Infrared thermography was used to obtain data on the state of the boundary layer of a natural laminar flow airfoil in supersonic flight. In addition to the laminar-to-turbulent transition boundary, the infrared camera was able to detect shock waves and present a time dependent view of the flow field. A time dependent heat transfer code was developed to predict temperature distributions on the test subject and any necessary surface treatment. A commercially available infrared camera was adapted for airborne use in this application. Readily available infrared technology has the capability to provide detailed visualization of various flow phenomena in subsonic to hypersonic flight regimes.
Visualization of In-Flight Flow Phenomena Using Infrared Thermography
International Symposium on Flow Visualization ; 2000 ; Edinburgh, Solomon Islands
01.07.2000
Preprint
Keine Angabe
Englisch
In-Flight Flow Visualization Using Infrared Thermography
NTIS | 1997
|In-Flight Flow Visualization Using Infrared Thermography
NTRS | 1997
|In-flight flow visualization using infrared imaging
AIAA | 1988
|