Non-axisymmetric exhaust nozzles exiting at or near the trailing edge of a lifting surface offer advanced aircraft configurations improved performance by induced aerodynamic effects. An experimental investigation of these induced effects was conducted at Mach numbers from 0.3 to 0.9 on a half-span wing body configuration with a vectoring (0, 15, 30 degree) non-axisymmetric exhaust nozzle incorporated into the wing trailing edge. Results indicate that at all Mach numbers, the thrustremoved lift, drag, and pitching moment coefficients for the wing body increased with increasing nozzle vectoring. Using the untrimmed data, an optimum drag polar can be formed which uses all three vector angles. As the nozzle pressure ratio increased, the induced effects on the wing aerodynamics tend to increase proportionally.(rsetz)
An investigation of the induced aerodynamic effects of a vectored non-axisymmetric exhaust nozzle
Eine Untersuchung der induzierten aerodynamischen Wirkung von vektorverstellbaren, nichtachsensymmetrischen Abgasduesen
AIAA-Papers ; 1-8
1978
8 Seiten, 25 Bilder, 3 Tabellen, 8 Quellen
Conference paper
English
LUFTFAHRT , TURBOLUFTSTRAHLTRIEBWERK , MACHZAHL , AERODYNAMIK , STROEMUNGSGESCHWINDIGKEIT , STROEMUNGSPROFIL , TRAGFLUEGELUMSTROEMUNG , TRAGFLUEGEL , SCHUBDUESE , ANSTELLWINKEL (TRAGFLUEGEL) , ABGASSTROEMUNG , GESCHWINDIGKEIT , WINKELGESCHWINDIGKEIT , DRUCKAENDERUNG , UNSYMMETRIE , MATHEMATISCHES MODELL