Transfer of an existing continous circuit supersonic wind tunnel to Langley and its operation there as a blowdown tunnel is planned. Flow disturbance requirements in the supply section and methods for reducing the high level broad band acoustic disturbances present in typical blowdown tunnels are reviewed. Based on recent data and the analysis of two blowdown facilities at Langley, methods for reducing the total turbulence levels in the settling chamber, including both acoustic and vorticity modes, to less than one percent are recommended. The pertinent design details of the damping screens and honeycomb and the recommended minimum pressure drop across the porous components providing the required two orders of magnitude attenuation of acous...
The measurement of wind tunnel background pressure fluctuations in a Ludwig Tube is discussed. The m...
Measurements were made in the no. 1 7'x10' wind tunnel at NASA Ames Research Center, with the object...
The principal sources of flow unsteadiness in the circuit of a transonic wind tunnel are presented. ...
During the past years, there was an extensive program under way at the Langley Research Center to up...
Acoustic baffles installed in the extended settling chamber of the NAL 1.2-m tunnel have substantial...
The NASA-Langley Research Center 4 x 7 Meter Low Speed Wind Tunnel is currently being used for low s...
The acoustically significant features of the NASA 4X7m wind tunnel and the Dutch-German DNW low spee...
Aspects of the design and construction of the Laminar Flow Supersonic Wind Tunnel at the NASA-Ames F...
Measures to reduce the intensity of fan noise in the NASA Langley 30 ft x 60 ft subsonic wind tunnel...
The development of a large-scale anechoic test facility where large models of engine/airframe/high-l...
The feasibility of quiet, suction laminarized, high Reynolds number (Re) supersonic wind tunnel nozz...
The Boeing/AFOSR Mach-6 Quiet Tunnel has been achieving low-disturbance flow at high Reynolds number...
Unsteady Pressure Measurements In The NAL 1.2m Trisonic Wind Tunnel Indicated That Levels Of Test Se...
In the design of control system of a wind tunnel, it is important to understand the importance of op...
The 9- by 15-Foot Low Speed Wind Tunnel (9x15 LSWT) at NASA Glenn Research Center was built in 1969 ...
The measurement of wind tunnel background pressure fluctuations in a Ludwig Tube is discussed. The m...
Measurements were made in the no. 1 7'x10' wind tunnel at NASA Ames Research Center, with the object...
The principal sources of flow unsteadiness in the circuit of a transonic wind tunnel are presented. ...
During the past years, there was an extensive program under way at the Langley Research Center to up...
Acoustic baffles installed in the extended settling chamber of the NAL 1.2-m tunnel have substantial...
The NASA-Langley Research Center 4 x 7 Meter Low Speed Wind Tunnel is currently being used for low s...
The acoustically significant features of the NASA 4X7m wind tunnel and the Dutch-German DNW low spee...
Aspects of the design and construction of the Laminar Flow Supersonic Wind Tunnel at the NASA-Ames F...
Measures to reduce the intensity of fan noise in the NASA Langley 30 ft x 60 ft subsonic wind tunnel...
The development of a large-scale anechoic test facility where large models of engine/airframe/high-l...
The feasibility of quiet, suction laminarized, high Reynolds number (Re) supersonic wind tunnel nozz...
The Boeing/AFOSR Mach-6 Quiet Tunnel has been achieving low-disturbance flow at high Reynolds number...
Unsteady Pressure Measurements In The NAL 1.2m Trisonic Wind Tunnel Indicated That Levels Of Test Se...
In the design of control system of a wind tunnel, it is important to understand the importance of op...
The 9- by 15-Foot Low Speed Wind Tunnel (9x15 LSWT) at NASA Glenn Research Center was built in 1969 ...
The measurement of wind tunnel background pressure fluctuations in a Ludwig Tube is discussed. The m...
Measurements were made in the no. 1 7'x10' wind tunnel at NASA Ames Research Center, with the object...
The principal sources of flow unsteadiness in the circuit of a transonic wind tunnel are presented. ...