Effect of vortices on delta wing lee-side heating at Mach 6

Lee-side vortices on delta wings at hypersonic speeds.

“…10 ' 13 The data of Ref. 1 show that while the lee-surface pressure field was essentially conical in conformity with the nature of the inviscid flow, the vortex-induced heating patterns were not.…”

“…=(x-x*)RR L = model length Reynolds number St^ = Stanton number based on freestream conditions x = coordinate along center line from apex (or nose), positive downstream x* = distance along x to peak heating (or other flow characteristic) x' = coordinate along center line, originating at x = x* y = spanwise coordinate from center line z = coordinate normal to planar upper wing surface, positive upward a = incidence angle of upper planar surface, positive leeward a 0 = incidence relative to model reference axis Introduction E the extensive research on hypersonic aerodynamics of delta ings, the leeward flowfield has so far received limited attention. Although lee surface pressures contribute the smallest part to the aerodynamic loads at high Mach numbers, vortex phenomena have been found responsible for intense local heating over the lee meridian of delta wings (peaking to more than three times the two-dimensional laminar estimates), 1 and also on hypersonic configurations such as the space shuttle. 2 Since such heating could constitute a potential design problem for hypersonic vehicles in sustained cruising flight, the need for improved prediction of the lee-side heating is indicated.…”

Hypersonic Lee Surface Flow Phenomena over a Space Shuttle

“…= angle of attack 6 C = cone half-angle Subscripts P -conditions at peak heating s -separation / = total stagnation conditions t 2 = local stagnation conditions behind a normal shock w = conditions at the wall w 0 -laminar stagnation conditions oo = freestream conditions Ooo = freestream stagnation conditions…”