Influence of a heated leading edge on boundary layer growth, stability, and transition

Conference · Thu Jan 01 00:00:00 EST 1987

OSTI ID:6867013

Landrum, D B; Macha, J M

This paper presents the results of a combined theoretical and experimental study of the influence of a heated leading edge on the growth, stability, and transition of a two-dimensional boundary layer. The findings are directly applicable to aircraft wings and nacelles that use surface heating for anti-icing protection. The potential effects of the non-adiabatic condition are particularly important for laminar-flow sections where even small perturbations can result in significantly degraded aerodynamic performance. The results of the study give new insight to the fundamental coupling between streamwise pressure gradient and surface heat flux in laminar and transitional boundary layers.

• Research Organization: Sandia National Labs., Albuquerque, NM (USA)
• DOE Contract Number: AC04-76DP00789
• OSTI ID: 6867013
• Report Number(s): SAND-86-2718C; CONF-870622-3; ON: DE87008516
• Resource Relation: Conference: 19. fluid dynamics, plasma dynamics, and laser conference, Honolulu, HI, USA, 8 Jun 1987; Other Information: Portions of this document are illegible in microfiche products
• Country of Publication: United States
• Language: English

Related Subjects

42 ENGINEERING
AIRFOILS
BOUNDARY LAYERS
HEATING
FLUID FLOW
ADIABATIC PROCESSES
BOUNDARY CONDITIONS
HEAT FLUX
PRESSURE GRADIENTS
REYNOLDS NUMBER
STABILITY
LAYERS
420400* - Engineering- Heat Transfer & Fluid Flow