#
Mach number
Resource Information
The concept ** Mach number** represents the subject, aboutness, idea or notion of resources found in **University of Missouri-St. Louis Libraries**.

The Resource
Mach number
Resource Information

The concept

**Mach number**represents the subject, aboutness, idea or notion of resources found in**University of Missouri-St. Louis Libraries**.- Label
- Mach number

- Source
- nasat

## Context

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- [Flight and static exhaust flow properties of an F110-GE-129 engine in an F-16XL airplane during acoustic tests]
- A correlation between flight-determined derivatives and wind-tunnel data for the X-24B research aircraft
- A fan pressure ratio correlation in terms of Mach number and Reynolds number for the Langley 0.3-Meter Transonic Cryogenic Tunnel
- 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
- Acoustic performance of the GEAE UPS research fan in the NASA Glenn 9- by 15-foot low-speed wind tunnel
- Acoustically excited heated jets
- Aerodynamic characteristics of two waverider-derived hypersonic cruise configurations
- Aerodynamic effects of simulated ice accretion on a generic transport model
- Aeropropulsive characteristics of isolated combined turbojet/ramjet nozzles at Mach numbers from 0 to 1.20
- Aerothermodynamic measurement and prediction for modified orbiter at Mach 6 and 10
- An experimental evaluation of the performance of two combination pitot pressure probes
- An interactive software for conceptual wing flutter analysis and parametric study
- An inviscid computational study of three '07 Mars lander aeroshell configurations over a Mach number range of 2.3 to 4.5
- Analysis of buzz in a supersonic inlet
- Analytical MHD theory for Earth's bow shock at low Mach numbers
- Automated boundary conditions for wind tunnel simulations
- Coherent large-scale structures in high Reynolds number supersonic jets
- Cold-air investigation of first state of 4 1/2-stage, fan-drive turbine with average stage-loading factor of 4.66
- Comparison of Theodorsen's unsteady aerodynamic forces with double lattice generalized aerodynamic forces
- Comparison of the aeroacoustics of two small-scale supersonic inlets : final technical report, NASA contract #--NAG 3-1539
- Computational aeroservoelastic analysis with an Euler-based unsteady flow solver : NASA-Ames university consortium cooperative agreement no. NCC2-5105, final research summary for the period: 1 November 1994 - 31 January 1997
- Consistent initial conditions for the DNS of compressible turbulence
- Courant number and mach number insensitive CE/SE euler solvers
- Design of a slotted, natural-laminar-flow airfoil for a transport aircraft
- Determination of sun angles for observations of shock waves on a transport aircraft : David F. Fisher ... [et al.]
- Development of a flush airdata sensing system on a sharp-nosed vehicle for flight at Mach 3 to 8
- Development of a flush airdata sensing system on a sharp-nosed vehicle for flight at Mach 3 to 8
- Effectiveness of a wedge probe to measure sonic boom signatures in a supersonic wind tunnel
- Effects of wing sweep on boundary-layer transition for a smooth F-14A wing at Mach numbers from 0.700 to 0.825
- 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
- Equivalent longitudinal area distributions of the B-58 and XB-70-1 airplanes for use in wave drag and sonic boom calculations
- Euler/Navier-Stokes flow computations on flexible configurations for stability analysis
- Evaluation of a flow direction probe and a pilot-static probe on the F-14 airplane at high angles of attack and sideslip
- Evaluation of an ejector ramjet based propulsion system for air-breathing hypersonic flight
- Evaluation of an ejector ramjet based propulsion system for air-breathing hypersonic flight
- Evaluation of the low-speed stability and control characteristics of a Mach 5.5 waverider concept
- Experimental and theoretical study of flow fields around ducted-nacelle models
- Experimental and theoretical study of flow fields around ducted-nacelle models
- Experimental and theoretical study of longitudinal aerodynamic characteristics of delta and double-delta wings at Mach numbers of 1.60, 1.90, and 2.16
- Experimental and theoretical study of the longitudinal aerodynamic characteristics of delta and double-delta wings at mach numbers of 1.60, 1.90, and 2.16
- Experimental investigation of aeroelastic deformation of slender wings at supersonic speeds using a video model deformation measurement technique
- Experimental investigation of plume-induced flow separation on the National Launch System 11/2-stage launch vehicle : 32nd Aerospace Sciences meeting & exhibit, January 10-13, 1994, Reno, NV
- Experimental investigation of the flow field in a transonic, axial flow compressor, with respect to the development of blockage and loss
- Experimental investigation of unsteady shock wave turbulent boundary layer interactions about a blunt fin
- Experimental measurements of sonic boom signatures using a continuous data acquisition technique
- Experimental surface pressure data obtained on 65 Â° delta wing across Reynolds number and Mach number ranges
- Experimental surface pressure data obtained on 65 ĚŠdelta wing across Reynolds number and Mach number ranges
- 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
- Flow quality and operational enhancements in the NASA Lewis 8- by 6-Foot Supersonic Wind Tunnel
- Fluctuating pressures measured beneath a high-temperature, turbulent boundary layer on a flat plate at a Mach number of 5
- Full flight envelope direct thrust measurement on a supersonic aircraft
- Fuselage design for a specified Mach-sliced area distribution
- High resolution Euler solvers based on the space-time conservation element and solution element method
- Impingement of boundary-reflected disturbances originating at the nose of a body of revolution in the Langley Research Center 16-foot transonic tunnel
- Impingement of boundary-reflected disturbances originating at the nose of a body of revolution in the Langley Research Center 16-foot transonic tunnel
- In-flight boundary-layer measurements on a hollow cylinder at a Mach number of 3.0
- Instabilities and subharmonic resonances in subsonic heated round jets
- Interaction of a shock with a longitudinal vortex
- Invariance of hypersonic normal force coefficients with Reynolds number and determination of inviscid wave drag from laminar experimental results
- Investigation of active flow control to improve aerodynamic performance of oscillating wings
- Investigation of convergent-divergent nozzles applicable to reduced-power supersonic cruise aircraft
- Investigation of mixing a supersonic stream with the flow downstream of a wedge : NCC2-5190 final report
- Inviscid flow computations of the shuttle orbiter for Mach 10 and 15 and angle of attack 40 to 60 degrees
- Large-scale Advanced Propfan (LAP) performance, acoustic and weight estimation, January, 1984
- Local flow conditions for proplusion experiments on the F-15B Propulsion Flight Test Fixture
- Low speed calibration of the NASA Lewis Research Center 8- by 6-foot supersonic wind tunnel (1995 test) : under contract NAS3-27186
- Mach 5 inlet CFD and experimental results
- Mach 6 flow field surveys beneath the forebody of an airbreathing missile
- Mach number effects on turbine blade transition length prediction
- NASA Glenn 1-by 1-foot supersonic wind tunnel user manual
- NASA Glenn 1-by 1-foot supersonic wind tunnel user manual
- Natural laminar flow flight experiments on a swept wing business jet- boundary layer stability analyses
- Near-exit pressure fluctuations in jets from circular and rectangular nozzles
- Near-optimal operation of dual-fuel launch vehicles
- Nonlinear aerodynamic wing design
- Nozzle plume/shock interaction experimental and computational sonic boom analyses from the NASA Ames 9-by 7-foot supersonic wind tunnel
- Numerical simulation of jet aerodynamics using the three-dimensional Navier-Stokes code PAB3D
- Numerical simulation of scramjet inlet flow fields
- Numerical simulation of the generation of axisymmetric mode jet screech tones
- On the correlation of plume centerline velocity decay of turbulent acoustically excited jets : prepared for the 11th Aeroacoustics Conference sponsored by the American Institute of Aeronautics and Astronautics, Sunnyvale, California, October 19-21, 1987
- On the coupling between a supersonic boundary layer and a flexible surface : final report
- On the propagation of small perturbations in two simple aeroelastic systems
- Overview of HATP experimental aerodynamics data for the baseline F/A-18 configuration : High-Angle-of-Attack Technology Conference
- Parametric investigation of single-expansion-ramp nozzles at Mach numbers from 0.60 to 1.20
- Porous and microporous honeycomb composites as potential boundary-layer bleed materials
- Preconditioning for numerical simulation of low Mach number three-dimensional viscous turbomachinery flows
- Predictions of supersonic jet mixing and shock-associated noise compared with measured far-field data
- Progress in FavrĂ©-Reynolds stress closures for compressible flows
- R4 airfoil data corrected for sidewall boundary-layer effects in the Langley 0.3-meter transonic cryogenic tunnel
- Research on supersonic inlet bleed
- Results of aeroheating DFI and ET design-data test on a 0.0175-scale model 60-OTS conducted in the Von Karman gas dynamics facility (VKF) 40-inch supersonic and the 50-inch hypersonic wind tunnels A & C (IH-97A/B/C
- Robust airfoil optimization to achieve consistent drag reduction over a mach range
- Shock tunnel studies of scramjet phenomena : final technical report, NAGW-674
- Slot nozzle effects for reduced sonic boom on a generic supersonic wing section
- Summary of work on shock wave feature extraction in 3-D datasets
- Supersonic aerodynamic characteristics of some reentry concepts for angles of attack to 900
- The stability of radiatively cooling jets, II, Nonlinear evolution
- The stability of two-dimensional wakes and shear-layers at high Mach numbers
- Transonic shock oscillations and wing flutter calculated with an interactive boundary layer coupling method
- Transonic shock oscillations and wing flutter calculated with an interactive boundary layer coupling method
- Transonic shock oscillations and wing flutter calculated with an interactive boundary layer coupling method : EUROMECH-Colloquium 349, simulation of fluid-structure interaction in aeronautics, GĂ¶ttingen, Germany, September 16-18, 1996
- Transonic wind tunnel test of a 14% thick oblique wing
- Uncertainty analysis of the NASA Glenn 8X6 supersonic wind tunnel
- Wind tunnel investigation of passive vortex control and vortex-tail interactions on a slender wing at subsonic and transonic speeds
- 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

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