Ad
related to: boundary layer theory by schlichting design
Search results
Results From The WOW.Com Content Network
Hermann Schlichting, Erich Truckenbrodt: Aerodynamik des Flugzeugs Springer, Berlin 1967; Hermann Schlichting, Klaus Gersten, Boundary Layer Theory, 8th ed. Springer-Verlag 2004, ISBN 81-8128-121-7; Hermann Schlichting, Klaus Gersten, Egon Krause, Herbert, jun. Oertel: Grenzschicht-Theorie Springer, Berlin 2006, ISBN 3-540-23004-1
Turbulent boundary layers are more resistant to separation. The energy in a boundary layer may need to be increased to keep it attached to its surface. Fresh air can be introduced through slots or mixed in from above. The low momentum layer at the surface can be sucked away through a perforated surface or bled away when it is in a high pressure ...
Schlichting jet is a steady, laminar, round jet, emerging into a stationary fluid of the same kind with very high Reynolds number. The problem was formulated and solved by Hermann Schlichting in 1933, [ 1 ] who also formulated the corresponding planar Bickley jet problem in the same paper. [ 2 ]
The boundary layer thickness, , is the distance normal to the wall to a point where the flow velocity has essentially reached the 'asymptotic' velocity, .Prior to the development of the Moment Method, the lack of an obvious method of defining the boundary layer thickness led much of the flow community in the later half of the 1900s to adopt the location , denoted as and given by
Ludwig Prandtl (4 February 1875 – 15 August 1953) [1] was a German fluid dynamicist, physicist and aerospace scientist. He was a pioneer in the development of rigorous systematic mathematical analyses which he used for underlying the science of aerodynamics, which have come to form the basis of the applied science of aeronautical engineering. [2]
The transformation transforms the equations of axisymmetric boundary layer with external velocity in terms of original variables,,, into the equations of plane boundary layer with external velocity ¯ in terms of the new variables ¯, ¯, ¯, ¯. The transformation is given by the formulas
At this moderate free-stream turbulence level, he observed a velocity perturbation signal with a frequency under 12 Hz, much smaller than the usual Tollmien-Schlichting wave frequency. He also observed fluctuations in boundary layer thickness, which does not occur in low-turbulence free-stream flow. [2]
The VLM is the extension of Prandtl's lifting-line theory, [2] where the wing of an aircraft is modeled as an infinite number of Horseshoe vortices. The name was coined by V.M. Falkner in his Aeronautical Research Council paper of 1946. [3] The method has since then been developed and refined further by W.P. Jones, H. Schlichting, G.N. Ward and ...