Abstract
A correction method is described for half-model tests using wall pressures measured by longitudinal static pressure tubes and measured model forces. The Dirichlet problem for the Mach number correction is solved by a doublet-panel method and the flow angle corrections are obtained from the irrotational flow conditions. The method is applied to a transport aircraft half-model tested in the NAE perforated-wall wind tunnel. The Mach number and angle-of-attack corrections are presented as contour plots, allowing analysis of the effects of wallinduced gradients. In the range of normal operating lift coefficients, the corrected drag polar is shown to correlate well with data from full-model wind-tunnel tests and from the flight test aircraft.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.