In this study the nozzle/afterbody flowfield of a generic hypersonic cruise configuration has been investigated using several modern wind tunnel test techniques to provide both CFD correlation data and an understanding of the flow physics. A wind tunnel model with three different upswept afterbodies and simulated propulsion effects was designed, fabricated and tested at transonic and low supersonic conditions to explore the effects of Mach number and Reynolds number variation. The model was then tested again at low subsonic speeds using a 3-D laser velocimeter to quantify the turbulent behavior of the jet-freestream mixing region. For all three afterbodies tested, it was found that a high jet-to-freestream velocity ratio promoted jet attachment to the nozzle surface. In addition, the low-speed laser velocimeter data, when reduced and analyzed using a wake integration technique, showed that the crossflow velocities generated by the half-nozzle flow contribute heavily to the thrust losses. Further, the amount of thrust vectored by this propulsion integration concept also indicates that similar configurations may share common penalties in loss of thrust recovery.
Investigations of low-speed nozzle/afterbody performance for a generic hypersonic configuration
Wechselwirkung zwischen dem langsamen Duesenstrahl und dem hinteren Teil des Flugzeugrumpfes fuer eine Ueberschallflugzeugentwicklung
AIAA-Papers ; Jan ; 1-10
1988
10 Seiten, 20 Bilder, 10 Quellen
Conference paper
English
STROEMUNGSVORGANG , UMSTROEMUNG , VERKEHRSFLUGZEUG , WINDKANAL , UEBERSCHALLGESCHWINDIGKEIT , WECHSELWIRKUNG , FLUGZEUGRUMPF , MACH-ZAHL , REYNOLDS-ZAHL , EINFLUSSGROESSE , UNTERSCHALLGESCHWINDIGKEIT , LASER DOPPLER ANEMOMETER , DREIDIMENSIONALE STROEMUNG , DUESENSTROEMUNG , STRAHLTRIEBWERK , SCHUB (ANTRIEB)