Accession Number:

ADP007817

Title:

Further Investigation of the Effect of Model Cooling on Periodic Transonic Flow,

Descriptive Note:

Corporate Author:

ROYAL AEROSPACE ESTABLISHMENT BEDFORD (UNITED KINGDOM)

Personal Author(s):

• Raghunathan, S.
• Zarifi Rad, F.
• Mabey, D. G.

Report Date:

1992-03-01

Pagination or Media Count:

13.0

Abstract:

Experimental investigation of the effect of model cooling on transonic periodic flows on biconvex aerofoils are reported. The test conditions included shock interactions with laminar and turbulent boundary layers at a Reynolds number 0.9 million and model wall temperature to tunnel total temperature ratios 0.5 to 1.0. The results show large effects of model cooling on transonic periodic flows. The effects observed are thought to correspond to what would happen at high Reynolds numbers at adiabatic wall conditions.

Descriptors:

• *COOLING
• *SHOCK
• *AEROTHERMODYNAMICS
• *AIRFOILS
• BOUNDARIES
• INTERACTIONS
• LAYERS
• MODELS
• RATIOS
• REYNOLDS NUMBER
• TEMPERATURE
• TEST AND EVALUATION
• TURBULENT BOUNDARY LAYER
• WALLS
• UNITED KINGDOM
• WIND TUNNEL TESTS

Subject Categories:

• Aerodynamics
• Thermodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE