Approximate Formulas for the Computation of Turbulent Boundary-layer Momentum Thicknesses in Compressible Flows PDF Download
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Author: Neal Tetervin Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 38
Book Description
Summary: Approximate formulas for the computation of the momentum thicknesses of turbulent boundary layers on two-dimensional bodies, on bodies of revolution at zero angle of attack, and on the inner surfaces of round channels all in compressible flow are given in the form of integrals that can be conveniently computed. The formulas involve the assumptions that the momentum thickness may be computed by use of a boundary-layer velocity profile which is fixed and that skin-friction formulas for flat plates may be used in the computation of boundary-layer thicknesses in flow with pressure gradients. The effect of density changes on the ration of the displacement thickness to the momentum thickness of the boundary layer is taken into account. Use is made of the experimental finding that the skin-friction coefficient for turbulent flow is independent of Mach number. The computations indicated that the effect of density changes on the momentum thickness in flows with pressure gradients is small for subsonic flows.
Author: Neal Tetervin Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 38
Book Description
Summary: Approximate formulas for the computation of the momentum thicknesses of turbulent boundary layers on two-dimensional bodies, on bodies of revolution at zero angle of attack, and on the inner surfaces of round channels all in compressible flow are given in the form of integrals that can be conveniently computed. The formulas involve the assumptions that the momentum thickness may be computed by use of a boundary-layer velocity profile which is fixed and that skin-friction formulas for flat plates may be used in the computation of boundary-layer thicknesses in flow with pressure gradients. The effect of density changes on the ration of the displacement thickness to the momentum thickness of the boundary layer is taken into account. Use is made of the experimental finding that the skin-friction coefficient for turbulent flow is independent of Mach number. The computations indicated that the effect of density changes on the momentum thickness in flows with pressure gradients is small for subsonic flows.
Author: Hermann Schlichting (Deceased) Publisher: Springer ISBN: 366252919X Category : Technology & Engineering Languages : en Pages : 814
Book Description
This new edition of the near-legendary textbook by Schlichting and revised by Gersten presents a comprehensive overview of boundary-layer theory and its application to all areas of fluid mechanics, with particular emphasis on the flow past bodies (e.g. aircraft aerodynamics). The new edition features an updated reference list and over 100 additional changes throughout the book, reflecting the latest advances on the subject.
Author: Maurice Tucker Publisher: ISBN: Category : Air flow Languages : en Pages : 86
Book Description
As an application of the method, the contour correction of supersonic nozzles for the effects of boundary-layer development is discussed from the requirement of continuity of mass flow and from the requirement of expansion- and shock-wave elimination.
Author: Robert E. Dannenberg Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 678
Book Description
Tunnel-wall corrections for the induced upwash velocity for a swept wing completely spanning a rectangular wind tunnel are included in the appendix.
Author: Neal Tetervin
Author: Neal Tetervin
Author: Hermann Schlichting (Deceased)
Author: Maurice Tucker
Author: United States. National Advisory Committee for Aeronautics
Author: Robert E. Dannenberg
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: Jet Propulsion Laboratory (U.S.)
Author: