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Shu Sun, R. Guo, Yi-zhao Wu (2007)
Characterization and Performance Enhancement of Submerged Inlet with Flush-Mounted Planar Side EntranceJournal of Propulsion and Power, 23
M. Miansari, Sajad Ghezelsofloo, D. Toghraie (2020)
Numerical Investigation of Geometrical Design Effect on the Submerged Inlet Aerodynamics CharacteristicsInternational Journal of Aeronautical and Space Sciences, 21
Shu Sun, H. Tan, Chenxi Wang (2016)
Submerged Inlet Performance Enhancement Using a Unique Bump-Shaped Vortex GeneratorJournal of Propulsion and Power, 32
(2001)
Junction flows
F. Knoth, C. Breitsamter (2017)
Flow Analysis of a Helicopter Engine Side Air IntakeJournal of Propulsion and Power, 33
R. Steijl, G. Barakos (2009)
Computational Study of Helicopter Rotor-Fuselage Aerodynamic InteractionsAIAA Journal, 47
R. Mineck, Susan GortonLangley (2000)
Steady and Periodic Pressure Measurements on a Generic Helicopter Fuselage Model in the Presence of a Rotor
V. Jovanovic, E. Taşkinoğlu, D. Knight, G. Elliott (2004)
Experimental Investigation of a Submerged Subsonic InletJournal of Propulsion and Power, 22
(2002)
Radar cross section characteristics of three different inlet-body missile models
J. Wang, W. Bi, Q. Wei (2009)
Effects of an upstream inclined rod on the circular cylinder–flat plate junction flowExperiments in Fluids, 46
R. Cummings, J. Forsythe, S. Morton, K. Squires (2003)
Computational challenges in high angle of attack flow predictionProgress in Aerospace Sciences, 39
J. Yin (2019)
Investigation of Rotor Noise Shielding Effects by the Helicopter Fuselage in Forward FlightJournal of Aircraft
E. Quon, Marilyn Smith, G. Whitehouse, D. Wachspress (2012)
Unsteady Reynolds-Averaged Navier-Stokes-Based Hybrid Methodologies for Rotor-Fuselage InteractionJournal of Aircraft, 49
H. Nam, Y. Park, O. Kwon (2006)
Simulation of Unsteady Rotor-Fuselage Aerodynamic Interaction Using Unstructured Adaptive MeshesJournal of The Korean Society for Aeronautical & Space Sciences, 33
Daishu Cheng, H. Tan, Shu Sun, Y. Tong (2012)
Computational Study of a High-Performance Submerged Inlet with Bleeding VortexJournal of Aircraft, 49
T. Quackenbush, C. Lam, D. Bliss (1994)
Vortex Methods for the Computational Analysis of Rotor/Body InteractionJournal of The American Helicopter Society, 39
B. Sumer, N. Christiansen, J. Fredsøe (1997)
The horseshoe vortex and vortex shedding around a vertical wall-mounted cylinder exposed to wavesJournal of Fluid Mechanics, 332
(1985)
Intake Aerodynamics
Ye Yuan, Renliang Chen, Pan Li (2019)
Trim investigation for coaxial rigid rotor helicopters using an improved aerodynamic interference modelAerospace Science and Technology
F. Akram, Matthew Prior, D. Mavris (2010)
Design Space Exploration of Submerged Inlet Capturing Interaction between Design Parameters
O. Rand, A. Gessow (1989)
Model for investigation of helicopter fuselage influence on rotor flowfieldsJournal of Aircraft, 26
F. Menter (1994)
Two-equation eddy-viscosity turbulence models for engineering applicationsAIAA Journal, 32
A. Conlisk (2001)
Modern helicopter rotor aerodynamicsProgress in Aerospace Sciences, 37
The submerged inlet is an attractive configuration for advanced helicopters due to its high stealth performance and low external drag. In this paper, a submerged inlet, integrated with a ROBIN helicopter fuselage and a simplified power output shaft, is experimentally and numerically investigated to obtain the basic flow characteristics under a freestream velocity of 23.6 m/s. The results indicate that the pylon ahead of the inlet induces a horseshoe vortex. Though the vortex is ingested into the inlet, it has little effect on the internal flows and can be neglected. When the airflow enters into the inlet, it interacts with the shaft with a large incidence angle, yielding a vortex pair. At the leeside of the shaft, the two side flows of the shaft impinge at the center plane, generating a local high-pressure region at the azimuthal angle of 180°, which forces the boundary layer to roll up a counter-rotating vortex pair. In addition, the airflow adjacent to the cowl lip accelerates rapidly, resulting in a local low-pressure region at the azimuthal angle of 0°. Therefore, the inlet duct has a strong circumferential pressure gradient, which originates from an azimuthal angle of 180° to 0° and induces a vortex pair at the azimuthal angle of 0°. The three vortex pairs are the main origins of the distortion at the duct exit plane, among which the one near the cowl lip with the azimuthal angle of 0° plays the dominant role. Additionally, as the velocity ratio increases from 3.9 to 5.5, the circumferential pressure gradient and the cowl lip vortex get intensified, which causes that the total-pressure recovery coefficient drops by 0.5% and the distortion index increases by 28%.Graphic abstractA submerged inlet, integrated with a ROBIN helicopter fuselage and a simplified power output shaft, is experimentally and numerically investigated. Three vortex pairs, which locate at the azimuthal angle of 0°, the leeside of the shaft, and 180° of the inlet surface, are the main origins of the distortion of the inlet, among which the one near the cowl lip with the azimuthal angle of 0° plays the dominant role. As the velocity ratio increases, the circumferential pressure gradient gets intensified, leading to stronger vortex pairs.[graphic not available: see fulltext]
"Acta Mechanica Sinica" – Springer Journals
Published: Jan 4, 2021
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