XV-15 aeroacoustic testing at NASA Ames

Abstract

Two tests were completed by NASA Ames Research Center to measure the acoustics and performance of an XV-15 rotor. These tests were a flight test of the XV-15 aircraft and a wind tunnel test of a single, full-scale XV-15 rotor. Acoustics and performance measurements were obtained for helicopter-mode forward flight and descent conditions. This paper summarizes the data obtained from these tests. Comparisons are made of blade loads and acoustics data obtained from the two tests. These comparisons indicate that, for the single test condition examined, pitch-link, flap bending, and chord bending loads agree reasonably well. No discernible effect was observed on blade bending loads by the presence of the wind tunnel test model or aircraft wing/fuselage. Several alternative methods of correlating flight and wind tunnel test data are discussed. These comparisons provide insight into both wind tunnel and flight test experimental techniques and capabilities.