Observations on three-dimensional nonlinear transonic wall-interference assessment and correction using semispan wing data

Abstract

The current interest in semispan wing testing generally places a greater demand on understanding wall-interference effects than is required in conventional sting-mounted model testing. As part of NASA Langley Research Center's development and evaluation of transonic wind-tunnel wall-interference assessment and correction (WIAC) ideas and methods, a nonlinear, three-dimensional, transonic WIAC code has been applied to four sets of transonic semispan wing data. These data were acquired nearly 20 years ago for the specific purpose of evaluating three-dimensional transonic computational fluid dynamics methodologies and included the measured wall (or near wall) pressure data that are required by the WIAC procedure. Previous papers have focused on the evaluation of nonlinear WIAC and other correction-method results by monitoring the correlations of corrected data and by using a Navier–Stokes code as an independent “free air” check. In the present paper, synoptic observations are made in regard to the transonic WIAC results and the factors that affect these results.