Computational Fluid Dynamic Analysis of the Flow Around a Propeller Blade of Multirotor Unmanned Aerodynamic Vehicle

2021 ◽  
Author(s):  
Victor H. Martinez ◽  
Kiran Bhaganagar
Keyword(s):  
Fluid Dynamic ◽  
Aerodynamic Characteristics ◽  
The Body ◽  
Power Coefficient ◽  
Navier Stokes ◽  
Propeller Blade ◽  
Computational Fluid Dynamic Analysis ◽  
Thrust Coefficient ◽  
Emergency Rescue ◽  
Propeller Blades

Abstract Multirotor Unmanned Aerodynamic Vehicles (MUAV) have been a high interest topic in the aerodynamic community for its many applications, such as, logistics, emergency rescue, agriculture data collection, and environmental sensing to name a few. MUAV propeller blades create a highly complex turbulent fluid flow around the body and the environment around it. The flow physics generated from the rotation of the propeller blades were studied in this paper along with the analysis of aerodynamic characteristics. A Reynolds Average Navier-Stokes (RANS) Computational Fluid Dynamics (CFD) analysis of a propellor blade from a MUAV has been performed to quantify the aerodynamic effects. For this purpose, the verification and validation of the commercially available CFD solver COMSOL Multiphysics v5.5 was performed using the NACA 0012 airfoil which is one of the most highly studied of the NACA family. With this validation it created confidence on the results for simulating a MUAV propeller and evaluate the aerodynamic characteristics of thrust coefficient (KT), power coefficient (KP), and Efficiency (η). These characteristics were compared against experimental data and results showed to have a similar trend. This showed that the CFD solver is capable of solving the aerodynamic characteristics of any propeller blade geometry.

scholarly journals Numerical Analysis of Thermal and Aerodynamic Fields in a Channel with Cascaded Baffles

2017 ◽  
Vol 62 (1) ◽  
pp. 16 ◽  
Author(s):  
Younes Menni ◽  
Ahmed Azzi
Keyword(s):  
Fluid Dynamic ◽  
Reynolds Numbers ◽  
Navier Stokes ◽  
Turbulent Regime ◽  
Transfer Coefficients ◽  
Computational Fluid Dynamic Analysis ◽  
Heat Transfer Coefficients ◽  
Discretization Algorithm ◽  
Volume Method ◽  
The Impact

A computational fluid dynamic analysis of thermal and aerodynamic fields for an incompressible steady-state flow of a Newtonian fluid through a two-dimensional horizontal rectangular section channel with upper and lower wall-attached, vertical, staggered, transverse, cascaded rectangular-triangular (CRT), solid-type baffles is carried out in the present paper using the Commercial, Computational Fluid Dynamics, software FLUENT. The flow model is governed by the Reynolds averaged Navier-Stokes (RANS) equations with the SST k-ω turbulence model and the energy equation. The finite volume method (FVM) with the SIMPLE-discretization algorithm is applied for the solution of the problem. The computations are carried out in the turbulent regime for different Reynolds numbers. In this study, thermo-aeraulic fields, dimensionless axial profiles of velocity, skin friction coefficients, local and average heat transfer coefficients, and thermal enhancement factor were investigated, at constant surface temperature condition along the heated upper wall of the channel, for all the geometry under investigation and chosen for various stations. The impact of the cascaded rectangular-triangular geometry of the baffle on the thermal and dynamic behavior of air is shown and this in comparing the data of this obstacle type with those of the simple flat rectangular-shaped baffle. This CFD analysis can be a real application in the field of heat exchangers, solar air collectors, and electronic equipments.

Studies on Aerodynamic Characteristics of Dump Diffusers for Modern Aircraft Engines

2012 ◽  
Vol 232 ◽  
pp. 246-251 ◽  
Author(s):  
P. Sathyan ◽  
S. Srikanth ◽  
I. Dheepan ◽  
M. Arun ◽  
C. Aswin ◽  
...  
Keyword(s):  
Stokes Equations ◽  
Numerical Study ◽  
Fluid Dynamic ◽  
Aerodynamic Characteristics ◽  
Navier Stokes ◽  
Finite Volume Scheme ◽  
Aircraft Engines ◽  
Navier Stokes Equations ◽  
Dynamic Constraints ◽  
Fully Implicit

The geometrical optimization of dump diffusers are extremely demanding as the flow fields and stress fields are very complex and must be well understood to achieve the required design efficiencies. In this paper parametric analytical studies have been carried out for examining the aerodynamics characteristics of different dump diffusers for modern aircraft engines. Numerical studies have been carried out using SST K- ω turbulence model. This code solves SST k- ω turbulence equations using the coupled second order implicit unsteady formulation. In the numerical study, a fully implicit finite volume scheme of the compressible, Reynolds-Averaged, Navier-Stokes equations is employed. We concluded that in addition to the dump gap ratio, the aerodynamic shape of the flame tube case and the other geometric variables are also need to be optimized judiciously after considering the fluid dynamic constraints for controlling the pressure recovery and the losses.

scholarly journals Preliminary Determination of Propeller Aerodynamic Characteristics for Small Aeroplanes

10.14311/558 ◽  
2004 ◽  
Vol 44 (2) ◽  
Author(s):  
S. Slavík
Keyword(s):  
Aerodynamic Characteristics ◽  
Propeller Blade ◽  
Analytical Functions ◽  
Advance Ratio ◽  
Propeller Blades ◽  
Lift And Drag ◽  
S Model ◽  
Integral Decomposition ◽  
Preliminary Determination

This paper deals with preliminary determination of propeller thrust and power coefficients depending on the advance ratio by means of some representative geometric parameters of the blade at a specific radius: propeller blade chord and blade angle setting at 70 % of the top radius, airfoil thickness at the radius near the tip and the position of the maximum blade width. A rough estimation of the non-linear influence of propeller blades number is included.The published method is based on Lock`s model of the characteristic section and the Bull-Bennett lift and drag propeller blade curves. Lock`s integral decomposition factors and the loss factor were modified by the evolution of the experimental propeller characteristics. The numerical-obtained factors were smoothed and expressed in the form of analytical functions depending on the geometric propeller blade parameters and the advance ratio.

scholarly journals Aerodynamic Performance Characterization and Structural Analysis of Slotted Propeller: Part A Effect of Position

2020 ◽  
Vol 12 (2) ◽  
pp. 183-198
Author(s):  
Aravind SEENI
Keyword(s):  
Pressure Distribution ◽  
Structural Integrity ◽  
Power Coefficient ◽  
Propeller Blade ◽  
Ansys Fluent ◽  
Thrust Coefficient ◽  
Baseline Design ◽  
Propeller Design ◽  
Advance Ratio ◽  
C 50

Novel slotted propeller design performance is presented in terms of thrust coefficient, power coefficient and efficiency by utilizing ANSYS Fluent. The effects of slotted positions were discussed with respect to baseline APC Slow Flyer 10’ x 7’ configurations. Seven slot locations with respect to chord length(c) namely 12.5%c, 25%c, 37.5%c, 50%c, 62.5%c, 75%c and 87.5%c were tested. The result shows that introduction of slot along the propeller blade increases the thrust coefficient, in the range of 0.1% to 4.74% for low advance ratios. However, increase in thrust coefficient also increases power coefficient compared to baseline design, hence reducing propeller efficiency. In addition, structural integrity of the blade was tested. The pressure distribution of the propeller blade demonstrated higher pressure on the back section, and lower pressure at the front section which results in thrust. In addition, the result shows that the pressure distribution is highly influenced by changes in advance ratio. The analysis shows that the novel propeller design managed to withstand stress and strain breaking point when operated at high advance ratio.

Compressible Flow Simulations Over Basic Reusable Rocket Configurations

2003 ◽  
Author(s):  
Keiichiro Fujimoto ◽  
Kozo Fujii
Keyword(s):  
Shock Wave ◽  
Mach Number ◽  
Compressible Flow ◽  
Simulation Method ◽  
Aerodynamic Characteristics ◽  
Pressure Level ◽  
The Body ◽  
Navier Stokes ◽  
Aerodynamic Coefficients ◽  
Flow Simulations

Compressible flow around the basic reusable rocket configurations are numerically simulated by Navier-Stokes computations. The study started with the simulations of Apollo configuration to validate the simulation method by the comparison of the aerodynamic data with NASA’s experiments, and the capability of CFD estimation are discussed. Computed aerodynamic coefficients for the Apollo agreed well with the experiments at subsonic to supersonic flow regime for whole angle of attack range. Then, the effects of the configuration parameters on the aerodynamic characteristics are numerically investigated and clarified in detail. It turns out that the aerodynamic characteristicsismainlyinfluenced by the separating position of the flow, shock wave on the surface and the pressure level behind the body. Large shoulder radius causes the strong Mach number dependency of the aerodynamic characteristics, and large fineness ratio strongly influences to the (CL)max.

Numerical Analysis of an External Flow-Field around a Formula SAE Car Body Based on FLUENT

2014 ◽  
Vol 1039 ◽  
pp. 17-24 ◽  
Author(s):  
Xiao Han Cheng ◽  
Shan Ming Luo ◽  
Xue Feng Chang ◽  
Dan Xie
Keyword(s):  
Flow Field ◽  
Drag Coefficient ◽  
Static Pressure ◽  
Fluid Dynamic ◽  
Aerodynamic Characteristics ◽  
External Flow ◽  
Attack Angle ◽  
The Body ◽  
Formula Sae ◽  
Rear Wing

This paper proposed a method to analysis an external flow-field around a Formula SAE car. Firstly, the body of Formula SAE car was designed conforming to the FSAE rules using CATIA. Then, the model of the external flow-field around the vehicle was established using computational fluid dynamic technology. A comparative analysis of the aerodynamic characteristics was made for the body between the conditions of being without the wing package and being with the wing package under different attack angle to get the static pressure graph, the lift force and the drag force then worked out the drag coefficient and confirmed which is the most suitable angle for the wings. The results showed that: the static pressure of the front body, the front part of the tires and the driver’s chest and head is the highest; the body has good streamline since its drag coefficient is 0.385; the rear wings can supply 65% downforce, when the attack angle of the rear wing is set to 8°. Finally, the real mold was fabricated according to the above 3D model and the analysis results. The method presented in this paper can provide theoretical basis and technical parameter for the aerodynamic formation designing and amelioration of the Formula SAE cars. Also it has guiding significance for the design and aerodynamic analysis of the Ordinary Passenger car.

Numerical Simulation of the Aerodynamic Behavior of Propeller Blades at Subsonic Conditions

2012 ◽  
Author(s):  
Mohamed B. Farghaly ◽  
Ahmed F. El-Sayed ◽  
Galal B. Salem
Keyword(s):  
Mach Number ◽  
Control Volume ◽  
Three Dimensional ◽  
Power Coefficient ◽  
Detailed Knowledge ◽  
Computational Domain ◽  
Thrust Coefficient ◽  
Oil Crisis ◽  
Propeller Blades ◽  
Control Volume Approach

The Organization of the Petroleum Exporting Countries (OPEC) oil crisis of the mid 1970s led to a revival in interest in the propeller as a possible fuel-efficient propulsion for aircraft operating at subsonic cruise speeds. A propeller aerodynamics is complex and should be analyzed carefully to ensure maximum propellers efficiency. Detailed knowledge of flow patterns and aerodynamics loads is necessary for blade material and manufacturing process. In this study, an isolated propeller blade is chosen as the base of analysis, the geometry of the propeller: twist and chord variation with radius, are taken from real case module. The boundary conditions of the computational domain are set corresponding to that exist in the propeller manuals. A three dimensional unstructured grid was generated and adopted using commercial grid generator GAMBIT software. The governing equations are solved using FLUENT6.3.26 a commercial CFD code, which uses a control volume approach on a grid over the computational domain. Results identified that the propeller efficiency, power coefficient are increases to reach maximum values and then decreases with increase Mach number. The thrust coefficient decreases with increase Mach number.

scholarly journals Time-Dependent Effects of Glaze Ice on the Aerodynamic Characteristics of an Airfoil

2018 ◽  
Vol 2018 ◽  
pp. 1-14 ◽  
Author(s):  
Narges Tabatabaei ◽  
Michel J. Cervantes ◽  
Chirag Trivedi
Keyword(s):  
Strouhal Number ◽  
Fluid Dynamic ◽  
Low Frequency ◽  
Leading Edge ◽  
Aerodynamic Characteristics ◽  
Time Dependent ◽  
Frequency Mode ◽  
Flat Plates ◽  
Computational Fluid Dynamic Analysis ◽  
Pressure Profiles

The main objective of this study is to estimate the dynamic loads acting over a glaze-iced airfoil. This work studies the performance of unsteady Reynolds-averaged Navier-Stokes (URANS) simulations in predicting the oscillations over an iced airfoil. The structure and size of time-averaged vortices are compared to measurements. Furthermore, the accuracy of a two-equation eddy viscosity turbulence model, the shear stress transport (SST) model, is investigated in the case of the dynamic load analysis over a glaze-iced airfoil. The computational fluid dynamic analysis was conducted to investigate the effect of critical ice accretions on a 0.610 m chord NACA 0011 airfoil. Leading edge glaze ice accretion was simulated with flat plates (spoiler-ice) extending along the span of the blade. Aerodynamic performance coefficients and pressure profiles were calculated and validated for the Reynolds number of 1.83 × 106. Furthermore, turbulent separation bubbles were studied. The numerical results confirm both time-dependent phenomena observed in previous similar measurements: (1) low-frequency mode, with a Strouhal number Sth≈0,013–0.02, and (2) higher frequency mode with a Strouhal number StL≈0,059–0.69. The higher frequency motion has the same characteristics as the shedding mode and the lower frequency motion has the flapping mode characteristics.

scholarly journals Aerodynamic Performance Characterization of Slotted Propeller: Part B Effect of Angle

2019 ◽  
Vol 11 (4) ◽  
pp. 155-170
Author(s):  
Aravind SEENI
Keyword(s):  
Rotational Speed ◽  
Aerodynamic Performance ◽  
Von Mises Stress ◽  
Power Coefficient ◽  
Small Scale ◽  
Propeller Blade ◽  
Static Structure ◽  
Thrust Coefficient ◽  
Advance Ratio ◽  
Von Mises

In this paper, designs of slotted propeller blade were discussed numerically, in terms of aerodynamic performance and static structural analysis. Baseline APC Slow Flyer 10’ x 7’ small scale propeller blade was modified by including slots along the propeller blade. Numerical analysis has been done to determine the influence of slots angle towards thrust coefficient, power coefficient and efficiency. Simulations were performed by using ANSYS Fluent implementing k-ω turbulence model and Multiple Reference Frame to incorporate rotational speed of the propeller. The analyses were conducted at a fixed rotational speed, with variance of advance ratio. Initial slotted design is set at 180 degree and the angles were changed with 10-degree interval, ranging from 180 degree to 90 degree. The results were compared with available experimental data. For the slotted design, the result shows that inducing slots do not always lead to improvement in propeller blade performance. Improvement in thrust coefficient with the range of 0.267% to 2.71% can be seen for low advance ratio for most of slot angles. However, a significant increase in power coefficient can be observed which reduces the overall efficiency of the propeller blade. For stress and deformation, ANSYS Mechanical Static Structure was used to determine maximum Von-Mises stress, maximum Von-Mises strain, and total deformation. The analyses were conducted by using 60% long strand fiber glass reinforced nylon 6 Natural. The blade is more suitable to operate at higher velocity. At lower operational velocity, the blade tends to experience material failure as the stress exceeds stress at break.

Analysis of rotor aerodynamic response during ramp collective pitch increase by CFD method

2020 ◽  
pp. 095441002096540
Author(s):  
Kai Zhang ◽  
Qijun Zhao ◽  
Xiayang Zhang ◽  
Guohua Xu
Keyword(s):  
Steady State ◽  
Stokes Equations ◽  
Aerodynamic Characteristics ◽  
Weno Scheme ◽  
Helicopter Rotor ◽  
Navier Stokes ◽  
Thrust Coefficient ◽  
Response Characteristics ◽  
Cfd Method ◽  
Delay Phenomenon

In order to study the aerodynamic response characteristics of the helicopter rotor during ramp collective pitch increase, the moving-embedded grid technique is employed for numerical simulation. The governing equations are modeled via Navier-Stokes equations, as well as one equation S-A turbulence model. In order to improve the precision of unsteady simulation of the rotor flowfield, the three-order scheme known as Roe-WENO scheme is employed for the spatial discretization of convective fluxes, and the implicit LU-SGS scheme is adopted for the temporal discretization. The flowfield and aerodynamic characteristics of the SA349/2 Gazelle helicopter rotor are computed for verification, and thereafter, the present method is used to simulate the transient aerodynamic response of the rotor under different collective pitch increment rates. The unsteady flowfield and aerodynamic characteristics of the rotor under ramp collective pitch increase are obtained and compared with the experimental data. The results show that the numerical method not only can accurately predict the unsteady aerodynamic loads of the rotor in steady state, but also is capable of effectively simulating the transient aerodynamic response of the rotor, characterized by overshoot and delay phenomenon, during ramp collective pitch increase. Finally, the opposite ramp decrease in collective pitch and the influence of pre-twist on aerodynamic response are analyzed. The result shows that the transient aerodynamic response of the rotor under ramp collective pitch increase and decrease present a certain of symmetry. The change in pre-twist of blades only affects the thrust coefficient in steady state, while have little influence on the transient maneuvering process of collective pitch.

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