Accession Number : ADA298724

Title :   Pressure Distribution over a Thick, Tapered and Twisted Monoplane Wing Model - N.A.C.A. 81-J,

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC

Personal Author(s) : Wenzinger, Carl J.

PDF Url : ADA298724

Report Date : 1930

Pagination or Media Count : 19

Abstract : The structural design of airplane wings calls for a knowledge of the manner in which the air loads are distributed over the wing as well as the magnitude of the total loads. Standard load distributions, for example, such as are specified by the Department of Commerce, are only approximate, and while wings designed according to these loadings may be generally safe, they are doubtless often heavier than need be. It is, therefore, desirable to know more exactly the actual load distribution over a given type of wing if minimum weight is to be obtained. The increasing amount of interest in cantilever monoplane wing systems has furnished the basis for an extensive pressure distribution investigation made in the Atmospheric Wind Tunnel of the National Advisory Committee for Aeronautics. Several models of tapered wings suitable for internal bracing have previously been tested and the results published (Reference 1). The results of these tests indicated that further improvement in aerodynamic and geometric features were desirable, and in consequence, a new tapered wing was designed. (KAR) P. 5

Descriptors :   *AIRCRAFT MODELS, *PRESSURE DISTRIBUTION, *THICK WINGS, LOAD DISTRIBUTION, AERODYNAMIC LOADING, TAPER, STRUCTURAL ENGINEERING, TWIST(AERODYNAMICS).

Subject Categories : Aerodynamics
      Aircraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE