Numerical Assessment of Leading- and Trailing-Edge Control on a Swept Lambda Wing

Tormalm, Magnus; Roy, Jean-François Le; Morgand, Stephane

doi:10.2514/1.c033820

Journal of Aircraft

2018

DOI: 10.2514/1.c033820

|View full text |Cite

Numerical Assessment of Leading- and Trailing-Edge Control on a Swept Lambda Wing

Magnus Tormalm

Jean-François Le Roy

Stephane Morgand

Help me understand this report

Search citation statements

Order By: Relevance

Paper Sections

Select...

Citation Types

Supporting

Mentioning

Contrasting

Year Published

2023

Publication Types

Select...

Article1

Relationship

Self Cite0

Independent1

Authors

Journals

Cited by 1 publication

(1 citation statement)

References 21 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…It was used to evaluate utilizing CFD to estimate the S&C characteristics of UCAVs. The research task group AVT-161 was later expanded by the task group NATO STO/AVT-201 to provide S&C databases for UCAV simulation and to predict the effects of the control surface [8,28,33,35,36,[46][47][48][49]. Liersch et al [15] provided conceptual design analyses for the SACCON configuration and compared the aerodynamic performance of the SACCON model using lowand high-fidelity approaches.…”

mentioning

confidence: 99%

Conceptual Design of a Nonconstant Swept Flying Wing Unmanned Combat Aerial Vehicle

Aleisa¹,

Kontis²,

Pirlepeli³

et al. 2023

Journal of Aircraft

View full text Add to dashboard Cite

The design of unmanned combat aerial vehicles (UCAVs) is primarily governed by the low-observability requirement for military applications rather than aerodynamic performance. The conceptual design and optimization of UCAV models via size and shape variables for different missions in different flow regimes form a research area for military vehicle design. Flying wing UCAVs experience flow separation during takeoff and landing, and furthermore exhibit stability issues. The aerodynamic performance of these UCAVs can be significantly improved by redesigning their leading-edge sweep angle and wing planform. In the present work, the initial weight determination, aerodynamic sizing, and planform with and without inlet lip integration, and the conceptual design of a nonconstant leading-edge flying wing UCAV configuration are performed. Next, the obtained conceptual design is downscaled 1:20 to be used as a wind-tunnel model and optimized for low-speed conditions using a kriging-based surrogate model with a vortex-lattice method to maximize the lift-to-drag ratio. Later, the optimized design is validated using an open-source computational fluid dynamics code, OpenFOAM 8.0, to verify the accuracy of the surrogate model and to investigate the aerodynamic characteristics. The optimized UCAV design exhibited improved aerodynamic characteristics in terms of the lift-to-drag ratio. Furthermore, the aerodynamic performance and flowfield of the optimized UCAV model with and without inlet lip integration have been evaluated at low and high speeds.

show abstract

mentioning

confidence: 99%

Conceptual Design of a Nonconstant Swept Flying Wing Unmanned Combat Aerial Vehicle

Aleisa¹,

Kontis²,

Pirlepeli³

et al. 2023

Journal of Aircraft

View full text Add to dashboard Cite

show abstract

scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citations–citations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.

Contact Info

hi@scite.ai

10624 S. Eastern Ave., Ste. A-614

Henderson, NV 89052, USA

Blog Terms and Conditions API Terms Privacy Policy Contact Cookie Preferences Do Not Sell or Share My Personal Information

Made with 💙 for researchers

Part of the Research Solutions Family.

Numerical Assessment of Leading- and Trailing-Edge Control on a Swept Lambda Wing

Cited by 1 publication

References 21 publications

Conceptual Design of a Nonconstant Swept Flying Wing Unmanned Combat Aerial Vehicle

Conceptual Design of a Nonconstant Swept Flying Wing Unmanned Combat Aerial Vehicle

Contact Info

Product

Resources

About