Schlichting, Hermann 1907
Overview
Works:  142 works in 416 publications in 7 languages and 4,247 library holdings 

Genres:  Conference papers and proceedings 
Roles:  Author, Honoree, Creator, Editor 
Classifications:  TL574.B6, 532.052 
Publication Timeline
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Most widely held works about
Hermann Schlichting
 Hermann Schlichting  100 Years Scientific Colloquium Celebrating the Anniversary of His Birthday, Brunswick, Allemagne 2007( )
 Hermann Schlichting100 years : scientific colloquium celebrating the anniversary of his birthday, Braunschweig, Germany 2007 by Rolf Radespiel( )
Most widely held works by
Hermann Schlichting
Boundarylayer theory by
Hermann Schlichting(
Book
)
158 editions published between 1813 and 2006 in 7 languages and held by 2,621 WorldCat member libraries worldwide
Die berarbeitung fr die 10. deutschsprachige Auflage von Hermann Schlichtings Standardwerk wurde wiederum von Klaus Gersten geleitet, der schon die umfassende Neuformulierung der 9. Auflage vorgenommen hatte. Es wurden durchgngig Aktualisierungen vorgenommen, aber auch das Kapitel 15 von Herbert Oertel jr. neu bearbeitet. Das Buch gibt einen umfassenden berblick ber den Einsatz der GrenzschichtTheorie in allen Bereichen der Strmungsmechanik. Dabei liegt der Schwerpunkt bei den Umstrmungen von Krpern (z.B. Flugzeugaerodynamik). Das Buch wird wieder den Studenten der Strmungsmechanik wie auch I
158 editions published between 1813 and 2006 in 7 languages and held by 2,621 WorldCat member libraries worldwide
Die berarbeitung fr die 10. deutschsprachige Auflage von Hermann Schlichtings Standardwerk wurde wiederum von Klaus Gersten geleitet, der schon die umfassende Neuformulierung der 9. Auflage vorgenommen hatte. Es wurden durchgngig Aktualisierungen vorgenommen, aber auch das Kapitel 15 von Herbert Oertel jr. neu bearbeitet. Das Buch gibt einen umfassenden berblick ber den Einsatz der GrenzschichtTheorie in allen Bereichen der Strmungsmechanik. Dabei liegt der Schwerpunkt bei den Umstrmungen von Krpern (z.B. Flugzeugaerodynamik). Das Buch wird wieder den Studenten der Strmungsmechanik wie auch I
Aerodynamics of the airplane by
Hermann Schlichting(
Book
)
33 editions published between 1959 and 2001 in 3 languages and held by 413 WorldCat member libraries worldwide
33 editions published between 1959 and 2001 in 3 languages and held by 413 WorldCat member libraries worldwide
Ludwig Prandtl collected treatises on applied mechanics, hydro and aerodynamics by
W Tollmien(
Book
)
1 edition published in 1988 in English and held by 73 WorldCat member libraries worldwide
1 edition published in 1988 in English and held by 73 WorldCat member libraries worldwide
Ludwig Prandtl collected treatises on applied mechanics, hydro and aerodynamics by
W Tollmien(
Book
)
1 edition published in 1988 in English and held by 73 WorldCat member libraries worldwide
1 edition published in 1988 in English and held by 73 WorldCat member libraries worldwide
Aerodynamik des Tragflügels (Teil 2), des Rumpfes, der FlügelRumpfAnordnung und der Leitwerke by
Hermann Schlichting(
Book
)
5 editions published between 1960 and 2001 in German and held by 55 WorldCat member libraries worldwide
5 editions published between 1960 and 2001 in German and held by 55 WorldCat member libraries worldwide
Grundlagen aus der Strömungsmechanik = Aerodynamik des Tragflügels (Teil 1) by
Hermann Schlichting(
Book
)
4 editions published between 1959 and 1967 in German and held by 50 WorldCat member libraries worldwide
4 editions published between 1959 and 1967 in German and held by 50 WorldCat member libraries worldwide
Bian jie ceng yuan li by Shi li xi ting(
Book
)
1 edition published in 2001 in Chinese and held by 36 WorldCat member libraries worldwide
1 edition published in 2001 in Chinese and held by 36 WorldCat member libraries worldwide
Aerodynamik des Flugzeuges by
Hermann Schlichting(
Book
)
4 editions published between 1960 and 1969 in German and held by 33 WorldCat member libraries worldwide
4 editions published between 1960 and 1969 in German and held by 33 WorldCat member libraries worldwide
Grundlagen aus der Strömungstechnik, Aerodynamik des Tragflügels (Teil 1) by
Hermann Schlichting(
Book
)
1 edition published in 2001 in German and held by 30 WorldCat member libraries worldwide
1 edition published in 2001 in German and held by 30 WorldCat member libraries worldwide
Hermann Schlichting100 years : scientific colloquium celebrating the anniversary of his birthday, Braunschweig, Germany
2007 by
Rolf Radespiel(
Book
)
2 editions published in 2009 in English and held by 21 WorldCat member libraries worldwide
This volume contains the contributions to the scientific anniversary colloquium in honor of the 100th birthday of Hermann Schlichting, Braunschweig, September2007. His outstanding achievements in boundary layer theory and aircraft aerodynamics are reviewed by invited scholars. Contributions of current leading research by the institutes formerly lead by Hermann Schlichting, the Institute of Fluid Mechanics of the Technische Universität Braunschweig and the Institute of Aerodynamics and Flow Technology of German Aerospace Center, in the fields of numerical flow simulation, experimental techniques, wing aerodynamics and turbomachinery highlight the lasting impact of his work until today
2 editions published in 2009 in English and held by 21 WorldCat member libraries worldwide
This volume contains the contributions to the scientific anniversary colloquium in honor of the 100th birthday of Hermann Schlichting, Braunschweig, September2007. His outstanding achievements in boundary layer theory and aircraft aerodynamics are reviewed by invited scholars. Contributions of current leading research by the institutes formerly lead by Hermann Schlichting, the Institute of Fluid Mechanics of the Technische Universität Braunschweig and the Institute of Aerodynamics and Flow Technology of German Aerospace Center, in the fields of numerical flow simulation, experimental techniques, wing aerodynamics and turbomachinery highlight the lasting impact of his work until today
Berechnung der reibungslosen inkompressiblen Strömung für ein vorgegebenes ebenes Schaufelgitter by
Hermann Schlichting(
Book
)
3 editions published in 1955 in German and held by 17 WorldCat member libraries worldwide
3 editions published in 1955 in German and held by 17 WorldCat member libraries worldwide
Aerodynamik des Flugzeuges by
Hermann Schlichting(
Book
)
5 editions published between 1959 and 1967 in German and held by 17 WorldCat member libraries worldwide
5 editions published between 1959 and 1967 in German and held by 17 WorldCat member libraries worldwide
Threedimensional Boundary Layer Flow by
Hermann Schlichting(
Book
)
6 editions published between 1961 and 1962 in German and English and held by 16 WorldCat member libraries worldwide
6 editions published between 1961 and 1962 in German and English and held by 16 WorldCat member libraries worldwide
Discussion on aerodynamic aspects of V/STOL aeroplanes by
Hermann Schlichting(
Book
)
5 editions published in 1961 in German and English and held by 11 WorldCat member libraries worldwide
5 editions published in 1961 in German and English and held by 11 WorldCat member libraries worldwide
Report on the special field "interference" to the wind tunnel committee in February 1945 by
Hermann Schlichting(
Book
)
3 editions published in 1953 in English and held by 6 WorldCat member libraries worldwide
Contains an outline of investigations dealing with interference effects on the static stability of various airplane configurations that were conducted, were being conducted, and were started at the time of this report. Results of several investigations are presented and discussed briefly. A supplement is attached showing the configurations tested and outlining the various test programs. Suggestions for future investigations are also included
3 editions published in 1953 in English and held by 6 WorldCat member libraries worldwide
Contains an outline of investigations dealing with interference effects on the static stability of various airplane configurations that were conducted, were being conducted, and were started at the time of this report. Results of several investigations are presented and discussed briefly. A supplement is attached showing the configurations tested and outlining the various test programs. Suggestions for future investigations are also included
Laminar flow about a rotating body of revolution in an axial airstream by
Hermann Schlichting(
Book
)
3 editions published in 1956 in English and held by 6 WorldCat member libraries worldwide
We have set ourselves the problem of calculating the laminar flow on a body of revolution in an axial flow which simultaneously rotates about its axis. The problem mentioned above, the flow about a rotating disk in a flow, which we solved some time ago, represents the first step in the calculation of the flow on the rotating body of revolution in a flow insofar as, in the case of a round nose, a small region about the front stagnation point of the body of revolution may be replaced by its tangential plane. In our problem regarding the rotating body of revolution in a flow, for laminar flow, one of the limiting cases is known: that of the body which is in an axial approach flow but does not rotate. The other limiting case, namely the flow in the neighborhood of a body which rotates but is not subjected to a flow is known only for the rotating circular cylinder, aside from the rotating disk. In the case of the cylinder one deals with a distribution of the circumferential velocity according to the law v = omega R(exp 2)/r where R signifies the cylinder radius, r the distance from the center, and omega the angular velocity of the rotation. The velocity distribution as it is produced here by the friction effect is therefore the same as in the neighborhood of a potential vortex. When we treat, in what follows, the general case of the rotating body of revolution in a flow according to the calculation methods of Prandtl's boundarylayer theory, we must keep in mind that this solution cannot contain the limiting case of the body of revolution which only rotates but is not subjected to a flow. However, this is no essential limitation since this case is not of particular importance for practical purposes
3 editions published in 1956 in English and held by 6 WorldCat member libraries worldwide
We have set ourselves the problem of calculating the laminar flow on a body of revolution in an axial flow which simultaneously rotates about its axis. The problem mentioned above, the flow about a rotating disk in a flow, which we solved some time ago, represents the first step in the calculation of the flow on the rotating body of revolution in a flow insofar as, in the case of a round nose, a small region about the front stagnation point of the body of revolution may be replaced by its tangential plane. In our problem regarding the rotating body of revolution in a flow, for laminar flow, one of the limiting cases is known: that of the body which is in an axial approach flow but does not rotate. The other limiting case, namely the flow in the neighborhood of a body which rotates but is not subjected to a flow is known only for the rotating circular cylinder, aside from the rotating disk. In the case of the cylinder one deals with a distribution of the circumferential velocity according to the law v = omega R(exp 2)/r where R signifies the cylinder radius, r the distance from the center, and omega the angular velocity of the rotation. The velocity distribution as it is produced here by the friction effect is therefore the same as in the neighborhood of a potential vortex. When we treat, in what follows, the general case of the rotating body of revolution in a flow according to the calculation methods of Prandtl's boundarylayer theory, we must keep in mind that this solution cannot contain the limiting case of the body of revolution which only rotates but is not subjected to a flow. However, this is no essential limitation since this case is not of particular importance for practical purposes
An approximate method for calculation of the laminar boundary layer with suction for bodies of arbitrary shape by
Hermann Schlichting(
Book
)
3 editions published in 1949 in English and held by 5 WorldCat member libraries worldwide
Various ways were tried recently to decrease the friction drag of a body in a flow; they all employ influencing the boundary layer. One of them consists in keeping the boundary layer Laminar by suction; promising tests have been carried out. Since for large Reynolds numbers the friction drag of the laminar boundary layer is much lower than that of the turbulent boundary layer, a considerable saving in drag results from keeping the boundary layer laminar, even with the blower power required for suction taken into account. The boundary layer is kept laminar by suction in two ways: first, by reduction of the thickness of the boundary layer and second, by the fact that the suction changes the form of the velocity distribution so that it becomes more stable, in a manner similar to the change by a pressure drop. There by the critical Reynolds number of the boundary layer (USigma/V) (sub crit) becomes considerably higher than for the case without suction. This latter circumstance takes full effect only if continuous suction is applied which one might visualize realized through a porous wall. Thus the suction quantities required for keeping the boundary layer laminar become so small that the suction must be regarded as a very promising auxiliary means for drag reduction
3 editions published in 1949 in English and held by 5 WorldCat member libraries worldwide
Various ways were tried recently to decrease the friction drag of a body in a flow; they all employ influencing the boundary layer. One of them consists in keeping the boundary layer Laminar by suction; promising tests have been carried out. Since for large Reynolds numbers the friction drag of the laminar boundary layer is much lower than that of the turbulent boundary layer, a considerable saving in drag results from keeping the boundary layer laminar, even with the blower power required for suction taken into account. The boundary layer is kept laminar by suction in two ways: first, by reduction of the thickness of the boundary layer and second, by the fact that the suction changes the form of the velocity distribution so that it becomes more stable, in a manner similar to the change by a pressure drop. There by the critical Reynolds number of the boundary layer (USigma/V) (sub crit) becomes considerably higher than for the case without suction. This latter circumstance takes full effect only if continuous suction is applied which one might visualize realized through a porous wall. Thus the suction quantities required for keeping the boundary layer laminar become so small that the suction must be regarded as a very promising auxiliary means for drag reduction
Amplitude distribution and energy balance of small disturbances in plate flow by
Hermann Schlichting(
Book
)
3 editions published in 1950 in English and held by 5 WorldCat member libraries worldwide
The distribution of the correlation coefficient and of the amplitude of the disturbance velocities is calculated as a function of the distance from the wall for two neutral disturbances, one at the lower and one at the upper branch of the neutral stability curve. The energy balance of the disturbance motion is also investigated and it is found that as required for neutral stability the energy of the disturbance motion that is dissipated by viscosity is equal to the energy transferred to the disturbance motion from the main flow during one cycle
3 editions published in 1950 in English and held by 5 WorldCat member libraries worldwide
The distribution of the correlation coefficient and of the amplitude of the disturbance velocities is calculated as a function of the distance from the wall for two neutral disturbances, one at the lower and one at the upper branch of the neutral stability curve. The energy balance of the disturbance motion is also investigated and it is found that as required for neutral stability the energy of the disturbance motion that is dissipated by viscosity is equal to the energy transferred to the disturbance motion from the main flow during one cycle
Airfoil theory at supersonic speed by
Hermann Schlichting(
Book
)
3 editions published in 1939 in English and held by 5 WorldCat member libraries worldwide
A theory is developed for the airfoil of finite span at supersonic speed analogous to the Prandtl airfoil theory of 19181919 for incompressible flow. In addition to the profile and induced drags, account must be taken at supersonic flow of still another drag, namely, the wave drag, which is independent of the wing aspect ratio. Both wave and induced drags are proportional to the square of the lift and depend on the Mach number, that is, the ratio of flight to sound speed. In general, in the case of supersonic flow, the draglift ratio is considerably less favorable than is the case for incompressible flow. Among others the following examples are considered: 1) lifting line with constant lift distribution (horseshoe vortex); 2) computation of wave and induced drag and the twist of a trapezoidal wing of constant lift density; 3) computation of the lift distribution and drag of an untwisted rectangular wing
3 editions published in 1939 in English and held by 5 WorldCat member libraries worldwide
A theory is developed for the airfoil of finite span at supersonic speed analogous to the Prandtl airfoil theory of 19181919 for incompressible flow. In addition to the profile and induced drags, account must be taken at supersonic flow of still another drag, namely, the wave drag, which is independent of the wing aspect ratio. Both wave and induced drags are proportional to the square of the lift and depend on the Mach number, that is, the ratio of flight to sound speed. In general, in the case of supersonic flow, the draglift ratio is considerably less favorable than is the case for incompressible flow. Among others the following examples are considered: 1) lifting line with constant lift distribution (horseshoe vortex); 2) computation of wave and induced drag and the twist of a trapezoidal wing of constant lift density; 3) computation of the lift distribution and drag of an untwisted rectangular wing
Lecture series "boundary layer theory." by
Hermann Schlichting(
Book
)
4 editions published in 1949 in English and held by 3 WorldCat member libraries worldwide
The subject of turbulent flow is treated in detail. The available data on flow through pipes and over flat plates are presented. Turbulent wakes and jets are treated by means of the Prandtl mixing length theory. A section is devoted to the Gruschwitz method for calculating turbulent boundary layers in accelerated and retarded flows. The methods of Betz and Jones for determining profile drag from wake surveys are given. A chapter on the theory of the stability of the laminar boundary layer, developed from the point of view of small oscillations, is also included
4 editions published in 1949 in English and held by 3 WorldCat member libraries worldwide
The subject of turbulent flow is treated in detail. The available data on flow through pipes and over flat plates are presented. Turbulent wakes and jets are treated by means of the Prandtl mixing length theory. A section is devoted to the Gruschwitz method for calculating turbulent boundary layers in accelerated and retarded flows. The methods of Betz and Jones for determining profile drag from wake surveys are given. A chapter on the theory of the stability of the laminar boundary layer, developed from the point of view of small oscillations, is also included
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Related Identities
 Gersten, K. Author
 Truckenbrodt, Erich 1917
 Radespiel, Rolf
 Rossow, CordChristian
 Brinkmann, Benjamin
 Krause, Egon Other Contributor
 Tollmien, Walter Author Editor Creator
 Goertler, Henry
 United States National Aeronautics and Space Administration
 United States National Advisory Commitee for Aeronautics
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Associated Subjects
Aerodynamic load Aerodynamics Aerodynamics, Supersonic Aerofoils Aeronautics Aerospace engineering Air flow AirplanesNacelles AirplanesTail surfaces AirplanesWings Astronautics Axial flow Body of revolution Boundary layer Boundary layer control Cascades (Fluid dynamics) Drag (Aerodynamics) Engineering Engineering mathematics Fluid dynamics Fluid mechanics Fluids Friction Gas flow Hydraulic engineering Hydrodynamics Interference (Aerodynamics) Laminar boundary layer Laminar flow Lift (Aerodynamics) Mathematical physics Mathematics Mechanics, Applied Physics Plates (Engineering) Stability Stability of airplanes Turbulence Turbulent boundary layer
Alternative Names
Hermann Schlichting German engineer
Hermann Schlichting tysk ingenir
Hermann Schlichting tysk ingenjr
Schlichting, H.
Schlichting, H. 1907
Schlichting, H. 19071982
Schlichting, H. (Hermann), 1907
Schlichting, Hermann
Schlichting Herrmann
Schlichting, Herrmann 1907
Schlichting, Herrmann 19071982
Šlihting, G.
Шлихтинг, Герман
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