Scientific and Technical Aerospace Reports

Scientific and Technical Aerospace Reports PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702

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Scientific and Technical Aerospace Reports

Scientific and Technical Aerospace Reports PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702

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Research in Progress

Research in Progress PDF Author:
Publisher:
ISBN:
Category : Military research
Languages : en
Pages : 746

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Free Turbulent Mixing

Free Turbulent Mixing PDF Author: Philip Thomas Harsha
Publisher:
ISBN:
Category : Turbulence
Languages : en
Pages : 340

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Analytical Nodel of Supersonic, Turbulent, Near-wake Flows

Analytical Nodel of Supersonic, Turbulent, Near-wake Flows PDF Author: C. E. Peters
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ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 80

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An analytical model for planar and axisymmetric, supersonic, turbulent, near-wake flows is presented. The viscous region behind the blunt base is described by the integral form of the boundary-layer equations, and the inviscid outer-flow region, including the remnant of the initial turbulent boundary layer, is computed with the rotational method of characteristics. The solution of the two regions is fully coupled. The saddle-point singularity, similar to the Crocco-Lees critical point, occurs downstream of the rear stagnation point. The base pressure is obtained by iteration of the initial conditions until the flow-field solution will pass through the singularity. Base bleed of a gas different from the outer-stream gas is included in the formulation, and provision is made to treat equilibrium chemical reactions in the viscous wake. However, an unresolved problem has been encountered in the solution of the species conservation equations. Therefore, results for only single gas flows are presented. The analytical model is shown to adequately predict the effect of free-stream Mach number and initial boundary layer on the planar base pressure. In addition, the planar flow-field structure is well predicted. Axisymmetric base pressure and flow-field structure are reasonably well predicted for free-stream Mach numbers greater than 2.0, but the turbulent transport model used yields only fair results for Mach numbers less than 1.7. The effect of base bleed on the axisymmetric base pressure is well predicted. (Author).

NASA Scientific and Technical Reports and Publications for 1969 - A Selected Listing

NASA Scientific and Technical Reports and Publications for 1969 - A Selected Listing PDF Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 956

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Applied Mechanics Reviews

Applied Mechanics Reviews PDF Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 300

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U.S. Government Research & Development Reports

U.S. Government Research & Development Reports PDF Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 784

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Technical Abstract Bulletin

Technical Abstract Bulletin PDF Author:
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ISBN:
Category : Science
Languages : en
Pages : 912

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Dissertation Abstracts International

Dissertation Abstracts International PDF Author:
Publisher:
ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 1776

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U.S. Government Research and Development Reports Index

U.S. Government Research and Development Reports Index PDF Author:
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ISBN:
Category : Nuclear science abstracts
Languages : en
Pages : 1306

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