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 hotfilm 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. The temperature-compensated hot-film anemometers worked well over the Mach number and altitude range of the flight test. This paper describes the temperature-compensated hot-film anemometer and presents some of the data obtained during the flight test.


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    Title :

    Development of a temperature-compensated hot-film anemometer system for boundary-layer transition detection on high-performance aircraft


    Additional title:

    Entwicklung eines temperaturkompensierten Hitzfilm-Anemometers fuer die Grenzschichtuebergangserfassung an leistungsfaehigen Flugzeugen


    Contributors:

    Published in:

    Publication date :

    1985


    Size :

    6 Seiten, 7 Bilder, 2 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English