· · · Aerospace Engineering reports

The present (and concluding) Part II of UTIA Review No. 12 on shock-tube theory and technique complements Part I by I.I. Glass which deals with the theory and performance of simple shock tubes . The coverage of Part II is as follows: Sec. 4. Production of strong shocks, including limits of the simple shock tube, electrical and combustion heating, multiple diaphragms, cross -section area change, performance comparison for various drives, explosive and magnetic drives, strong-shock attenuation; Sec. 5. Shock tube applications, including use as a sub-to supersonic wind tunnel, hypersonic shock and gun tunnels, aerophysics research, chemical research, instrument calibration; Sec. 6. Shock-tube materials, design, and construction, including diaphragm technique, pressure and vacuum technique, shocktube hazards; Sec. 7. Shock-tube flow measurement and instrumentation. The existing literature has been freely drawn on for the presentation of results in graphical form. A considerable amount of new material has also been added .

Canadian research on flow noise and some aspects of the aircraft noise problem is described . The work was done at the Defence Research Board, the University of Toronto Institute of Aerophysics and A. V. Roe (Canada) Ltd. Specific experimental and/ or theoretical investigations include: Aeolian Tones; Boundary Layer Noise (rigid wall and flexible wall); Effects of Boundary Layers and Noise on Aircraft Structures; Distribution of Noise Sources Along a Jet; Ground Run-up Mufflers; Transmission of Sound from, and Acoustic Energy Flow in, a Moving Medium; Sound Generated by Interaction of a Vortex with a Shock Wave .

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.

The reattachment of a laminar boundary-layer after separation has been investigated at a Mach number of 2.05. Backward facing step models were used that completely spanned the working section,. Surface flow was observed by a sublimation technique and detailed span-wise surveys were made in the reattachment region of the flow with total head probes. Strong, regular and repeatable span-wise perturbations were observed which could not be explained by irregularities either in the airflow upstream of the models or in the models themselves.

The evolution of a flight-worthy instrumentation system for measuring turbine rotor blade temperatures in an Orenda 14 turbojet engine is described. The system comprises sheathed chromel-alumel thermocouples installed in drilled turbine blades and used in conjunction with mercury sliprings mounted in the exhaust bullet of the engine. The instrumentation has been used to measure under sea level static conditions the turbine blade cooling produced by the pre-turbine injection of reheat fuel. An instrumented engine is currently being flown in a Sabre 6 aircraft to obtain similar data at altitude.