Remiger, Jonas; Schwagerus, Nils; Stößel, Marcel; Kožulovic, Dragan; Krummenauer, Michael
Dokumenttyp:
Konferenzbeitrag / Conference Paper
Titel:
Evaluation of a Subsonic Fluidic Thrust Vectoring Concept
Untertitel:
Part II: Impact on Propulsion System and Mission Performance
Titel Konferenzpublikation:
AIAA AVIATION 2023 Forum
Veranstalter (Körperschaft):
American Institute of Aeronautics and Astronautics
Konferenztitel:
AIAA Aviation Forum (2023, San Diego,Calif.)
Tagungsort:
San Diego, Calif., USA
Jahr der Konferenz:
2023
Datum Beginn der Konferenz:
12.06.2023
Datum Ende der Konferenz:
16.06.2023
Jahr:
2023
Sprache:
Englisch
Abstract:
This paper presents an investigation into the feasibility and performance of fluidic
thrust vector control based on the Coanda effect for smaller aircraft. The study focuses
on medium-mass unmanned airborne systems and demonstrates that fluidic thrust
vector nozzles are viable at both the engine and aircraft level. A fully coupled simulation
between the aircraft and its engine is conducted for an example generic mission with two
variants to deflect the thrust vector. The results show that using fluidic thrust vectoring
systems can lead to slight improvements in aerodynamic characteristics while reducing
control surface size and thereby drag and radar cross-section. However, this comes at
the cost of a slight increase in fuel consumption and a loss in the available engine thrust
during flight situations with high power demand. The aerodynamic parameters used to
model the fluidic thrust vector nozzle are obtained from CFD calculations «
This paper presents an investigation into the feasibility and performance of fluidic
thrust vector control based on the Coanda effect for smaller aircraft. The study focuses
on medium-mass unmanned airborne systems and demonstrates that fluidic thrust
vector nozzles are viable at both the engine and aircraft level. A fully coupled simulation
between the aircraft and its engine is conducted for an example generic mission with two
variants to deflect the thrust vector. The results show t... »