#
Mach number
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The concept ** Mach number** represents the subject, aboutness, idea or notion of resources found in **University of Oklahoma Libraries**.

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Mach number
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The concept

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

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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 comparison at mach numbers up to 0.92 of the calculated and experimental downwash and wake characteristics at various horizonatl tail heights behind a wing with 45 degrees of sweepback
- A longitudinal aerodynamic data repeatability study for a commercial transport model test in the National Transonic Facility
- A preliminary design study of supersonic through-flow fan inlets
- A shadowgraphic study of the national launch system's 1 1/2 stage vehicle configuration and heavy lift launch vehicle configuration
- A simple analytical aerodynamic model of Langley winged-cone aerospace plane concept
- Aeroacoustics of low Mach number flows : fundamentals, analysis, and measurement
- Aerodynamic and acoustic performance of high Mach number inlets
- Aerodynamic characteristics of the NACA 64-010 and 0010-1.10 40/1.051 airfoil sections at Mach numbers from 0.30 to 0.85 and Reynolds numbers from 4.0 x 10(exp. 6) to 8.0 x 10(exp. 6)
- Aerodynamic characteristics of two waverider-derived hypersonic cruise configurations
- Aeroelastic analysis of aircraft : wing and wing/fuselage configurations
- Aerothermodynamic measurement and prediction for modified orbiter at Mach 6 and 10
- Airfoil section characteristics at high angles of attack
- An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability below the Mach Number of Lift Divergence
- An Investigation of the damping in pitch characteristics of a ten degree cone
- An implementation of a chemical and thermal nonequilibrium flow solver on unstructured meshes and application to blunt bodies
- An investigation of several NACA 1-series inlets at Mach numbers from 0.4 to 1.29 for mass-flow ratios near 1.0
- Comparison of computational and experimental results for a supercritical airfoil
- Comparison of experimental surface pressure with theoretical predictions on twin two-dimensional convergent-divergent nozzles
- 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
- Control of unsteady separated flow associated with the dynamic stall of airfoils : final report, 95-09
- Data on shape and location of detached shock waves on cones and spheres
- Development of flow distortions in a full-scale nacelle inlet at mach numbers 0.63 and 1.6 to 2.0
- Effect of Reynolds number and Mach number on flow angularity probe sensitivity
- Effect of leading- and trailing-edge flaps on clipped delta wings with and without wing camber at supersonic speeds
- Effect of pressure gradient on first mode of instability in high-speed boundary layers
- Effect of thickness, camber, and thickness distribution on airfoil characteristics at Mach numbers up to 1.0
- Effects of Mach number up to 0.34 and Reynolds number up to 8,000,000 on the maximum lift coefficient of a wing of NACA 66-series airfoil sections
- Effects of independent variation of Mach and Reynolds numbers on the low-speed aerodynamic characteristics of the NACA 0012 airfoil section
- Effects of wing inboard plan-form modifications on lift, drag, and longitudinal stability at Mach numbers from 1.0 to 2.3 of a rocket-propelled free-flight model with a 52.5 degree sweptback wing of aspect ratio 3
- 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
- Euler/Navier-Stokes flow computations on flexible configurations for stability analysis
- Evaluation of F/A-18A HARV inlet flow analysis with flight data
- Evaluation of an ejector ramjet based propulsion system for air-breathing hypersonic flight
- Experimental aerodynamic characteristics for slender bodies with thin wings and tail at angles of attack from 0 ̊to 58 ̊and Mach from 0.6 to 2.0
- Experimental aerodynamic characteristics of a generic hypersonic accelerator configuration at Mach numbers 1.5 and 2.0
- Experimental and theoretical aerodynamic characteristics of two hypersonic cruise aircraft concepts at Mach numbers of 2.96, 3.96, and 4.63
- Experimental evaluation of wall Mach number distributions of the octagonal test section proposed for NASA Lewis Research Center's altitude wind tunnel
- Experimental investigation of base pressure on blunt-trailing-edge wings at supersonic velocities
- 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 pressure distributions and force coefficients on block forms for varying Mach number, Reynolds number, and yaw angle
- Experimental study of a generic high speed civil transport : tabulated data
- Flight and wind-tunnel measurements showing base drag reduction provided by a trailing disk for high Reynolds number turbulent flow for subsonic and transonic Mach numbers
- Flight calibration of four airspeed systems on a swept-wing airplane at Mach numbers up to 1.04 by the NACA radar-phototheodolite method
- Flight investigation at Mach numbers from 0.6 to 1.7 to determine drag and base pressures on a blunt-trailing-edge airfoil and drag of diamond and circular-arc airfoils at zero lift
- Flow coefficient behavior for boundary layer bleed holes and slots
- Free-flight measurements of the rolling effectiveness and drag of trailing-edge spoilers on a tapered sweptback wing at Mach numbers between 0.6 and 1.4
- Full flight envelope direct thrust measurement on a supersonic aircraft
- Fundamental study of flow field generated by rotorcraft blades
- Handbook of blunt-body aerodynamics : volume 1 - static stability.
- Handbook of inviscid sphere-cone flow fields and pressure distributions
- High resolution Euler solvers based on the space-time conservation element and solution element method
- High-resolution shock capturing scheme for high Mach number internal flow
- Highlights of unsteady pressure tests on a 14 percent supercritical airfoil at high Reynolds number, transonic condition
- 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 transition measurement on a 10?cone at Mach numbers from 0.5 to 2.0
- Investigation of a three-blade propeller in combination with two different spinners and an NACA D-type cowl at mach numbers up to 0.80
- Investigation of axially symmetric and two-dimensional multinozzles for producing supersonic streams
- Investigation of mixing a supersonic stream with the flow downstream of a wedge : NCC2-5190 final report
- Investigation of the NACA 4-(0)(03)-45 two-blade propeller at forward Mach numbers to 0.925
- Investigation of the NACA-4-(3)(08)-03 two-blade propeller at forward Mach numbers to 0.925
- Investigation of the aerodynamic characteristics at high supersonic Mach numbers of a family of delta wings having double-wedge sections with the maximum thickness at 0.18 chord
- Investigation of the aerodynamic characteristics in pitch and sideslip of a 45° swept-wing airplane configuration with various vertical locations of the wing and horizontal tail : Static lateral and directional stability ; Mach numbers of 1.41 and 2.01
- Investigation of three types of supersonic diffuser over a range of Mach numbers from 1.75 to 2.74
- 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
- Measurement of gust response on a turbine cascade
- Measurements of store forces and moments and cavity pressures for a generic store in and near a box cavity at subsonic and transonic speeds
- Molecular dynamics simulation of a piston driven shock wave in a hard sphere gas
- Multigrid strategies for viscous flow solvers on anisotropic unstructured meshes
- On the modulational instability of large amplitude waves in supersonic boundary layers
- On the propagation of small perturbations in two simple aeroelastic systems
- Performance of the 0.3-meter transonic cryogenic tunnel with air, nitrogen, and sulfer hexafluoride media under closed loop automatic control
- Pitot-pressure measurements in flow fields behind a rectangular nozzle with exhaust jet for free-stream mach numbers of 0.00, 0,60, and 1.20
- Preconditioning for numerical simulation of low Mach number three-dimensional viscous turbomachinery flows
- Research in robust control for hypersonic vehicles : progress report #1
- Screech tones of supersonic jets from bevelled rectangular nozzles
- Shock-tunnel combustor testing for hypersonic vehicles
- Simulation of two projectiles connected by a flexible tether
- Some effects of density and Mach number on the flutter speed of two uniform wings
- Some measurements of aerodynamic forces and moments at subsonic speeds on a rectangular wing of aspect ratio 2 oscillating about the midchord
- Splitting methods for low Mach number Euler and Navier-Stokes equations
- Standard nomenclature for airspeeds with tables and charts for use in calculation of airspeed
- Summary of drag coefficients of various shaped cylinders
- Supplementary note on modified-impact-theory calculations for bodies of revolution having minimum drag at hypersonic speeds
- Tests of a small-scale NACA submerged inlet at transonic Mach numbers
- The aerodynamic design and calibration of an asymmetric variable Mach number nozzle with sliding block for the Mach number range 1.27 to 2.75
- The aerodynamic design and calibration of an asymmetric variable Mach number nozzle with sliding block for the Mach number range 1.27 to 2.75
- The effects of viscosity on the stability of a trailing-line vortex in compressible flow
- The influence of Mach number and heat transfer on the turbulent flow wall law
- Thermal analysis and design of a cooling system for a Mach 14 nozzle : final report covering period February, 1986 to January, 1987
- Transonic aerodynamic characteristics of a proposed wing-body reusable launch vehicle concept
- Transonic shock oscillations and wing flutter calculated with an interactive boundary layer coupling method
- Turbulent boundary-layer temperature recovery factors in two-dimensional supersonic flow
- Two- and three-dimensional viscous computations of a hypersonic inlet flow
- Wind-tunnel calibration of a combined pitot-static tube and vane-type flow-angularity indicator at Mach numbers of 1.61 and 2.01
- Wing pressure distributions from subsonic tests of a high-wing transport model

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