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
2000
16 pages
Report
Keine Angabe
Englisch
Fluid Mechanics , Meetings , Flow visualization , Boundary layer transition , Fluid flow , Thermography , Infrared imagery , Infrared radiation , Shock waves , Supersonic flight , Supersonic flow , Laminar flow airfoils , Flow distribution , Heat transfer , Time dependence , Temperature distribution , Surface treatment , Cameras
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 | 1990
|