RAE Rests on AGARD Tailplane

• Main Author: Kaynes, I W
• Format: Report
• Language: English
• Subjects: AERODYNAMIC CONFIGURATIONS; Aerodynamics; AEROELASTICITY; Aircraft; COMPONENT REPORT; FOREIGN REPORT; MILITARY AIRCRAFT; NATO FURNISHED; PRESSURE; TAILLESS AIRCRAFT; UNSTEADY AERODYNAMICS; WINGS

This data set relates to tests at RAE which were carried out and reported by D (3 Mabey, B L Welsh and B E Cripps, ref. 1. The tests were undertaken to provide data for the validation of codes for the prediction of both steady and unsteady pressures on low aspect ratio configurations, suitable for the wings or controls of military aircraft. Comprehensive measurements have not been available to verify such codes, although some measurements were obtained during the NORA programmer. This was a collaborative test on a low aspect ratio model oscillating about a swept axis, with the main aim of investigating dynamic interference in transonic wind tunnels. NORA was named after the participating organizations: NLR, ONERA, RAE, and AVA (branch of DFVLR). For the verification of transonic theories, a serious limitation of the NORA tests was that the steady and unsteady pressures were measured at different sections, with only a few measurements at each section. To overcome the lack of comprehensive measurements on a low aspect ratio configuration it was decided to make extensive measurements of steady and unsteady pressures on a model of the AGARD SMP (Structures and Materials Panel) tailplane, which has a planform similar to that of the wings and controls used on many military aircraft. Previous tests have shown that for experiments in time-dependent aerodynamics it is essential to minimise aeroelastic distortion when the model is driven. To avoid measured pressures with a significant contribution due to the distortion in the present tests, the model had to move almost as a rigid body when it was oscillated at high frequencies. Hence the model was constructed in carbon fibre, which provided both high stiffness and low inertia. The high stiffness was aided by the 1 0% thickness of the section used, which is significantly thicker than the sections usually employed on combat aircraft. The original document contains color images, p271-294. This article is from ADA390566 Verification and Validation Data for Computational Unsteady Aerodynamics (Donnees de verification et de valadation pour l'aerodynamique instationnaire numerique)