The Collected Data for Ramp Function Tests on a NACA 23012 Aerofoil. Volume 1: Description and Pressure Data. G.U. Aero Report 8413

Summary: Here in is presented the collected data for tests in which a NACA 23012 aerofoil was subjected to a variety of ramp type displacements in pitch about the quarter chord position. The data clearly illustrates the effect of reduced frequency on the aerofoil characteristics and the chordal pressure distribution at the midspan position of the aerofoil model

Search for an invisibly decaying Higgs boson or dark matter candidates produced in association with a Z boson in pp collisions at root s=13 TeV with the ATLAS detector

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The Collected Data for Ramp Function Tests on a NACA 23012 Aerofoil. Volume 1: Description and Pressure Data. G.U. Aero Report 8413

Summary: Here in is presented the collected data for tests in which a NACA 23012 aerofoil was subjected to a variety of ramp type displacements in pitch about the quarter chord position. The data clearly illustrates the effect of reduced frequency on the aerofoil characteristics and the chordal pressure distribution at the midspan position of the aerofoil model

Collected Data for Oscillatory Pitch Tests on a NACA 23012 Aerofoil. Volume 1: Description and Pressure Data for a Reynolds Number 1.0 Million. G.U. Aero Report 8600

Summary: The collected data for a series of oscillatory pitch tests on a NACA 23012 aerofoil at low Mach number are presented. These tests have been conducted to establish the validity of a recently constructed wind tunnel based unsteady aerofoil test facility, and to provide a comprehensive aerodynamic data base for further aerofoil investigations. The aerofoil was oscillated in pitch about the quarter-chord axis for a variety of mean angles of incidence, amplitudes and reduced frequencies. The aerofoil aerodynamic characteristics were evaluated from the simultaneous measurement of the outputs from miniature pressure transducers distributed in a chordwise manner at the mid-span. These pressures were logged by a dedicated micro-computer based data acquisition system and recorded in real-time on a disc volume for subsequent analysis. Static stall of the NACA 23012 aerofoil was found to occur by the mechanism of abrupt trailing-edge separation, which became more abrupt with Increasing Reynolds number. The qualitative features observed during dynamic stall were found to be similar to those documented previously by other Investigators, Including the formation of a vortex disturbance shed from the aerofoil leading-edge region. Two features were noted that appeared to be prevalent at the low Mach numbers of the current tests. These were a pronounced non-linear lift overshoot during dynamic stall and the presence of strong secondary vortex shedding. The collected data are presented in two volumes. Volume 1 contains the test data at a Reynolds number of one million and Volume 2 contains data for a Reynolds number of 1.5 million

Collected Data for Oscillatory Pitch Tests on a NACA 23012 Aerofoil. Volume 1: Description and Pressure Data for a Reynolds Number 1.0 Million. G.U. Aero Report 8600

Summary: The collected data for a series of oscillatory pitch tests on a NACA 23012 aerofoil at low Mach number are presented. These tests have been conducted to establish the validity of a recently constructed wind tunnel based unsteady aerofoil test facility, and to provide a comprehensive aerodynamic data base for further aerofoil investigations. The aerofoil was oscillated in pitch about the quarter-chord axis for a variety of mean angles of incidence, amplitudes and reduced frequencies. The aerofoil aerodynamic characteristics were evaluated from the simultaneous measurement of the outputs from miniature pressure transducers distributed in a chordwise manner at the mid-span. These pressures were logged by a dedicated micro-computer based data acquisition system and recorded in real-time on a disc volume for subsequent analysis. Static stall of the NACA 23012 aerofoil was found to occur by the mechanism of abrupt trailing-edge separation, which became more abrupt with Increasing Reynolds number. The qualitative features observed during dynamic stall were found to be similar to those documented previously by other Investigators, Including the formation of a vortex disturbance shed from the aerofoil leading-edge region. Two features were noted that appeared to be prevalent at the low Mach numbers of the current tests. These were a pronounced non-linear lift overshoot during dynamic stall and the presence of strong secondary vortex shedding. The collected data are presented in two volumes. Volume 1 contains the test data at a Reynolds number of one million and Volume 2 contains data for a Reynolds number of 1.5 million

Collected Data for Sinusoidal Tests on a NACA 23012 Aerofoil. Volume 2: Pressure Data for a Reynolds Number of 1.5 Million. G.U. Aero Report 8600.

Summary: Herein is presented the collected data for tests in which a NACA 23012 aerofoil was subjected to oscillatory displacements in pitch about the quarter chord position. The data clearly illustrates the effect of reduced frequency on the aerofoil characteristics and the chordal pressure distribution at the midspan position of the aerofoil model. The data are presented in two volumes. This volume contains the test data for a Reynolds number of 1.5 x 10 6. For a full introduction and description of test procedure, see volume 1

Collected Data for Sinusoidal Tests on a NACA 23012 Aerofoil. Volume 2: Pressure Data for a Reynolds Number of 1.5 Million. G.U. Aero Report 8600.

Summary: Herein is presented the collected data for tests in which a NACA 23012 aerofoil was subjected to oscillatory displacements in pitch about the quarter chord position. The data clearly illustrates the effect of reduced frequency on the aerofoil characteristics and the chordal pressure distribution at the midspan position of the aerofoil model. The data are presented in two volumes. This volume contains the test data for a Reynolds number of 1.5 x 10 6. For a full introduction and description of test procedure, see volume 1

An investigation of three-dimensional stall development on NACA 23012 and NACA 0012 aerofoils

SIGLEAvailable from British Library Lending Division - LD:6015.42F(N--84-24554)(microfiche) / BLDSC - British Library Document Supply CentreGBUnited Kingdo

The effectiveness of monostatic and bistatic deployment of low frequency active sonar

The merits of monostatic and bistatic geometries in terms of the evasion probability for area and barrier searches were described. Detection probabilities were calculated by generating signal excess surfaces for a given sonar geometry. Acoustic modeling and operational analysis allowed to detect the impact of the problem on performance and effectiveness to be identified and quantified. The use of insight to consider acoustic and sonar performance, together with the development of a new tactical simulation, and the use of traditional analytic operational analysis techniques provided an effective integrated toolset for tackling the overall problem

The collected data for ramp function tests on a NACA 23012 aerofoil Volume 1: desciption and pressure data

SIGLEAvailable from British Library Lending Division - LD:7620.935(GU--AERO--8413) / BLDSC - British Library Document Supply CentreGBUnited Kingdo