Pressure distribution
Resource Information
The concept Pressure distribution represents the subject, aboutness, idea or notion of resources found in University of Missouri-St. Louis Libraries.
The Resource
Pressure distribution
Resource Information
The concept Pressure distribution represents the subject, aboutness, idea or notion of resources found in University of Missouri-St. Louis Libraries.
- Label
- Pressure distribution
- Source
- nasat
101 Items that share the Concept Pressure distribution
Context
Context of Pressure distributionSubject of
No resources found
No enriched resources found
- Wing leading edge joint laminar flow tests
- A comparison of pressure measurements between a full-scale and a 1/6-scale F/A-18 twin tail during buffet
- A comparison of pressure measurements between a full-scale and a 1/6-scale F/A-18 twin tail during buffet
- A non-cut cell immersed boundary method for use in icing simulations
- A wind tunnel investigation of three NACA 1-series inlets at Mach numbers up to 0.92
- A wind tunnel investigation of three NACA 1-series inlets at Mach numbers up to 0.92
- Aeroacoustic characteristics of a rectangular multi-element supersonic jet mixer-ejector nozzle
- Aerodynamic investigation of incidence angle effects in a large scale transonic turbine cascade
- An airfoil flutter model suspension system to accommodate large static transonic airloads
- An approach to the constrained design of natural laminar flow airfoils
- An approach to the constrained design of natural laminar flow airfoils : a thesis ...
- An experimental investigation of propfan installations on an unsewpt supercritical wing at transonic Mach numbers
- Analysis of two-phase flow in damper seals for cryogenic turbomachinery : NASA grant NAG3-1434 : final report to NASA Lewis Research Center
- Analysis of two-phase flow in damper seals for cryogenic turbopumps : NASA grant NAG3-1434 : final report to NASA Lewis Research Center
- Application of a third order upwind scheme to viscous flow over clean and iced wings : 32nd Aerospace Sciences Meeting & Exhibit, January 10-13, 1994/Reno, NV
- Application of laminar flow control to supersonic transport configurations
- Application of the pressure sensitive paint technique to steady and unsteady flow
- Approximate pressure distribution in an accelerating launch-vehicle fuel tank
- Background pressure profiles for sonic boom vehicle testing in the NASA Glenn 8- by 6-foot supersonic wind tunnel
- Bidirectional brush seals : post-test analysis
- Bidirectional brush seals--post-test analysis
- Calculation of multistage turbomachinery using steady characteristic boundary conditions
- Characterization of cavity flow fields using pressure data obtained in the Langley 0.3-meter transonic cryogenic tunnel
- Cold-flow model tests to determine static performance of a NASA one-sided ejector nozzle system
- Computation of lifting wing-flap configurations : NASA grant NCC2-5070, final report ... funding dates: July 1, 1994 to June 30, 1995
- Computer code study of asteroid entry into Venusian atmosphere : pressure and density fields : final report : contract NASW-4992
- Contraction design for small low-speed wind tunnels
- Coupling of low speed fan stator vane unsteady pressures to duct modes : measured versus predicted
- Cure cycle design methodology for fabricating reactive resin matrix fiber reinforced composites : a protocol for producing void-free quality laminates
- DBD plasma actuators for flow control in air vehicles and jet engines : simulation of flight conditions in test chambers by density matching
- DBD plasma actuators for flow control in air vehicles and jet engines : simulation of flight conditions in test chambers by density matching
- Design and use of a guided weight impactor to impart barely visible impact damage
- Design concepts for cooled ceramic composite turbine vane
- Detailed pressure distribution measurements obtained on several configurations of an aspect-ratio-7 variable twist wing
- Dynamic inlet distortion prediction with a combined computational fluid dynamics and distortion synthesis approach
- Effect of actuated forebody strakes on the forebody aerodynamics of the NASA F-18 HARV
- Effect of actuated forebody strakes on the forebody aerodynamics of the NASA F-18 HARV
- Effect of sweep on cavity flow fields at subsonic and transonic speeds
- Effects of velocity profile and inclination on dual-jet-induced pressures on a flat plate in a crosswind
- Effects of wing sweep on in-flight boundary-layer transition for a laminar flow wing at Mach numbers from 0.60 to 0.79
- Effects of yaw angle and Reynolds number on rectangular-box cavities at subsonic and transonic speeds
- Enhanced design of turbo-jet LPT by separation control using phased plasma actuators
- Evaluation of 3D inverse code using rotor 67 as test case : final report
- Exhaust plume effects on sonic boom for a delta wing and a swept wing-body model
- Experimental and computational investigation of lift-enhancing tabs on a multi-element airfoil
- Experimental effects of wing location on wing-body pressures at supersonic speeds
- Experimental investigation of unsteady flows at large incidence angles in a linear oscillating cascade
- Experimental investigation of unsteady flows at large incidence angles in a linear oscillating cascade
- Experimental optimization methods for multi-element airfoils : final report
- Experimental surface pressure data obtained on 65 ̊delta wing across Reynolds number and Mach number ranges
- F-15B/flight test fixture II : a test bed for flight research
- F-18 High Alpha Research Vehicle surface pressures : initial in-flight results and correlation with flow visualization and wind-tunnel data
- Flight wing surface pressure and boundary-layer data report from the F-111 smooth variable-camber supercritical mission adaptive wing
- Flight wing surface pressure and boundary-layer data report from the F-111 smooth variable-camber supercritical mission adaptive wing
- Flow processes in overexpanded chemical rocket nozzles, Part 2, Side loads due to asymmetric separation
- Heat transfer and flow on the first stage blade tip of a power generation gas turbine
- High-area-ratio rocket nozzle at high combustion chamber pressure--experimental and analytical validation
- In-flight boundary-layer transition on a large flat plate at supersonic speeds
- Interaction of sound from supersonic jets with nearby structures
- Interaction of two-dimensional transverse jet with a supersonic mainstream
- Large eddy simulation of transonic flow field in NASA rotor 37
- Large-scale advanced propeller blade pressure distributions : predictions and data
- Laser scanning system for pressure and temperature paints : final report, NASA NCC2-5115
- Low speed calibration of the NASA Lewis Research Center 8- by 6-foot supersonic wind tunnel (1995 test) : under contract NAS3-27186
- Measured pressure distributions inside nonaxisymmetric nozzles with partially deployed thrust reversers
- Measurements of heat transfer, flow, and pressures in a simulated turbine blade internal cooling passage
- Measurements of supersonic wing tip vortices : 18th AIAA Aerospace Ground Testing Conference, June 20-23, 1994/Colorado Springs, CO
- Mir cooperative solar array flight performance data and computational analysis
- Numerical analysis of base flowfield for a four-engine clustered nozzle configuration
- Onset of condensation effects with an NACA 0012-64 airfoil tested in the Langley 0.3-meter transonic cryogenic tunnel
- Prediction of sound fields in acoustical cavities using the boundary element method
- Prediction of unsteady blade surface pressures on an advanced propeller at an angle of attack
- Pressure distribution for the wing of the YAV-8B airplane : with and without pylons
- Pressure distributions from high Reynolds number tests of a Boeing BAC I airfoil in the Langley 0.3-Meter Transonic Cryogenic Tunnel
- Pressure-distribution measurements on a transonic low-aspect ratio wing
- Prevention of over-pressurization during combustion in a sealed chamber
- Reliability of COPVs accounting for margin of safety on design burst
- Results of design studies and wind tunnel tests of an advanced high lift system for an energy efficient transport
- Rocket-based combined cycle engine technology development : inlet CFD validation and application
- Simulation of turbine tone noise generation using a turbomachinery aerodynamics solver
- Solar rocket plume/mirror interactions
- Static internal performance of a two-dimensional convergent-divergent nozzle with external shelf
- Structural analysis and optimization of a composite fan blade for future aircraft engine
- Subsonic analysis of 0.04-scale F-16XL models using an unstructured Euler code
- Summary of pressure gain combustion research at NASA
- Supersonic wind tunnel tests of a half-axisymmetric 12°-spike inlet to a rocket-based combined-cycle propulsion system
- Supersonic wind tunnel tests of a half-axisymmetric 12°-spike inlet to a rocket-based combined-cycle propulsion system
- The effect of vortex generators on a jet in a cross-flow
- The fast scattering code (FSC) : validation studies and program guidelines
- Three-dimensional flow field measurements in a transonic turbine
- Three-dimensional flow field measurements in a transonic turbine cascade
- USSAERO version D computer program development using ANSI standard FORTRAN 77 and DI-3000 graphics
- Unsteady potential flow past a propeller blade section
- Validation of a CFD methodology for variable speed power turbine relevant conditions
- Vibroacoustic response of pad structures to space shuttle launch acoustic loads
- Wind tunnel measured effects on a twin-engine short-haul transport caused by simulated ice accretions : data report
- Wind tunnel measured effects on a twin-engine short-haul transport caused by simulated ice accretions : data report
- Wind tunnel results of the aerodynamic performance of a 1/8-scale model of a twin-engine transport with multi-element wing
- Wind tunnel results of the aerodynamic performance of a 1/8-scale model of a twin-engine transport with multi-element wing
- Wind-tunnel investigation of aerodynamic characteristics and wing pressure distributions of an airplane with variable-sweep wings modified for laminar flow
- Wing leading edge joint laminar flow tests
Embed
Settings
Select options that apply then copy and paste the RDF/HTML data fragment to include in your application
Embed this data in a secure (HTTPS) page:
Layout options:
Include data citation:
<div class="citation" vocab="http://schema.org/"><i class="fa fa-external-link-square fa-fw"></i> Data from <span resource="http://link.umsl.edu/resource/tB85Ko_K8D8/" typeof="CategoryCode http://bibfra.me/vocab/lite/Concept"><span property="name http://bibfra.me/vocab/lite/label"><a href="http://link.umsl.edu/resource/tB85Ko_K8D8/">Pressure distribution</a></span> - <span property="potentialAction" typeOf="OrganizeAction"><span property="agent" typeof="LibrarySystem http://library.link/vocab/LibrarySystem" resource="http://link.umsl.edu/"><span property="name http://bibfra.me/vocab/lite/label"><a property="url" href="http://link.umsl.edu/">University of Missouri-St. Louis Libraries</a></span></span></span></span></div>
Note: Adjust the width and height settings defined in the RDF/HTML code fragment to best match your requirements
Preview
Cite Data - Experimental
Data Citation of the Concept Pressure distribution
Copy and paste the following RDF/HTML data fragment to cite this resource
<div class="citation" vocab="http://schema.org/"><i class="fa fa-external-link-square fa-fw"></i> Data from <span resource="http://link.umsl.edu/resource/tB85Ko_K8D8/" typeof="CategoryCode http://bibfra.me/vocab/lite/Concept"><span property="name http://bibfra.me/vocab/lite/label"><a href="http://link.umsl.edu/resource/tB85Ko_K8D8/">Pressure distribution</a></span> - <span property="potentialAction" typeOf="OrganizeAction"><span property="agent" typeof="LibrarySystem http://library.link/vocab/LibrarySystem" resource="http://link.umsl.edu/"><span property="name http://bibfra.me/vocab/lite/label"><a property="url" href="http://link.umsl.edu/">University of Missouri-St. Louis Libraries</a></span></span></span></span></div>
