The two test sections of the Langley Unitary Plan Wind Tunnel were calibrated over the operating Mach number range from 1.47 to 4.63. The results of the calibration are presented along with a a description of the facility and its operational capability. The calibrations include Mach number and flow angularity distributions in both test sections at selected Mach numbers and tunnel stagnation pressures. Calibration data are also presented on turbulence, test-section boundary layer characteristics, moisture effects, blockage, and stagnation-temperature distributions. The facility is described in detail including dimensions and capacities where appropriate, and example of special test capabilities are presented. The operating parameters are ful...
Afterbody and nozzle pressures measured on a 1/12-scale model and in flight on a twin-jet fighter ai...
The Langley 6 by 28 inch transonic tunnel is described. The tunnel is a two dimensional facility wit...
An experimental and theoretical evaluation of the Langley 4- by 7- Meter Tunnel was conducted to det...
Performance data are presented for this tunnel, which has a Mach number range from 2.0 to 3.5. The t...
The Langley 14- by 22-foot Subsonic Tunnel is a closed circuit, single-return atmospheric wind tunne...
Performance data are presented for the tunnel, which has a Mach number range from 0.36 to 2.0. The t...
The initial evaluation of a large-chord, swept, supercritical airfoil incorporating an active lamina...
A computational procedure was developed which can be used to determine the flow properties in hypers...
A turbulent air motion measurement system (TAMMS) was integrated onboard the Lockheed 188 Electra ai...
Parameters affecting the performance of a scale model V/STOL wind tunnel were measured. These includ...
Data reduction and procedures for conducting force tests in a 20 inch Mach 6 tunnel are described. A...
The High Reynolds Number Wind Tunnel at the George C. Marshall Space Flight Center is described. The...
A one-dimensional distributed-parameter dynamic model of a cryogenic wind tunnel was developed which...
NASA is investigating the feasibility of modifying the 4x7m Wind Tunnel at the Langley Research Cent...
Transient starting characteristics of small scale blowdown wind tunnel test facilit
Afterbody and nozzle pressures measured on a 1/12-scale model and in flight on a twin-jet fighter ai...
The Langley 6 by 28 inch transonic tunnel is described. The tunnel is a two dimensional facility wit...
An experimental and theoretical evaluation of the Langley 4- by 7- Meter Tunnel was conducted to det...
Performance data are presented for this tunnel, which has a Mach number range from 2.0 to 3.5. The t...
The Langley 14- by 22-foot Subsonic Tunnel is a closed circuit, single-return atmospheric wind tunne...
Performance data are presented for the tunnel, which has a Mach number range from 0.36 to 2.0. The t...
The initial evaluation of a large-chord, swept, supercritical airfoil incorporating an active lamina...
A computational procedure was developed which can be used to determine the flow properties in hypers...
A turbulent air motion measurement system (TAMMS) was integrated onboard the Lockheed 188 Electra ai...
Parameters affecting the performance of a scale model V/STOL wind tunnel were measured. These includ...
Data reduction and procedures for conducting force tests in a 20 inch Mach 6 tunnel are described. A...
The High Reynolds Number Wind Tunnel at the George C. Marshall Space Flight Center is described. The...
A one-dimensional distributed-parameter dynamic model of a cryogenic wind tunnel was developed which...
NASA is investigating the feasibility of modifying the 4x7m Wind Tunnel at the Langley Research Cent...
Transient starting characteristics of small scale blowdown wind tunnel test facilit
Afterbody and nozzle pressures measured on a 1/12-scale model and in flight on a twin-jet fighter ai...
The Langley 6 by 28 inch transonic tunnel is described. The tunnel is a two dimensional facility wit...
An experimental and theoretical evaluation of the Langley 4- by 7- Meter Tunnel was conducted to det...