Calibration of the 11-By 11-Foot Transonic Wind Tunnel at the NASA Ames Research Center

Abstract

A series of calibration and flow survey tests were conducted in the 11-By 11-Foot Transonic Wind Tunnel following the modernization of the Unitary Plan Wind Tunnel at the NASA Ames Research Center. These tests included measurements of the static and total pressure which are required to develop the calibration tables used to compute the facility tunnel conditions and to correct the model airplane data for longitudinal buoyancy effects. Measurements of the total temperature, flow angle, and boundary layer characteristics were also made to provide an indication of the flow quality in the test section. Calibration parameters were determined for both test section wall configurations; slots normal for fullspan model testing and floor slots sealed for semi-span model testing.

Use of the Ames Check Standard Model for the Validation of Wall Interference Corrections

“…Therefore, the test matrix of the ACSM will be defined for the validation test such that two highly accurate long static pipe calibrations of the test section can be used (i) to set the uncorrected Mach numbers for the angle of attack sweeps and (ii) to determine clear tunnel buoyancy (see Ref. [9] for more details). Figure 3b shows the location of the long static pipe when the test section was originally calibrated with slots on the test section side walls, the ceiling, and the floor in "open" configuration.…”

Pressure-Sensitive Paint Measurements on the NASA Common Research Model in the NASA 11-ft Transonic Wind Tunnel

“…The wind tunnel is driven by a 3-stage compressor turned by a 176 MW electric motor system. A general description of the facility can be found at http://windtunnels.arc.nasa.gov/, and the facility is additionally described by Amaya & Kmak 17 as well as Amaya & Boone 18 , from which the present description is taken. Readers seeking more detailed information are referred to the NASA Ames UPWT test planning guide 19 .…”

The lagRST Model: a Turbulence Model for Non-Equilibrium Flows

“…As part of the CEV (now Orion) program, an experimental study 40,41 of the CEV geometry (shown in figure 21) was conducted at the Ames Unitary Plan Wind Tunnel (UPWT) 42 in the 11-foot Transonic Test Section and the 9X7 foot Supersonic Test Section. Test data were obtained for conditions at 0.3 ≤ M ∞ ≤ 2.5, 140…”