Investigation Of A Technique For Measuring Dynamic Ground Effect In A Subsonic Wind Tunnel
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Investigation of a Technique for Measuring Dynamic Ground Effect in a Subsonic Wind Tunnel
Author: National Aeronautics and Space Administration (NASA)
language: en
Publisher: Createspace Independent Publishing Platform
Release Date: 2018-06
To better understand the ground effect encountered by slender wing supersonic transport aircraft, a test was conducted at NASA Langley Research Center's 14 x 22 foot Subsonic Wind Tunnel in October, 1997. Emphasis was placed on improving the accuracy of the ground effect data by using a "dynamic" technique in which the model's vertical motion was varied automatically during wind-on testing. This report describes and evaluates different aspects of the dynamic method utilized for obtaining ground effect data in this test. The method for acquiring and processing time data from a dynamic ground effect wind tunnel test is outlined with details of the overall data acquisition system and software used for the data analysis. The removal of inertial loads due to sting motion and the support dynamics in the balance force and moment data measurements of the aerodynamic forces on the model is described. An evaluation of the results identifies problem areas providing recommendations for future experiments. Test results are validated by comparing test data for an elliptical wing planform with an Elliptical wing planform section with a NACA 0012 airfoil to results found in current literature. Major aerodynamic forces acting on the model in terms of lift curves for determining ground effect are presented. Comparisons of flight and wind tunnel data for the TU-144 are presented.Graves, Sharon S.Langley Research CenterGROUND EFFECT (AERODYNAMICS); AERODYNAMIC FORCES; SUBSONIC WIND TUNNELS; WIND TUNNEL TESTS; DATA ACQUISITION; AIRCRAFT DESIGN; AERODYNAMIC CONFIGURATIONS; AIRCRAFT CONFIGURATIONS; SLENDER WINGS; WING PLANFORMS; SUPERSONIC TRANSPORTS; TU-144 AIRCRAFT; VERTICAL MOTION
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