Accession Number : ADA130488

Title :   Unsteady Transonic Pressure Measurements on a Semi-Span Wind Tunnel Model of a Transport-Type Supercritical Wing (LANN) Lockheed-Georgia, Air Force, NASA, and NLR Model. Part 2. Pressure Distributions (PLOTTED) and Plots of the Vibration Modes.

Descriptive Note : Final technical rept. Apr 80-Apr 82,

Corporate Author : NATIONAL AEROSPACE LAB AMSTERDAM (NETHERLANDS)

Personal Author(s) : Hortsen,J J ; Boer,R G den ; Zwaan,R J

PDF Url : ADA130488

Report Date : Mar 1983

Pagination or Media Count : 187

Abstract : Unsteady transonic pressure measurements have been performed on a semi-span wind-tunnel model of a transport-type supercritical wing, oscillating in pitch. For each run, the vibration mode and detailed steady and unsteady pressure distributions have been measured. Sectional as well as wing aerodynamic coefficients have been obtained by integration of the pressure distributions. The tests covered a Mach number range between 0.62 and 0.95. The reduced frequency covered a range between zero and a maximum value varying from 0.3 at M = 0.62 to 0.2 at M = 0.95 (related to half mean aerodynamic chord). Part I of the report presents the general description, the aerodynamic coefficients (printed and plotted vs. incidence, reduced frequency and Mach number and the vibration modes. Part II presents the plotted pressure distributions and vibrations modes. (Author)

Descriptors :   *Supercritical wings, Transport aircraft, Transonic airfoils, Transonic flow, Unsteady flow, Vibration, Pitch(Motion), Pressure distribution

Subject Categories : Transport Aircraft
      Test Facilities, Equipment and Methods
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE