Summary
A difference method is developed for computing shear stress and temperature in the boundary layer as functions of the coordinate x along the wall and the velocity u parallel to the wall. Pressure gradient and temperature distribution along the wall are given continuous finite functions of the coordinate x. Density and viscosity coefficient depend on the local temperature in the boundary layer.
This research was supported by the United States Air Force, through the Office of Scientific Research of, the Air Research and Development Command.
This is a preview of subscription content, log in via an institution.
Buying options
Tax calculation will be finalised at checkout
Purchases are for personal use only
Learn about institutional subscriptionsPreview
Unable to display preview. Download preview PDF.
References
Hantzche, W., and Wendt, H.: Die laminare Grenzschicht der ebenen Platte mit und ohne Wärmeübergang unter Berücksichtigung der Kompressibilität. Jahrbuch 1942 der Deutschen Luftfahrtforschung, pp. I, 40—I, 50.
Crocco, L. : Lo strato limite laminare nei gas. Monografie scientifiche di aeronautica, Numero 3, Dicembre 1946, Roma.
Chapman, D. R., and Rubesin, M. W.: Temperature and Velocity Profiles in the Compressible Laminar Boundary Layer with Arbitrary Distribution of Surface Temperature. Journal of the Aeronautical Sciences, Sept. 1949, pp. 547–565.
Illingworth, C. R.: Steady Flow in the Laminar Boundary Layer of a Gas. Proceedings of the Royal Society, London, England, Ser. A., vol. 199, 1949, pp. 533–558.
Levy, S., and Seban, R. A.: Skin Friction and Heat Transfer for Laminar Boundary-Layer Flow with Variable Properties and Variable Free Stream Velocity. Journ. of Applied Mech., Sept. 1953, p. 415.
Eichelbrenner, E. A.: Sur une méthode approchée de calcul de la couche-limite laminaire compressible pour gradient de pression extérieure, loi de température à la paroi et nombre de Prandtl quelconques. La Recherche Aéronautique, No. 34 Jouillet-Août 1953.
Collatz, L.: Numerische Behandlung von Differentialgleichungen. Springer, Berlin/Göttingen/Heidelberg, 1951, p. 208.
Schlichting, H.: Grenzschicht-Theorie. Karlsruhe, G. Braun, 1951, p. 70.
Kaye, J.: Survey of Friction Coefficients, Recovery Factors and Heat Transfer Coefficients for Supersonic Flow. Journ. of the Aeronautical Sciences, February, 1954, pp. 117–129.
Johnson, A. F.: The Laminar Boundary Layer of a Compressible Fluid Passing Over A Curved Insulated Surface. Ph. D. thesis, Stanford University, Department of Mechanical Engineering, June, 1952. (To appear in Journal of the Aeronautical Sciences.)
Author information
Authors and Affiliations
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 1955 Springer Fachmedien Wiesbaden
About this chapter
Cite this chapter
Flügge-Lotz, I. (1955). A difference method for the computation of the laminar compressible boundary layer. In: Görtler, H., Tollmien, W. (eds) 50 Jahre Grenzschichtforschung. Vieweg+Teubner Verlag, Wiesbaden. https://doi.org/10.1007/978-3-663-20219-6_37
Download citation
DOI: https://doi.org/10.1007/978-3-663-20219-6_37
Publisher Name: Vieweg+Teubner Verlag, Wiesbaden
Print ISBN: 978-3-663-19879-6
Online ISBN: 978-3-663-20219-6
eBook Packages: Springer Book Archive