The simulation of ice accretion on a wing or other surface is often required for aerodynamic evaluation, particularly at small scale low Reynolds number. Although there are commonly accepted practices simulation, no established and validated guidelines. purpose this paper to report the results an experimental study establishing high-fidelity, full-scale, iced-airfoil performance database. This research was conducted as part larger program with goal developing subscale methods iced airfoils....

NASA, FAA, ONERA, the University of Illinois and Boeing have embarked on a significant, collaborative research effort to address technical challenges associated with icing large-scale, three-dimensional swept wings. The overall goal is improve fidelity experimental computational simulation methods for swept-wing ice accretion formation resulting aerodynamic effect. A seven-phase has been designed that incorporates ice-accretion experiments simulations. As baseline, full-scale,...

This article presents some application of the morphing technology for aerodynamic performance improvement turboprop regional aircraft. It summarizes results obtained in framework Clean Sky 2 AIRGREEN2 program development and dedicated devices take-off landing, their uses off design conditions. The wing reference aircraft configuration considers Natural Laminar Flow (NLF) characteristics. A deformable leading edge device ("droop nose") a multi-functional segmented flap system have been...

In the present work, aerodynamic shape design of an advanced high-lift system for a natural laminar flow (NLF) wing, based on combination morphing droop nose and single slot trailing edge flap, is presented. The paper presents both optimization NLF wing configuration considering mutual effects flap devices. Concerning (DN), after defining parameterization techniques adopted to describe geometry in terms settings, external obtained by procedure able meet geometrical constraints skin...

The evolution of maximum lift coefficient a transport aircraft as function Reynolds number can be linked to modifications the laminar-turbulent transition process. In framework European project EUROLIFT (I), task was dedicated physical understanding and numerical modeling process in high-lift configurations. Then, follow-on II, major step is integration prediction tools within Reynolds-averaged Navier-Stokes (RANS) solvers order estimate impact on performance. This paper presents an overview...

The application of riblets on a typical regional turboprop configuration is discussed in this paper. effect the modeled as singular roughness problem by proper boundary condition at wall. model, already proposed previous paper, briefly described. drag prediction capabilities are verified showing some airfoil flow applications. Then wing–body aircraft considered. has been designed to have extended natural laminar cruise conditions. Riblets applied specifications representative combination...

This paper presents the results of an experimental and computational study low-Reynolds number swept wing aerodynamics. work has been conducted in preparation for icing effects on a wing. A complete abstract will be written final paper.

The design activity within the European 6th framework project EUROLIFT II is targeted towards an improvement of take-off performance a generic transport aircraft configuration by redesign trailing edge flap. involved partners applied different optimization strategies as well types flow solvers in order to cover wide range possible approaches for aerodynamic optimization. results obtained have been cross-calculated eliminate solver dependencies and identify best design. final selected has...

With the objective to integrate transition prediction within RANS codes with a minimal user interaction, cooperative actions are under way in frame of European EUROLIFT 2 Project, especially involved improvement knowledge flow developed around modeling high lift configurations. Transition criteria and simplified stability analysis considered for insertion or automatic coupling 3D codes, possibly involving 2.5D boundary layer code. Recent developments from INTA ONERA presented, comparisons...

Performance of transport aircraft in high-lift conditions is directly related to the maximum lift. However, most tests are carried out at subscale conditions, and performance then derived by extrapolation flight Reynolds number. So-called adverse number effects (sudden decrease lift with increasing number) often occur when extrapolations from wind-tunnel flight-tests results compared. Most these due changes transition process. Improvement knowledge process for three-dimensional...

The evolution of maximum lift coefficient a transport aircraft as function Reynolds number can be linked to modifications the laminar-turbulent transition process. In framework European project EUROLIFT (I), task was dedicated physical understanding and numerical modeling process in high-lift configurations. Then, follow-on II, major step is integration prediction tools within Reynolds-averaged Navier-Stokes (RANS) solvers order estimate impact on performance. This paper presents an overview...

The simulation of ice accretion on a wing or other surface is often required for aerodynamic evaluation, particularly at small scale low-Reynolds number. While there are commonly accepted practices simulation, no established and validated guidelines. purpose this article to report the results an experimental study establishing high-fidelity, full-scale, iced-airfoil performance database. This research was conducted as part larger program with goal developing subscale methods iced airfoils....

The design of high-lift systems represents a challenging task within the aerospace community, being multidisciplinary, multi-objective, and multipoint problem. Design, Simulation Flight Reynolds Number Testing for Advanced High-Lift Solution project, funded by European Commission under Seventh Framework Programme, aimed at improving aerodynamics developing, in coordinated approach, both efficient numerical strategies measurement techniques cryogenic conditions. Within different partners used...

Laminar-turbulent transition appears in high-lift configurations through instabilities, attachment-line contamination, or separation. Its prediction may improve the estimation of maximum lift and allows extrapolation from wind-tunnel measurements to flight conditions. This is being inserted within Reynolds-averaged Navier-Stokes codes become part standard design procedures. requires fast reliable transition-prediction tools, a very difficult issue itself. paper presents recent ONERA progress...

The design activity within the European 6th framework project EUROLIFT II is targeted towards an improvement of take-off performance a generic transport aircraft configuration by redesign trailing edge flap. involved partners applied different optimization strategies as well types flow solvers in order to cover wide range possible approaches for aerodynamic optimization. results obtained have been cross-calculated eliminate solver dependencies and identify best design. final selected has...

Purpose – Today, the design process of high‐lift configurations in industry mainly relies on experts' knowledge, and lacks a simple exploration space. Therefore, introduction high‐fidelity tools an optimization chain is now envisaged. The purpose this paper to define solve realistic problem by use constrained evolutionary algorithm, coupled Navier‐Stokes (RANS) solver. complete (shape settings) 3‐element configuration has been carried out for landing take‐off using sequential approach.

A multidisciplinary design analysis and optimization process is developed at ONERA for the of tube wing blended wing–body aircraft configurations. This composed different disciplinary modules (geometry, propulsion, aerodynamics, structure, handling qualities flight mission), overall considers fidelity levels these each step process. article describes low-fidelity aerodynamic module used during preliminary Analytical formulations retained lift drag components are presented in first part....

This paper presents the analysis of aeroacoustic experiments performed with an Airbus 1/11 scaled aircraft model in open anechoic wind tunnel CEPRA 19. study aimed at checking aerodynamic condition on wing and characterizing airframe noise sources. The results have shown that flight conditions can be well reproduced by adjusting slightly pitch angle for each configuration. main sources been localized using a 2D cross-shaped array microphones. Near-field/farfield correlations order to...

Modern transport aircraft wings have reached near-peak levels of energy-efficiency and there is still margin for further relevant improvements. A promising strategy improving efficiency to change the shape wing in flight order maximize its aerodynamic performance under all operative conditions. In present work, this has been developed framework Clean Sky 2 (REG-IADP) European research project, where authors focused on design a multifunctional twistable trailing-edge Natural Laminar Flow...

The improvement of slatless high-lift configurations is high importance for future aircraft. This statement valid turbulent wing as well integrating laminar flow technologies. Such performance can be obtained by using active control at the main leading edge, or use passive devices (vortex generators) (blowing slot) located on flap, in order to suppress separation that generally exists flap trailing edge lift-optimized landing configurations. paper presents numerical optimization a system...

des établissements d'enseignement et de recherche français ou étrangers, laboratoires publics privés.