21st Congress of International Council of the Aeronautical Sciences, Melbourne, Australia, 13-18 September, 1998
Paper ICAS-98-3.3.3

IN-FLIGHT SHOCK DETECTION USING HOT FILM SENSORS AND CONSTANT VOLTAGE ANEMOMETER SYSTEM

Mangalam S., Sarma G. R., Moes T. M.*
Tao Systems, USA; * NASA, USA

Keywords: hot-films, shock detection, in-flight

Transonic shock locations were successfully detected in flight tests conducted at NASA Dryden Flight Research Center on a F-1SB aircraft using a 1O"-chord modified NACA 0021 airfoil instrumented with hot-film sensors. The hot-film sensors were operated by a bank of automated constant voltage anemometer system installed in the Flight Test Fixture (FTF). The airfoil was designed to generate transonic shocks at speeds above Mach 0.7. Shock location estimated by in-flight pressure measurements were used to correlate the hot-film measurements. Hot-film measurements were also used to de(ermine the state of the boundary layer (laminar, transitional, or turbulent).

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