Work

Lifting-Line Predictions for the Ideal Twist Effectiveness of Spanwise Continuous and Discrete Control Surfaces

Year: 2025

Type: article

Abstract: Modern materials and manufacturing technologies have allowed the construction of morphing wings that are able to continuously vary certain airfoil parameters such as twist, camber, or control surface deflection as a function of span. This work presents a twist effectiveness parameter as a means of comparing the ideal aerodynamic efficiency of spanwise continuous control surfaces (morphing wings) and spanwise discrete control surfaces (standard wings). A numerical algorithm is used to compute the twist effectiveness of both continuous and discrete control-surface designs over a wide range of planform shapes with evenly spaced actuation for inviscid, incompressible flow. Results included here show that using continuous control surfaces instead of discrete control surfaces reduces induced drag by less than 5% for most applications.

Source: Applied Sciences

DOI: 10.3390/app15063383

Authors: Zachary S. Montgomery, Douglas F. Hunsaker, James J. Joo

Institutions: Utah State University, United States Air Force Research Laboratory, Wright-Patterson Air Force Base, Wright Laboratory

Language: English

Topic: Aeroelasticity and Vibration Control

Subfield: Aerospace Engineering

Field: Engineering

Domain: Physical Sciences

Open Access status: gold

Estimated APC paid: $2,896

Funder: Office of Naval Research