Development of a temperature-compensated hot-film anemometer system for boundary-layer transition detection on high-performance aircraft
Abstract
A hot-film constant-temperature anemometer (CTA) system was flight-tested and evaluated as a candidate sensor for determining boundary-layer transition on high-performance aircraft. The hot-film gage withstood an extreme flow environment characterized by shock waves and high dynamic pressures, although sensitivity to the local total temperature with the CTA indicated the need for some form of temperature compensation. A temperature-compensation scheme was developed and two CTAs were modified and flight-tested on the F-104/Flight Test Fixture (FTF) facility at a variety of Mach numbers and altitudes, ranging from 0.4 to 1.8 and 5,000 to 40,000 ft respectively.
- Publication:
-
ICIASF 1985 - 11th International Congress on Instrumentation in Aerospace Simulation Facilities
- Pub Date:
- 1985
- Bibcode:
- 1985icia.cong...86C
- Keywords:
-
- Autonomy;
- Boundary Layer Transition;
- Dynamic Pressure;
- Flight Tests;
- Hot-Film Anemometers;
- Mach Number;
- Shock Waves;
- Temperature Compensation;
- Transition Flow;
- Transonic Speed;
- Vibration;
- Aircraft Instruments;
- Flow Measurement;
- Laminar Boundary Layer;
- Turbulent Boundary Layer;
- Instrumentation and Photography