 41970343
Access and General Info:
- First Year Published: 1996
- Is Full Text Available: No
- Is The Book Public: No
- Access Status: No_ebook
Online Marketplaces
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3Effect of pressure gradients on plate response and radiation in a supersonic turbulent boundary layer
By Abdelkader Frendi
“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: Abdelkader Frendi
- Language: English
- Publisher: ➤ National Aeronautics and Space Administration, Langley Research Center - National Technical Information Service, distributor
- Publish Date: 1997
- Publish Location: Hampton, Va - [Springfield, Va
“Effect of pressure gradients on plate response and radiation in a supersonic turbulent boundary layer” Subjects and Themes:
- Subjects: Pressure gradients - Supersonic boundary layers - Turbulent boundary layer - High frequencies - Boundary layer thickness
Edition Identifiers:
- The Open Library ID: OL15505121M
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:
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Wiki
Source: Wikipedia
Wikipedia Results
Search Results from Wikipedia
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