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Aircraft
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title: AIAA Journal of Aircraft
Measurement and Identification of Supersonic Stationary Crossflow Waves Based on Sublimation Method
Aiming at the crossflow transition problem of supersonic swept wings, an experimental study on the measurement and identification of
...Theory of Machine Learning Assisted Structural Optimization Algorithm and Its Application
Noise Prediction of a Distributed Propulsion System Using the Actuator Line Method
Within this study, the capability of the actuator line method to simulate the noise of a high-lift distributed propulsion system is
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A three-dimensional combustion instability model is presented to study the effects of the wall impedance distributions of annular
...Leading-Edge Cone Method for Waverider Design
Multibody-Dynamics Approach to Study the Deformation and Aerodynamics of an Insect Wing
Modeling of Advanced Helmholtz Resonator Liners with a Flexible Wall
Acoustic liners are an effective way to dampen aircraft noise. Conventional single-degree-of-freedom liners consist of a perforated
...Fast and Robust Computation of Optimal Rotor Designs Using Blade Element Momentum Theory
Recent years have seen a renewed interest in rotary-wing aircraft, due to the emergence of urban air mobility. In the conceptual design
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The hydrodynamic characteristics and associated far-field acoustics of installed elliptical jets were studied using linear models based
...Instability of Rotating-Cone Boundary Layer in Axial Inflow: Effect of Cone Angle
Boundary-layer instability on a rotating cone induces coherent spiral vortices that are linked to the onset of laminar–turbulent
...Verification of the Transition Model in OVERFLOW and FUN3D
The findings of the recent AIAA and NATO workshops on transition modeling have underscored the importance of verifying the transition
...Summary of the 4th High-Lift Prediction Workshop Hybrid RANS/LES Technology Focus Group
This paper summarizes the collective efforts of multiple teams that contributed to the hybrid RANS/LES technical focus group for the 4th
...Characterization of Disturbance Resonance in Postshock of Blunt Body in Hypersonic Flow
A pitot probe is commonly used for the disturbance quantification of a hypersonic freestream, but the pitot results cannot reflect the
...Characterization of Slat Noise Radiation from a High-Lift Common Research Model
A test campaign was conducted in the open-jet test section of the NASA Langley Research Center’s 14- by 22-Foot Subsonic Tunnel on a 10
...FREEDOM: Validated Method for Rapid Assessment of Incipient Faults of Aerospace Systems
DPW-7: Steady and Unsteady Computations of the Common Research Model at Different Reynolds Numbers
This article presents the numerical computations performed at ONERA for the Seventh AIAA Drag Prediction Workshop. By introducing
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Propulsion-Airframe Integration for Conceptual Redesign of a Low-Boom Supersonic Transport
Two-Way Blade Modeling Method for Structural Redesign of Compressor Blades