An Approximate Method for Calculation of the Laminar Boundary Layer with Suction for Bodies of Arbitrary Shape Page: 2 of 86
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TECH LIBRARY KAFB, NM
01 441611 1511
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS 0144681
TECHNICAL MEMORANDUM NO. 1216
AN APPROXIMATE METHOD FOR CALCULATION OF THE
LAMINAR BOUNDARY LAYER WITH SUCTION FOR
BODIES OF ARBITRARY SHAPE*
By H. Schlichting
Outline: I. Introduction: Statement of the Problem
III. The Boundary Layer Equation with Suction
IV. The General Approximation Method for Arbitrary Pressure
Distribution and Arbitrary Distribution of the Veloct
S(a) The expression for the velocity distribution
(b) The differential equation for the momentum thickness
(c) Stagnation point and separation point
(d) Execution of the calculation for the general case
V. Special Cases
A. Without suction
(a) The plane plate in longitudinal flow
(b) The two-dimensional stagnation point flow
B. With suction
(a) The growth of the boundary layer for the plane plate
in longitudinal flow with homogeneous suction
(b) The two-dimensional stagnation point flow with
(a) The circular cylinder with homogeneous suction for
various suction quantities
(b) Symmetrical Joukowaey profile for ca = 0 with
*"Ein Ngherungoverfahren zu Berechnung der laminaren Grenzschicht
mit Absaugung bel beliebiger Korperform.' Aerodynamisches Institut der
Technischen Hochschule Braunschweig, Bericht 43/13, June 12, 1943.
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Schlichting, H. An Approximate Method for Calculation of the Laminar Boundary Layer with Suction for Bodies of Arbitrary Shape, report, March 1949; (digital.library.unt.edu/ark:/67531/metadc64833/m1/2/: accessed October 21, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.