Accession Number : ADA214740

Title :   Unsteady Airloads on a Sinusoidally Oscillating Supercritical Airfoil.

Descriptive Note : Final rept. 1 Apr 77-31 Dec 78,

Corporate Author : NATIONAL AEROSPACE LAB AMSTERDAM (NETHERLANDS)

Personal Author(s) : Tijdeman, H

PDF Url : ADA214740

Report Date : Jul 1979

Pagination or Media Count : 27

Abstract : The aim of the proposed investigation was to generate a set of theoretical and experimental unsteady aerodynamic data for an advanced type airfoil. This set of data should serve as a standard for the comparison and the evaluation of computational methods for two-dimensional unsteady transonic flow. For this purpose it was intended to complement the results of the wind tunnel tests conducted at NLR on the supercritical NLR 7301 airfoil with theoretical results. The statement of work of the intended investigation was: NLR provides the contour data of the 'shock free' NLR 7301 airfoil section, together with the hodograph solution for the design condition; and NLR provides the measured steady and unsteady pressure distributions in three characteristic flow conditions; subsonic flow, transonic flow with a well developed supercritical region terminated by a shock wave and the 'shock free' design condition. (sdw)

Descriptors :   *SUPERCRITICAL FLOW, *UNSTEADY FLOW, AIRFOILS, CONTOURS, FLOW, NUMERICAL METHODS AND PROCEDURES, OSCILLATION, PRESSURE DISTRIBUTION, REGIONS, SHOCK, SHOCK WAVES, STEADY STATE, SUBSONIC FLOW, SUPERCRITICAL AIRFOILS, TRANSONIC FLOW, TWO DIMENSIONAL FLOW, WIND TUNNEL TESTS

Subject Categories : Fluid Mechanics
      Aircraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE