As Part of a Multi-Phased Research Program, Known as the Benchmark Models Program, at the NASA Langley Research Center, Unsteady Pressure Measurements at Flutter Conditions of an Aeroelastic NACA 0012 Wing in Transonic Flows Were Obtained and Anafyzed. the Wing-Model Was Equipped with an Array of Eighty Pressure Transducers and Mounted on a Flexible Plunging/pitching Mechanism in the Langley Transonic Dynamics Tunnel. Streamwise Pressure Measurements at Two Spanwise Locations Were Acquired and Examined in the Time and Frequency Domains for a Mach Number Range between 0.5 and 0.88. the Objective Was to Obtain the Resulted Unsteady Pressure Distributions and Employ Them in Examining Associated Complicated Flow Developments Such as the Separat...
In the frame work of the JAXA-DLR cooperation, wind tunnel test for measuring unsteady aerodynamics ...
Steady and unsteady pressures were measured on a clipped delta wing with a 6-percent circular-arc ai...
The 2D unsteady shock motion on a NACA0012 aerofoil is examined in a transonic windtunnel. The aerof...
As Part of a Multi-Phased Research Program, Known as the Benchmark Models Program, at the NASA Langl...
The Structural Dynamics Div. at NASA-Langley has started a wind tunnel activity referred to as the B...
The Structural Dynamics Division at NASA Langley Research Center has started a wind tunnel activity ...
The NASA Langley Transonic Dynamics Tunnel has served as a unique national facility for aeroelastic ...
A computer code was developed to implement methods of analyzing unsteady pressure measurements acqui...
The Structural Dynamics Division at NASA LaRC has started a wind tunnel activity referred to as the ...
In the Transonic Wind Tunnel Goettingen, pitch oscillations were performed with a Lambda wing to stu...
In the Transonic Wind tunnel Göttingen, different test campaigns were performed with an oscillating ...
Four semispan wing model configurations were studied in the Transonic Dynamics Tunnel (TDT). The fir...
Unsteady pressure distributions measured in a transonic wind tunnel on a supercritical airfoil of 13...
Unsteady pressure distributions measured in a transonic wind tunnel on a supercritical airfoil of 13...
An extensive set of unsteady pressure data was acquired along the midspan of a modern transonic fan ...
In the frame work of the JAXA-DLR cooperation, wind tunnel test for measuring unsteady aerodynamics ...
Steady and unsteady pressures were measured on a clipped delta wing with a 6-percent circular-arc ai...
The 2D unsteady shock motion on a NACA0012 aerofoil is examined in a transonic windtunnel. The aerof...
As Part of a Multi-Phased Research Program, Known as the Benchmark Models Program, at the NASA Langl...
The Structural Dynamics Div. at NASA-Langley has started a wind tunnel activity referred to as the B...
The Structural Dynamics Division at NASA Langley Research Center has started a wind tunnel activity ...
The NASA Langley Transonic Dynamics Tunnel has served as a unique national facility for aeroelastic ...
A computer code was developed to implement methods of analyzing unsteady pressure measurements acqui...
The Structural Dynamics Division at NASA LaRC has started a wind tunnel activity referred to as the ...
In the Transonic Wind Tunnel Goettingen, pitch oscillations were performed with a Lambda wing to stu...
In the Transonic Wind tunnel Göttingen, different test campaigns were performed with an oscillating ...
Four semispan wing model configurations were studied in the Transonic Dynamics Tunnel (TDT). The fir...
Unsteady pressure distributions measured in a transonic wind tunnel on a supercritical airfoil of 13...
Unsteady pressure distributions measured in a transonic wind tunnel on a supercritical airfoil of 13...
An extensive set of unsteady pressure data was acquired along the midspan of a modern transonic fan ...
In the frame work of the JAXA-DLR cooperation, wind tunnel test for measuring unsteady aerodynamics ...
Steady and unsteady pressures were measured on a clipped delta wing with a 6-percent circular-arc ai...
The 2D unsteady shock motion on a NACA0012 aerofoil is examined in a transonic windtunnel. The aerof...