Browsing by Author "Nonweiler, T."

Browsing by Author "Nonweiler, T."

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  • The air resistance of racing cyclists 
    Nonweiler, T. (College of Aeronautics, Cranfield, 1956-10)
    Tests in the closed-section wind-tunnel on three different cyclists mounted on a racing bicycle are described, and figures quoted for the recorded air resistance. Some comments are also included on the implications of the ...
  • Incompressible flow past bodies of revolution 
    Nonweiler, T. (College of Aeronautics, 1955-07)
    In this paper we shall attempt to review the existing information, both theoretical and experimental, which relates to same of the more important aerodynamic problems arising in the study of the flaw over bodies of ...
  • The laminar boundary layer in slip flow 
    Nonweiler, T. (College of Aeronuatics, Cranfield, 1952-11)
    This report discusses the effects of the existence of a small, but finite, molecular mean-free-path on the steady air flow in the laminar boundary later. The boundary conditions at the exposed surface are modified by the ...
  • The man-propelled aircraft: a preliminary assessment 
    Nonweiler, T. (College of Aeronautics, 1956-03)
    1. Introduction It is the intention of this note to set down a few tentative, but (it is hoped) realistic, assessments of the problems involved in the design of an aircraft which by the crew's own muscular efforts shall ...
  • A method for numerical evaluation of the integral... 
    Nonweiler, T. (College of Aeronautics, Cranfield, 1956-03)
    This report presents formulae and data for the numerical evaluation of the double integral named in the title...
  • The numerical solution of certain differential equations occurring in Crocco's theory of the laminar boundary layer 
    Kirkby, S.; Nonweiler, T. (College of Aeronautics, Cranfield, 1953-05)
    A numerical method is described for the solution of certain differential equations which result from the application of Crocco’s transformation to the laminar boundary layer equations appropriate to high supersonic Mach ...
  • A resume of maximum lift data for symmetrical wings, with various high-lift aids 
    Nonweiler, T. (College of Aeronautics, 1954-03)
    We shall attempt here to summarise the existing data on the values of the low-speed CLmax of wings, in the absence of a fuselage, and without including information on stalling incidence or pitching moment. The summary ...
  • Skin temperatures and heat transfer over wedge wings at extreme speeds of flight 
    Nonweiler, T. (College of Aeronautics, Cranfield, 1956-08)
    By paying spacial attention to the wing design and altitude of flight, it is possible to ensure that the highest temperature reached at the leading edge of the wing of an aircraft, in level flight at speeds of the order ...
  • Surface conduction of the heat transferred from a boundary layer 
    Nonweiler, T. (College of Aeronautics, Cranfield, 1952-05)
    This note considers the effect of thermal conductivity upon the temperature distribution in the skin of a body (moving through air) due to the heat transferred from the boundary layer. It is found that the effects are of ...
  • Theoretical stability derivatives of a highly swept delta wing and slender body combination 
    Nonweiler, T. (College of Aeronautics, Cranfield, 1951-11)
    The stability derivatives of a delta wing of small aspect ratio, mounted on a cylindrical body with a slender pointed head, are derived by considering the flow in planes perpendicular to the body axis to be uninfluenced ...
  • The theoretical wave drag at zero lift of fully-tapered swept wings of arbitrary section 
    Nonweiler, T. (College of Aeronautics, Cranfield, 1953-10)
    An expression is deduced for the wave drag of a fully tapered swept wing of arbitrary section in the convenient form of a double integral involving the variation of wing-surface slope. It is concluded, in the general case, ...
  • The two-dimensional laminar boundary layer at hypersonic speeds 
    Nonweiler, T. (College of Aeronautics, Cranfield, 1953-01)
    A numerical solution is found for the equations governing the motion of a two-dimensional laminar boundary layer, in the absence of a pressure gradient, which would be valid if the flight Mach number is very high (i.e. ...
  • The wave drag of highly-swept wings: a comparison of linear theory and slender body theory 
    Nonweiler, T. (College of Aeronautics, 1954-10)
    This note comments on the comparison between the answer obtained by linear theory for the wave drag of slender-wings (as interpreted by the limit and that value for the drag obtained by Slender-Body Theory. It is shown ...