Theory of the Supersonic Turbulent Axisymmetric Near Wake behind Bluff-Base Bodies

Mehta, Gopal; Strahle, Warren C.

doi:10.2514/3.60754

Cited by 13 publications

(1 citation statement)

References 7 publications

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“…5 These analytical studies also have predicted that the base region is shortened or compressed by the combustion waves impinging on the base region. A compression of the base region has been demonstrated experimentally in wind tunnel tests with simulated external burning disturbances (no combustion) by Neale et al 6 and with external burning of fuel-rich solid propellant reaction products by Schadow and Chieze.…”

Section: Introductionmentioning

confidence: 96%

Experimental Study on Base Drag Reduction with Combined Lateral and Axial Injection

Schadow¹,

Chieze²

1978

AIAA Journal

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Experiments have been performed in a two-dimensional (2D), planar Mach 2 wind tunnel to study injection and combustion processes around a simulated projectile base. Lateral injection and external burning (EB) of hot fuel-rich reaction products from solid propellants, axial base injection (BI) of helium and nitrogen, and combined EB and BI have been studied. Test results show that the two base pressure rise mechanisms associated with EB and BI can be superimposed. Moreover, the base pressure rise associated with combined EB and BI was found to be higher than with EB or BI alone. NomenclatureA =area BB =base burning with axial fuel injection through projectile base into viscous near-wake region BI =base injection through projectile base without combustionburning in inviscid flow region achieved by lateral supersonic injection velocity EB/BR = external burning/base reaction achieved by lateral subsonic injection velocity h = base height / = injection parameter = m J /u 1 p 1 A b 7 sp = specific impulse = &p b A b /rhj M -Mach number m -mass flow p = static pressure RSP = rear stagnation point u = axial velocity component T = temperature X = axial coordinate measured from base a. = corner flow turning angle A/? = pressure rise due to injection and/or combustion K = ratio of specific heats p = density Subscripts 1 = condition before base corner expansion b = base £(ax) =in connection with A/?: base pressure rise due to axial injection in tests with EB and BI [A/7 Max) = (Ap b with BI and EB) -(Ap b with EB)] PM= primary motor j = injector ax = axial lat = lateral tot = total (in connection with 1:7 tot = 7 ax + 7 lat ) t = total (in connection with p: total pressure as determined with pressure probe) t(PM) = throat (primary motor)Presented as Paper 78-25 at

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Section: Introductionmentioning

confidence: 96%

Experimental Study on Base Drag Reduction with Combined Lateral and Axial Injection

Schadow¹,

Chieze²

1978

AIAA Journal

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Mach 3 Hydrogen ExternaVBase Burning

1981

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Experimental studies of base pressure manipulation for an axisymmetric model at Mach 3 with cold gas injection and burning are described. Air, nitrogen, helium, and hydrogen are used for cold gas injection tests. Burning tests use hydrogen subsonically injected either radially upstream of the base plane or axially through a porous base plate. These modes of injection yielded base burning that is efficient for base drag reduction. Base burning is also combined with external compression, simulating external burning to show that the separate effects are additive. NomenclatureA b = model base area 7 = injection mass flow parameter, Fig. 7 sp = specific impulse, Fig. 8 M = Mach number M = molecular weight M a = air molecular weight bieed = injection mass flow Pj = freestream static pressure p b-base pressure p b0 = undisturbed base pressure V l = freestream velocity P 1 = freestream density

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