Aerodynamic design assessment and comparisons of the MULDICON UCAV concept

Nangia, R. K.; Ghoreyshi, Mehdi; Rooij, M.P.C. van; Cummings, Russell M.

doi:10.1016/j.ast.2019.105321

Cited by 12 publications

(12 citation statements)

References 21 publications

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“…It can be seen the small apex vortex develops close to the wing, and when AOA is increased, this flow pattern mostly remains unchanged (Nangia et al, 2019;Loeser et al, 2010).…”

Section: Flow Visualizationmentioning

confidence: 90%

“…This default value is far too high, as proven by the fact that Fluent diverged in the AMG solver when iterations began. While a flow courant number of less than ten is not advised (Matsson, 2021). Furthermore, the Courant number of 50 has been used in several past aerodynamics research (Fuller, 2012).…”

Section: Numerical Modelingmentioning

confidence: 99%

“…Pressure-velocity coupling SettingsScheme Coupled Gradient Least squares cell-based Pressure Standard MomentumSecond-order upwind Turbulent kinetic energy Second-order upwind Specific dissipation rate Second-order upwind Source: Table2byMatsson (2021) …”

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confidence: 99%

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Flow characterization of low sweep MULDICON wing at low speed

Haider

Mansor

Mat

et al. 2023

AEAT

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Purpose The flow topology for multi-disciplinary configuration (MULDICON) wing is very complicated and nonlinear at low to high angle of attack (AOA). This paper aims to provide the correlation between the unsteadiness and uncertainties of the flow topology and aerodynamic forces and moments above MULDICON WING at a medium to a higher AOA. Design/methodology/approach The experimental and computational fluid dynamics methods were used to investigate a generic MULDICON wing. During the experiment, the AOA were varied from α = 5° to 30°, whereas yaw angle varies between β = ±20° and Reynolds number between Re = 3.0 × 105 and Re = 4.50 × 105. During the experiments steady-state loading, dynamic loading and flow visualization wind tunnel methods were used. Findings The standard deviation quantified the unsteadiness and uncertainties of flow topology and predicted that they significantly affect the pitching moment (Cm) at medium to higher AOA. A strong correlation between flow topology and Cm was exhibited, and the experiment data was well validated by previous numerical work. The aerodynamic center was not fixed and shifted toward the wing apex when AOA is increasing. For a = 10°, the flow becomes more asymmetric. Power spectral densities plots quantify the flow separation (apex vortex, leading-edge vortex and vortex breakdown) over the MULDICON wing. Originality/value The application and comparison of steady-state and dynamic loading data to quantify the unsteadiness and uncertainties of flow topology above the MULDICON wing.

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“…It can be seen the small apex vortex develops close to the wing, and when AOA is increased, this flow pattern mostly remains unchanged (Nangia et al, 2019;Loeser et al, 2010).…”

Section: Flow Visualizationmentioning

confidence: 90%

Section: Numerical Modelingmentioning

confidence: 99%

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Flow characterization of low sweep MULDICON wing at low speed

Haider

Mansor

Mat

et al. 2023

AEAT

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“…The X-47B blended wing body aircraft is selected as the basic configuration. [16][17] This aircraft is a U.S. experimental unmanned combat aircraft. The aircraft is 11.63 m long with a wingspan of 18.92 m, and the wings can be folded when the aircraft is shipborne.…”

Section: Calculation Modelmentioning

confidence: 99%

Intake grille design for an embedded ventilation-and-cooling system in an aircraft

Huang

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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An inlet grille typically needs to be installed at the inlet of the air intake of the ventilation-and-cooling system embedded in airborne electronic equipment to improve pneumatic stealth performance. Here, a typical flying wing model is used as a case study, and a computational fluid dynamics (CFD) simulation is performed. The flow resistance characteristics of the air intake of the opening of the ventilation-and-cooling system on a flat fuselage surface with and without an inlet grille are analyzed at different flow rates and Mach 0.25. The effects of the grille opening shape, diversion angle, thickness, aperture size, and hole shape on the flow resistance characteristics are investigated in detail. The grille is found to effectively guide airflow entry: although the flow resistance at the inlet is increased, the flow resistance at the inlet and outlet of the air intake is significantly reduced. The optimal developments of the outflow and flow resistance characteristics are obtained for a quadrilateral opening. The smaller the diversion angle is, the smoother the airflow entry, and the higher the quality of the internal airflow. The rectification, viscous resistance, and weight exhibit opposing trends with increasing thickness and must be comprehensively considered in designing an optimal scheme. A large-aperture grille ensures good flow patency at low flow rates, whereas a small-aperture grille can reduce flow perturbations and separation at high flow rates by smoothly guiding air into the intake. A grille with round holes has a better spanwise and chordwise balancing effect on the airflow and better flow resistance characteristics than a grille with diamond-shaped holes.

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“…Designing such a platform for sustainable supersonic cruise at Mach 1.60 is the goal of the current research project. The academic research projects are mostly focused on subsonic systems with general configurations, [2][3][4] and the list of operational unmanned flight systems consists of different types of cruise missiles, target drones, 5 and subsonic reconnaissance and attack systems, 6 but not many supersonic air-breathing flight vehicles with the ability for runway takeoff and landing; the JAXA S3TD Silent Supersonic Technology Demonstrator, for flight at Mach 1.6-1.7, first presented by Murakami 7,8 in 2006, is an example for which its aerodynamic configuration is unlike high maneuverable systems. In 2012, a concept of a light supersonic drone by Sibylle Walter 9 presented an economic single normal shock system to create a test bed for academic research such as thrust vectoring and control algorithms at Mach 1.40.…”

Section: Introductionmentioning

confidence: 99%

The inlet flow structure of a conceptual open-nose supersonic drone

Saheby

Shen

Hays

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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This study describes the aerodynamic efficiency of a forebody–inlet configuration and computational investigation of a drone system, capable of sustainable supersonic cruising at Mach 1.60. Because the whole drone configuration is formed around the induction system and the design is highly interrelated to the flow structure of forebody and inlet efficiency, analysis of this section and understanding its flow pattern is necessary before any progress in design phases. The compression surface is designed analytically using oblique shock patterns, which results in a low drag forebody. To study the concept, two inlet–forebody geometries are considered for Computational Fluid Dynamic simulation using ANSYS Fluent code. The supersonic and subsonic performance, effects of angle of attack, sideslip, and duct geometries on the propulsive efficiency of the concept are studied by solving the three-dimensional Navier–Stokes equations in structured cell domains. Comparing the results with the available data from other sources indicates that the aerodynamic efficiency of the concept is acceptable at supersonic and transonic regimes.

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Aerodynamic design assessment and comparisons of the MULDICON UCAV concept

Cited by 12 publications

References 21 publications

Flow characterization of low sweep MULDICON wing at low speed

Flow characterization of low sweep MULDICON wing at low speed

Intake grille design for an embedded ventilation-and-cooling system in an aircraft

The inlet flow structure of a conceptual open-nose supersonic drone

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