Free Stream Velocity Measurements in a Supersonic Impulse Flow Field.
Abstract
Measurements of free stream flow velocity were made in a detonation tube facility using a laser anemometer. Velocities were obtained close to the exit plane of a two dimensional nozzle under flow conditions that duplicated a hydrogen-air scramjet engine exhaust. The nozzle exit velocity was predicted by a method of characteristics solution that included real gas effects. Our velocity measurements agreed within a few percent with the predicted value (2200 meters/sec). In addition, the authors were able to determine the velocity of cold gases leaving the nozzle after diaphragm rupture but before ignition of the detonation wave. Measured cold gas velocities agreed closely with ideal gas predictions based on direct expansion of the unburned reactant gases. From this investigation it was concluded that, with minor modifications of the laser anemometer system described, free stream velocities up to about 3000 m/sec can be measured as a function of time in downstream regions of the flow field during routine detonation tube operation. This system could be modified to obtain velocity measurements above 5000 m/sec.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1976
- Accession Number
- ADA027381
Entities
People
- Richard C. Jenkins
- Wayne L. Konopka
Organizations
- Grumman