A Method of Calculating Turbulent-Boundary-Layer Growth at Hypersonic Mach Numbers

Sivells, James C; Payne, R. G.

doi:10.21236/ad0208774

Cited by 21 publications

(7 citation statements)

References 8 publications

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“…A boundary-layer computer program (Ref. 8) was used to determine the boundary layer in the nozzle. Boundary-layer thickness was computed to be approximately 0.…”

Section: Thrust Chamber Designmentioning

confidence: 99%

Design Characteristics and Performance of a Combustor for Use as an Ionized Gas Source in Magnetohydrodynamic Power Generation Studies

Darlington¹,

Ballard²

1969

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September 1969This document has been approved for public release e* f^-Vi.' its distribution is unlimited, .^/>Ot-r 71^ This document io nubjeefr-te^pixräi^xprnina)ltl.lOlS , Jlidnationals may rw made-only-with-pcieM-approvaLof -Air Force -Aere-Pfeputeien-JsafeeRttory-(AP.IEa2),»JWtighiPa«eMen=iAF'B»se^Ohiö-45433. ROCKET TEST FACILITY ARNOLD ENGINEERING DEVELOPMENT CENTER AIR FORCE SYSTEMS COMMAND ARNOLD AIR FORCE STATION, TENNESSEEWOHER OF U n S" m E02CB mim when U. S. Government drawings specifications, or other data are used for any purpose other than a definitely related Government procurement operation, the Government thereby incurs no responsibility nor any obligation whatsoever, and the fact that the Government may have formulated, furnished, or in any way supplied the said drawings, specifications, or other data, is not to be regarded by implication or otherwise, or in any manner licensing the holder or any other person or corporation, or conveying any rights or permission to manufacture, use, or sell any patented invention that may in any way be related thereto.Qualified users may obtain copies of this report from the Defense Documentation Center.References to named commercial products in this report are not to be considered in any sense as an endorsement of the product by the United States Air Force or the Government. AEDCTR-69- ABSTRACTDesign characteristics and performance of a combustor for use as a high energy, ionized gas source in magnetohydrodynamic power generator studies are described. The liquid oxygen (LC»2)/JP-4 combustor was operated over a chamber pressure range from 240 to 300 psia and at a characteristic exhaust velocity efficiency of 91 ± 1 percent for oxidizer/fuel ratios ranging from 2. 0 to 3. 1. Combustor power output was approximately 17.5 to 20.5 megawatts (MW) over its range of operation. Provisions were incorporated into the design for injection of a saturated solution of water and cesium carbonate seeding agent into the thrust chamber to provide a high ion concentration in the exhaust gases.This document is subject to special export controls and each transmittal to foreign governments or foreign nationals may be made only with prior approval of Air Force Aero-Propulsion Laboratory (APIE-2), WrightPatterson AF Base, Ohio 45433.Ill AEDC-TR.69.167 CONTENTS

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“…A boundary-layer computer program (Ref. 8) was used to determine the boundary layer in the nozzle. Boundary-layer thickness was computed to be approximately 0.…”

Section: Thrust Chamber Designmentioning

confidence: 99%

Design Characteristics and Performance of a Combustor for Use as an Ionized Gas Source in Magnetohydrodynamic Power Generation Studies

Darlington¹,

Ballard²

1969

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“…This was accomplished by applying a modified Stewartson transformation including the heat transfer term (15) and observing, from physical considerations, that no heat transfer occurs across the discontinuity. The effect of cooling is a strong favorable tendency to suppress distortion of the boundary layer in adverse pressure gradients.…”

Section: Discussionmentioning

confidence: 99%

“…The restoring characteristics of the incompressible turbulent boundary layer in zero pressure gradient in terms of the shape parameter are shown in Fig. 4 from the correlation of Sivells (15 Fig. 5 Qualitative behavior of a turbulent boundary layer encountering an adverse pressure gradient tortion) the effective Reynolds number is low and the restoring rate is high (Fig.…”

Section: Discontinuity/analogy Hypothesismentioning

confidence: 99%

“…4 is entered to obtain (Hi) 3. The corresponding compressible shape parameter can be found from the Stewartson transformation: H = Hdl + |(T ~ 1) M*] + Uy ~ 1) M* [14] In determining the thickness parameters for the restoring component, the rate of growth of momentum thickness is determined from the flat plate correlation of Coles (16): [15] Thus, between stations 2 and 3 of Fig. 3 the momentum thickness at station 2 is known from the discontinuity calculation and that at station 3 is found as Correlation of integrated turbulent stress and shape parameter has been found to approximate the empirical skin friction correlations of Sivells (15).…”

Section: Discontinuity/analogy Hypothesismentioning

confidence: 99%

“…6, wherein the calculated integrated turbulent stress for a flat plate boundary layer is compared with measured values for adverse pressure gradients. The values for the flat plate flow were calculated using the moment of momentum equation (2) and the temporal mean data correlation of Sivells (15). It seems reasonable to believe that the rate at which the turbulent boundary layer relaxes from a given distorted velocity profile (shape parameter) is principally a function of the mass flow mixing and momentum transport processes as manifested by the integrated turbulent stresses.…”

Section: Basis For Analogymentioning

confidence: 99%

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