Powered Model Wind Tunnel Tests of a High-Offset Subsonic Turboprop Air Intake

Ruiz-Calavera, Luis P.; Funes-Sebastian, David E.; Perdones-Diaz, David

doi:10.2514/6.2010-6502

Cited by 10 publications

(6 citation statements)

References 1 publication

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“…However, later, it was adapted to simulate single and arrays of horizontal axis wind and tidal turbines. Publications on aircrafts cover the impacts of rotating blades using VBM in different types of aircrafts, including helicopters ( [20][21][22][23][24][25][26][27][28][29][30]), unmanned aerial vehicles ( [31][32][33]), quad-copters ( [34]), turboprops ( [35]), and tilt-rotors ( [36]). Of these, the helicopter is the most analyzed vehicle (about 60% of all).…”

Section: Studies Using Vbmmentioning

confidence: 99%

Developing an Extended Virtual Blade Model for Efficient Numerical Modeling of Wind and Tidal Farms

Radfar¹,

Kinaoush²

2022

Preprint

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The Virtual Blade Model (VBM) is the implementation of the Blade element model (BEM). This was done by coupling the Blade Element Momentum theory equations to simulate rotor operation with the Reynolds Averaged Navier-Stokes (RANS) equation to simulate rotor wake and the turbulent flow field around it. Exclusion of actual geometry of blades causes lower computational cost (about 10 to 100 times). Also, due to simplifications in the meshing procedure, VBM is easier to set up than the models that consider the actual geometry of blades. One of the main unaddressed limitations of the VBM code was the constraint of modeling up to ten rotor zones within one computational domain. This paper provides a detailed and well-documented general methodology to develop a virtual blade model for simulation of ten-plus turbines within one computational domain to remove the limitation of this widely used and robust code. It is strongly believed that the technical contribution of this paper, combined with the current sky-rocketing advancement of available computational resources and hardware, would open the gates to simulate various engineering problems in the field of aerospace, clean energy, and many more.

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Section: Studies Using Vbmmentioning

confidence: 99%

Developing an Extended Virtual Blade Model for Efficient Numerical Modeling of Wind and Tidal Farms

Radfar¹,

Kinaoush²

2022

Preprint

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“…On the other hand, the two-equation turbulence model k − ω shear stress transport was used for the uninstalled, isolated turboprop S-ducts in the previous analysis phase (16) . The choice of a two-equation turbulence model is common practice for most of the investigations on S-ducts found in the literature (17,18) , but Reynolds stress transport models are also advocated with strong arguments (19) . However, Colin et al (20) reported that computations on intakes with the Spalart-Allmaras model were capturing the flow separation similar to the two-equation models at high mass flow rates.…”

Section: Fluid Model Actuator Disc Set-up and Gridmentioning

confidence: 99%

Aerodynamic investigation of S-duct intake for high power turboprop installed on a channel wing

2017

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Installation effects on the S-duct intakes of a high power turboprop were investigated by comparing three different nacelle configurations as the channel wing, over-the-wing and conventional tractor wing using computational fluid dynamic methods. The interaction of the propeller, the wing, and the nacelle on the scoop type turboprop intakes were identified in terms of recovery and distortion on the aerodynamic interface planes. An actuator disc model was used to simulate the propeller downstream effects. The channel wing installation of S-ducts showed approximately 2% higher total pressure recovery than the other configurations. The channel wing configuration with a wrap-around S-duct experienced a 2% lower circumferential distortion intensity, whereas over-the-wing had an increase by 3% in comparison to the tractor wing. It was also observed that the S-duct type had a greater influence on the radial distortion intensity than the installation type. The swirl coefficient distribution showed that multiple peaks occurred as opposed to swirl results based on a single sector of the aerodynamic interface plane. The difference between swirl peaks of shaft penetration S-duct was reduced by 14% when installed on channel wing, whereas the peaks of wrap-around experienced 90° phase shift, and their difference showed 10% increase on channel wing.

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“…Therefore, some research on the coupling aerodynamic effects of traditional propellers and aircraft components was collected as a reference for this study. Ruiz Calavera[15] studied the aerodynamic performance of the propeller and inlet port based on the military transport aircraft A-400M. The simulation results obtained by momentum source method and sliding mesh unsteady method were compared with the experimental results, and the results showed that the simulation results obtained by the sliding grid unsteady method were more similar to the experimental results.…”

mentioning

confidence: 94%

Research on aerodynamic influence of contra-rotating propfan slipstream on propfan engine nacelle inlet

Zhao,

Zhou,

Deng

et al. 2024

J. Phys.: Conf. Ser.

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In order to investigate the aerodynamic influence of contra-rotating propfan (CRP) slipstream on propfan engine nacelle, numerical simulation research on the CRP/Nacelle integrated configuration was carried out by using sliding mesh unsteady method. The aerodynamic performance of integrated configuration under different working conditions was studied, and compared with nacelle without CRP. Results show that the total pressure recovery coefficient of inlet port increases due to the work done by CRP. However, as the inhale of the wake vortex, the flow structure inside the inlet becomes more complex because of the mixing of wake vortex and wall separation vortex, which leads to a significant increase of distortion index and loss coefficient. Compared with isolated nacelle, the slipstream causes the total pressure recovery coefficient of inlet port increased by 10.2% and 13.4% under cruise condition and takeoff condition, which is accompanied by the intensification of flow loss and non-uniformity inside the inlet, resulting in a significant increase of the total pressure loss coefficient and total pressure distortion index.

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Powered Model Wind Tunnel Tests of a High-Offset Subsonic Turboprop Air Intake

Cited by 10 publications

References 1 publication

Developing an Extended Virtual Blade Model for Efficient Numerical Modeling of Wind and Tidal Farms

Developing an Extended Virtual Blade Model for Efficient Numerical Modeling of Wind and Tidal Farms

Aerodynamic investigation of S-duct intake for high power turboprop installed on a channel wing

Research on aerodynamic influence of contra-rotating propfan slipstream on propfan engine nacelle inlet

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