An Overview of ONERA Research Activities Related to Drag Analysis and Breakdown

Bailly, Didier; Petropoulos, Ilias; Wervaecke, Christelle; Méheut, Michaël; Atinault, Olivier; Fournis, Camille

doi:10.2514/6.2021-2551

Cited by 5 publications

(3 citation statements)

References 50 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Particular modeling considerations of this type then lead to a phenomenological decomposition of drag. The formulations and methods relative to the far-field theory have been presented in former ONERA publications [3,23,24,25]. In the present study, all the far-field analyses are carried out with the drag extraction code FFDπ [26], coupled with the Cassiopee library of ONERA [16].…”

Section: Far-field Drag Analysismentioning

confidence: 99%

DPW-7: Steady and Unsteady Computations of the Common Research Model at Different Reynolds Numbers

Hue,

Sartor,

Petropoulos

et al. 2023

Journal of Aircraft

Self Cite

View full text Add to dashboard Cite

This article presents the numerical computations performed at ONERA for the Seventh AIAA Drag Prediction Workshop. By introducing Reynolds numbers up to 30 million closer to the flight conditions, greater lift levels beyond the design point, and time-accurate simulations, this new session has allowed the previous studies to be extended. The Common Research Model aircraft configuration has been considered in its academic wing-body version and calculated in this work with point-matched structured grids. The ONERA Cassiopee software as well as the elsA solver and the FFDπ far-field drag code have been used. The grid convergence study has shown larger pressure drag variations than what was obtained at the cruise lift coefficient, but increasing the Reynolds number seems to reduce this trend. Then, the angle-of-attack sweep study with the lift, drag, and moment polars has given the opportunity to assess different numerical settings such as the Spalart–Allmaras and [Formula: see text] shear stress transport turbulence models with the quadratic constitutive relation approach (QCR-2000) and to discuss the comparison between computational fluid dynamics results and wind-tunnel data. Concerning the Reynolds number increase, it has appeared that the main part of drag reduction comes from the friction ([Formula: see text]) and viscous pressure drag ([Formula: see text]) components. The prediction of pitching moment increments due to Reynolds number variations still needs to be significantly improved. Finally, for an angle of attack above 4.00 deg, by the use of unsteady Reynolds-averaged Navier–Stokes computations, an unsteady buffet phenomenon has been observed and analyzed.

show abstract

Section: Far-field Drag Analysismentioning

confidence: 99%

DPW-7: Steady and Unsteady Computations of the Common Research Model at Different Reynolds Numbers

Hue,

Sartor,

Petropoulos

et al. 2023

Journal of Aircraft

Self Cite

View full text Add to dashboard Cite

show abstract

“…A more physically intuitive breakdown of the drag sources is obtained via the farfield momentum integration of the flow-field pertubations along the outer boundary surfaces of a control volume surrounding the body. Various farfield method techniques have been developed in an attempt to decipher physical drag generation mechanisms and attribute drag contributions to physical flow mechanisms related to shear layers, vortical systems and shock waves (see detailed reviews in [2][3][4]). A major motivation behind the development of farfield methods lies in their potential to establish compatibility between numerical and experimental measurement techniques [5,6] for accurate aerodynamic force extraction from limited wake plane data [3,7,8].…”

mentioning

confidence: 99%

Energy-Based Aerodynamic Loss and Recovery Characteristics of Adiabatic and Heated Fuselages

Lamprakis

Sanders

Laskaridis

2023

Journal of Aircraft

View full text Add to dashboard Cite

An energy-based aerodynamic analysis of the mechanical loss generation and potential energy/exergy recovery mechanisms is carried out for adiabatic and heated 2D axisymmetric flows over fuselage-shaped axisymmetric bodies. A generality of these mechanisms is obtained from dimensional analysis by appropriately scaling the freestream Reynolds and Mach numbers, while varying a reference fuselage’s fineness ratio. Thermo-aerodynamic implications and synergies of boundary-layer heating on the loss distribution, energy, and heat exergy recovery potentials are further considered for varying wall temperature ratios. The result is a clear identification of partial dynamic similarity and heat transfer effects on flow mechanisms such as shear layers, separation bubbles, and shockwaves of axisymmetric flows, and subsequent implications on loss distribution and energy recovery characteristics relating to boundary-layer ingestion. The analysis indicates that dissipating heat from aircraft surfaces aids, circumstantially, to drag reduction of unpowered fuselage bodies and increases, relative to the adiabatic, the recoverable energy fraction available for the boundary-layer ingestion propulsor, by strategically manipulating the loss distribution, while removing excess heat from the aircraft’s subsystem (batteries, fuel cells). Finally, an approach to assess the feasibility of exergetic heat recuperation as a possible means of useful work extraction and improved aerodynamic performance is explicitly introduced and discussed in the paper.

show abstract

“…To analyze the performance of new-generation configurations where the separation between thrust and drag is not as obvious as for a tube-and-wing architecture, the need for new theoretical and numerical models has emerged. Indeed, classical force-based models evaluating the different drag components [3][4][5] are less adapted to evaluate the performance of such new concepts.…”

mentioning

confidence: 99%

Exergy Balance Extension to Rotating Reference Frames: Application to a Propeller Configuration

2023

View full text Add to dashboard Cite

The exergy analysis has already proved to be of interest for aerospace applications, with the possibility to analyze new types of configurations. It is of particular interest when a pertinent thrust/drag breakdown is not possible and when significant thermal exchanges take place in the control volume. In addition, this method allows to link the different contributions of the exergy terms to physical phenomena in the flow, improving the understanding of the sources of losses degrading the performance of the system under study. The applications and results obtained in a fixed frame of reference have thus motivated the improvement and extension of the exergy balance to more complex flows. This paper aims at presenting an extension of the exergy balance to rotating frames of reference for the analysis of rotating components of the propulsion system (e.g. propeller, turbomachine or helicopter rotor blades). The newly developed theoretical development is summarized, and an application to a numerical simulation of a propeller is presented. Results are discussed in terms of both physical interpretation and numerical accuracy.

show abstract

An Overview of ONERA Research Activities Related to Drag Analysis and Breakdown

Cited by 5 publications

References 50 publications

DPW-7: Steady and Unsteady Computations of the Common Research Model at Different Reynolds Numbers

DPW-7: Steady and Unsteady Computations of the Common Research Model at Different Reynolds Numbers

Energy-Based Aerodynamic Loss and Recovery Characteristics of Adiabatic and Heated Fuselages

Exergy Balance Extension to Rotating Reference Frames: Application to a Propeller Configuration

Contact Info

Product

Resources

About