TY - GEN
T1 - A STATIC STABILITY COMPARISON OF WIND TUNNEL AND COMPUTATIONAL FLUID DYNAMICS METHODS
AU - Fitzgerald, L. K.
AU - Niven, A. J.
AU - Griffin, P. C.
N1 - Publisher Copyright:
© 2022 ICAS. All Rights Reserved.
PY - 2022
Y1 - 2022
N2 - The design of the modern aircraft has greatly evolved over the past century. Aircraft are now more manoeuvrable, controllable, and capable of flight in extreme flight envelopes than ever before. With these advances in aircraft design, there have come concurrent advances in aircraft stability determination. This research explores these advances in the form of the applicability of determining static stability derivatives using Computational Fluid Dynamics (CFD) methodologies. The focus of this work lies in the evaluation of the static pitch stability derivative (Cmα) and the weathercock directional stability derivative (Cnβ). A wind tunnel assessment of the Standard Dynamics Model was carried out at a Reynolds number of 94000, and this data was used as benchmark data for the CFD simulation. On examination, the agreement between CFD and wind tunnel obtained loads and derivatives was encouraging. It was observed that both the heading and pitch stability derivatives varied considerably over the angle of attack regime. In the low angle of attack envelope, the aircraft is directionally stable up until 25° degrees where its stability fluctuates further throughout the angle of attack range. In pitch, the SDM only satisfies the static stability criterion over select angle of attack envelopes and is in fact unstable in the linear range. After an angle of attack of 50°, it maintains stability throughout the remainder of the high angle of attack range.
AB - The design of the modern aircraft has greatly evolved over the past century. Aircraft are now more manoeuvrable, controllable, and capable of flight in extreme flight envelopes than ever before. With these advances in aircraft design, there have come concurrent advances in aircraft stability determination. This research explores these advances in the form of the applicability of determining static stability derivatives using Computational Fluid Dynamics (CFD) methodologies. The focus of this work lies in the evaluation of the static pitch stability derivative (Cmα) and the weathercock directional stability derivative (Cnβ). A wind tunnel assessment of the Standard Dynamics Model was carried out at a Reynolds number of 94000, and this data was used as benchmark data for the CFD simulation. On examination, the agreement between CFD and wind tunnel obtained loads and derivatives was encouraging. It was observed that both the heading and pitch stability derivatives varied considerably over the angle of attack regime. In the low angle of attack envelope, the aircraft is directionally stable up until 25° degrees where its stability fluctuates further throughout the angle of attack range. In pitch, the SDM only satisfies the static stability criterion over select angle of attack envelopes and is in fact unstable in the linear range. After an angle of attack of 50°, it maintains stability throughout the remainder of the high angle of attack range.
KW - Computational Fluid Dynamics
KW - Standard Dynamics Model
KW - Static Stability Derivatives
KW - Wind Tunnel Testing
UR - http://www.scopus.com/inward/record.url?scp=85159668773&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:85159668773
T3 - 33rd Congress of the International Council of the Aeronautical Sciences, ICAS 2022
SP - 2180
EP - 2202
BT - 33rd Congress of the International Council of the Aeronautical Sciences, ICAS 2022
PB - International Council of the Aeronautical Sciences
T2 - 33rd Congress of the International Council of the Aeronautical Sciences, ICAS 2022
Y2 - 4 September 2022 through 9 September 2022
ER -