Ground effects on the aerodynamics of a wing with slot type distributed propulsion system for VTOL applications
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ChengAn Bai
Abstract
During take-off of a vertical take-off and landing (VTOL) aircraft, ground effects can cause a downward force on the aircraft body and wings. The downward force could substantially reduce the payload of the aircraft, which is undesirable. This paper investigates the ground effects related to VTOL applications with distributed propulsion. A slot jet is used to simulate the distributed propulsion system. A model of a wing with a slot jet placed near the trailing edge of the wing is investigated. The slot jet is almost perpendicular to the ground to provide a vertical thrust. Experimental and numerical methods are used to investigate the aerodynamic performance of this model. Theoretical analysis is carried out to understand the formation mechanism of the low pressure region on the lower surface of the wing, which causes the downward force. The flow physics of the jet inducing ground vortex is investigated. It is found that the convection term in the ground vortex area is the main source of the pressure reduction. Based on the flow mechanism, a redesigned configuration is proposed to reduce the negative effect of the ground vortex. The flow structures such as the tip vortex are also investigated.
Funding source: National Natural Science Foundation of China (NSFC)
Award Identifier / Grant number: No. 52076001, No. 91752106
Funding source: National Science and Technology Major Project
Award Identifier / Grant number: 2019-â…¡-0011-0031
Funding source: Advanced Jet Propulsion Innovation Center (AEAC)
Award Identifier / Grant number: HKCX2022-01-015
Funding source: Science and Technology Major Project of Jiangxi Province
Award Identifier / Grant number: 20203ABC28W002
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Author contribution: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: The authors would like to acknowledge the support of National Natural Science Foundation of China (NSFC), Grant No. 52076001, No. 91752106; National Science and Technology Major Project (2019-â…¡-0011-0031); Advanced Jet Propulsion Innovation Center (AEAC), funding number HKCX2022-01-015; Science and Technology Major Project of Jiangxi Province (20203ABC28W002).
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
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© 2022 Walter de Gruyter GmbH, Berlin/Boston
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Articles in the same Issue
- Frontmatter
- The International Journal of Turbo and Jet Engines
- The aerothermodynamic cycle optimal design of a turbofan engine
- Multi-condition design optimization of groove flow control technique in an axial-flow pump
- Analysis on impulse characteristics of pulse detonation engine with nozzles
- Numerical investigation on implication of innovative hydrogen strut injector on performance and combustion characteristics in a scramjet combustor
- Optimization of Kiel geometry for better recovery factor in high temperature measurement in aero gas turbine engine
- Applicability of correlational data-mining to small-scale turbojet performance map generation
- Effect of multi-zone effusion cooling on an adiabatic flat plate for gas turbine application
- Flow quality improvement of the wind tunnel testing for a highly-loaded compressor cascade at high incidence
- Modeling and analysis of 3D radiative heat transfer in combustor
- A creep-fatigue life prediction model considering multi-factor coupling effect
- Optimization-based transient control of turbofan engines: a sequential quadratic programming approach
- Investigations on the interaction between the front and aft purge flow and the downstream vane of 1.5-stage turbine
- A study on design optimization for compressor blisks
- Exploration of an unconventional validation tool to investigate aero engine transonic fan flutter signature
- Evaluation of non-uniform water film behavior on the performance of an axial aeroengine compressor
- Predicting remaining useful life of turbofan engines using degradation signal based echo state network
- Effect of G-type integral squeeze film damper on the dynamic characteristics in rotor system
- Development of a one-dimensional code for the initial design of a micro gas turbine mixed flow compressor stage
- Numerical and experimental investigations of tip clearance effects in a high-flow-coefficient centrifugal compressor
- Experimental and numerical investigation on the effect of turboprop engine exhaust gas impingement on pusher aircraft
- Heat transfer distribution of single oblique jet impingement in crossflow under different inlet conditions
- Performance enhancement and flow separation control in an S-duct by air injection
- Gas dynamic analysis of the modern single shaft gas turbine engine flow path
- Aero engine health monitoring, diagnostics and prognostics for condition-based maintenance: an overview
- Influence of leading edge point on aerodynamic performance of asymmetric leading edge compressor airfoils
- The aerothermal performance of turbine blade squealer tip at various Reynolds numbers and Mach numbers with moving endwall
- Numerical investigation of a variable stator vane with nonuniform partial radial gaps in an annular compressor cascade
- Effect of self-recirculating casing treatment on the unsteady flow and stability of counter-rotating axial-flow compressor
- Research on temperature rise characteristics of end V-groove ring seal
- Research on the influence of honeycomb cell blockage on the seal leakage characteristics
- Vortex structure control based bleed in axial compressor cascade with tip clearance using large eddy simulation
- Development and application of a profile loss model considering the low-Re effect in low-pressure turbine
- Optimization of ACE mode transition control schedule considering geometric adjustment speed
- Numerical investigation of flow control in low-pressure turbine cascade using Gurney Flaps
- The design method of the V-shaped groove piston ring
- Control of subsonic jets using vanes as vortex generators
- Impact investigation of inlet environmental changes on the rated condition performance of a high-pressure compressor
- Research on new integral squeeze film damper vibration control of micro turbojet engine at high speed
- Effect of the distribution of the upstream probe support on performance of compressor cascade
- Effect of bypass ratio on sonic underexpanded co-flow jets with finite lip thickness
- Machine learning augmented multi-sensor data fusion to detect aero engine fan rotor blade flutter
- CFD analysis of flow control in compressor cascade using MVGs
- Quantitative investigation of the evaporation and resistance characteristics of inlet jet precooling
- Study on laser de-weight and dynamic balance technology of rotating machines
- Integrated design and analysis of inlet and missile with two side layout
- Research on turboprop engine control method based on linear parameter varying model
- Modeling and validation of the volume effect on the axial fan transient performance
- Ground effects on the aerodynamics of a wing with slot type distributed propulsion system for VTOL applications
- Multidisciplinary sensitivity analysis for turbine blade considering thickness uncertainties
- Accurate measurement and evaluation method of axial compressor efficiency under the influence of multiple factors
- Control mechanism of secondary flow in a turbine cascade with non-axisymmetric endwall profiling under Co-rotating incoming vortex
- Infrared simulation of aircraft rear fuselage based on a coupled CFD method
- Effect of multi-hole trench cooling on an adiabatic flat plate for gas turbine application
- Numerical study of transition process in different zones of a compressor cascade channel
