Open AccessUNCERTAINTY IN STATIC PRESSURE CORRECTION IN A SUBSONIC WIND TUNNEL
Author(s) -
M. L. C. C. Reis,
Olympio Mello,
M. Chisaki
Publication year - 2004
Publication title -
engenharia térmica
Language(s) - English
Resource type - Journals
ISSN - 1676-1790
DOI - 10.5380/reterm.v3i2.3533
Subject(s) - wind tunnel , static pressure , aerodynamics , mach number , subsonic and transonic wind tunnel , hypersonic wind tunnel , pressure measurement , dynamic pressure , supersonic wind tunnel , aerospace engineering , environmental science , mechanics , structural engineering , engineering , meteorology , physics , transonic
The static pressure p on the subsonic Wind Tunnel of the Aerodynamic Testing Laboratory
of the Institute of Aeronautics and Space IAE, Aerospace Technical Center CTA, is
measured using an absolute pressure sensor, located on the upper test section wall. This
measurement is not taken at the same location as the one where the model is mounted
during the actual wind tunnel test. This fact raises the need for a correction during data
reduction. The identification and evaluation of the associated error source is important
because the static pressure is an input quantity for the calculation of the total pressure pt,
Mach number M and density ρ during the test. The present paper is concerned with the
determination of the relationship between the static pressure measured on the tunnels
upper wall and that at the model location, and with the analysis of the uncertainty
propagation for the measured flow parameters.