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In the context of conceptual design there are low-fidelity lifting line models capable of predicting the maximum lift coefficient of trapezoidal twisted wings. However, more complex geometries like that of the blended-wing–body (BWB) require the introduction of additional geometrical hypotheses. This paper introduces a compound-wing lifting line model that predicts the maximum lift coefficient of geometries like the BWB. Such a model would decrease computation times at early design stages for the BWB. The proposed model is calibrated using Reynolds-Averaged Navier–Stokes (RANS) simulations of a regional BWB geometry near stall with three different twist distributions at low-speed conditions. Application of the calibrated compound wing model on the regional BWB geometry allows to quickly find an optimal twist distribution for this specific configuration: a semiconstant twist distribution on a fraction of the outer wing.
Oliverio E. Velazquez Salazar; François Morency; Julien Weiss. Predicting Maximum Lift Coefficient for Compound Wings Using Lifting Line Theory. Journal of Aircraft 2021, 58, 717 -732.
AMA StyleOliverio E. Velazquez Salazar, François Morency, Julien Weiss. Predicting Maximum Lift Coefficient for Compound Wings Using Lifting Line Theory. Journal of Aircraft. 2021; 58 (4):717-732.
Chicago/Turabian StyleOliverio E. Velazquez Salazar; François Morency; Julien Weiss. 2021. "Predicting Maximum Lift Coefficient for Compound Wings Using Lifting Line Theory." Journal of Aircraft 58, no. 4: 717-732.
Researchers have focused in the last five years on modelling the aircraft ground deicing process using CFD (computational fluid dynamics) in order to reduce its costs and pollution. As preliminary efforts, those studies did not model the ice melting nor the diffusion between deicing fluids and water resulting from the melting process. This paper proposes a CFD method to simulate this process filling these gaps. A particulate two-phase flow approach is used to model the spray impact on ice near the contaminated surface. Ice melting is modelled using an extended version of the enthalpy-porosity technique. The water resulting from the melting process is diffused into the deicing fluid forming a single-phase film. This paper presents a new model of the process. The model is verified and validated through three steps. (i) verification of the species transport. (ii) validation of the transient temperature field of a mixture. (iii) validation of the convective heat transfer of an impinging spray. The permeability coefficient of the enthalpy-porosity technique is then calibrated. The proposed model proved to be a suitable candidate for a parametric study of the aircraft ground deicing process. On the validation test cases, the precision of heat transfer prediction exceeds 88%. The model has the ability of predicting the deicing time and the deicing fluid quantities needed to decontaminate a surface.
Sami Ernez; François Morency. CFD Model for Aircraft Ground Deicing: Verification and Validation of an Extended Enthalpy-Porosity Technique in Particulate Two Phase Flows. Fluids 2021, 6, 210 .
AMA StyleSami Ernez, François Morency. CFD Model for Aircraft Ground Deicing: Verification and Validation of an Extended Enthalpy-Porosity Technique in Particulate Two Phase Flows. Fluids. 2021; 6 (6):210.
Chicago/Turabian StyleSami Ernez; François Morency. 2021. "CFD Model for Aircraft Ground Deicing: Verification and Validation of an Extended Enthalpy-Porosity Technique in Particulate Two Phase Flows." Fluids 6, no. 6: 210.
Successful icing/de-icing simulations for rotorcraft require a good prediction of the convective heat transfer on the blade’s surface. Rotorcraft icing is an unwanted phenomenon that is known to cause flight cancelations, loss of rotor performance and severe vibrations that may have disastrous and deadly consequences. Following a series of experiments carried out at the Anti-icing Materials International Laboratory (AMIL), this paper provides heat transfer measurements on heated rotor blades, under both the anti-icing and de-icing modes in terms of the Nusselt Number (Nu). The objective is to develop correlations for the Nu in the presence of (1) an ice layer on the blades (NuIce ) and (2) liquid water content (LWC) in the freestream with no ice (NuWet ). For the sake of comparison, the NuWet and the NuIce are compared to heat transfer values in dry runs (NuDry ). Measurements are reported on the nose of the blade-leading edge, for three rotor speeds (Ω) = 500, 900 and 1000 RPM; a pitch angle (θ) = 6°; and three different radial positions (r/R), r/R = 0.6, 0.75 and 0.95. The de-icing tests are performed twice, once for a glaze ice accretion and another time for rime ice. Results indicate that the NuDry and the NuWet directly increased with V∝ , r/R or Ω, mainly due to an increase in the Reynolds number (Re). Measurements indicate that the NuWet to NuDry ratio was always larger than 1 as a direct result of the water spray addition. NuIce behavior was different and was largely affected by the ice thickness (tice ) on the blade. However, the ice acted as insulation on the blade surface and the NuIce to NuDry ratio was always less than 1, thus minimizing the effect of convection. Four correlations are then proposed for the NuDry , the NuWet and the NuIce , with an average error between 3.61% and 12.41%. The NuDry correlation satisfies what is expected from heat transfer near the leading edge of an airfoil, where the NuDry correlates well with Re0.52 .
Abdallah Samad; Eric Villeneuve; Caroline Blackburn; François Morency; Christophe Volat. An Experimental Investigation of the Convective Heat Transfer on a Small Helicopter Rotor with Anti-Icing and De-Icing Test Setups. Aerospace 2021, 8, 96 .
AMA StyleAbdallah Samad, Eric Villeneuve, Caroline Blackburn, François Morency, Christophe Volat. An Experimental Investigation of the Convective Heat Transfer on a Small Helicopter Rotor with Anti-Icing and De-Icing Test Setups. Aerospace. 2021; 8 (4):96.
Chicago/Turabian StyleAbdallah Samad; Eric Villeneuve; Caroline Blackburn; François Morency; Christophe Volat. 2021. "An Experimental Investigation of the Convective Heat Transfer on a Small Helicopter Rotor with Anti-Icing and De-Icing Test Setups." Aerospace 8, no. 4: 96.
The effects of atmospheric icing can be anticipated by Computational Fluid Dynamics (CFD). Past studies show that the convective heat transfer influences the ice accretion and is itself a function of surface roughness. Uncertainty quantification (UQ) could help quantify the impact of surface roughness parameters on the reliability of ice accretion prediction. This paper aims to quantify ice accretion uncertainties and identify the key surface roughness correction parameters contributing the most to the uncertainties in a Reynolds-Averaged Navier-Stokes (RANS) formulation. Ice accretion simulations over a rough flat plate using two thermal correction models are used to construct a RANS database. Non-Intrusive Polynomial Chaos Expansion (NIPCE) metamodels are developed to predict the convective heat transfer and icing characteristics of the RANS database. The metamodels allow for the computation of the 95% confidence intervals of the output probability distribution (PDF) and of the sensitivity indexes of the roughness parameters according to their level of influence on the outputs. For one of the thermal correction models, the most influential parameter is the roughness height, whereas for the second model it is the surface correction coefficient. In addition, the uncertainty on the freestream temperature has a minor impact on the ice accretion sensitivity compared to the uncertainty on the roughness parameters.
Kevin Ignatowicz; François Morency; Héloïse Beaugendre. Sensitivity Study of Ice Accretion Simulation to Roughness Thermal Correction Model. Aerospace 2021, 8, 84 .
AMA StyleKevin Ignatowicz, François Morency, Héloïse Beaugendre. Sensitivity Study of Ice Accretion Simulation to Roughness Thermal Correction Model. Aerospace. 2021; 8 (3):84.
Chicago/Turabian StyleKevin Ignatowicz; François Morency; Héloïse Beaugendre. 2021. "Sensitivity Study of Ice Accretion Simulation to Roughness Thermal Correction Model." Aerospace 8, no. 3: 84.
In-flight icing affects helicopter performance, limits its operations, and reduces safety. The convective heat transfer is an important parameter in numerical icing simulations and state-of-the-art icing/de-icing codes utilize important computing resources when calculating it. The BEMT–RHT and UVLM–RHT offer low- and medium-fidelity approaches to estimate the rotor heat transfer (RHT). They are based on a coupling between Blade element momentum theory (BEMT) or unsteady vortex lattice method (UVLM), and a CFD-determined heat transfer correlation. The latter relates the Frossling number (Fr) to the Reynolds number (Re) and effective angle of attack (αEff ). In a series of experiments carried out at the Anti-icing Materials International Laboratory (AMIL), this paper serves as a proof of concept of the proposed correlations. The objective is to propose correlations for the experimentally measured rotor heat transfer data. Specifically, the Frx is correlated with the Re and αEff in a similar form as the proposed CFD-based correlations. A fixed-wing setup is first used as a preliminary step to verify the heat transfer measurements of the icing wind tunnel (IWT). Tests are conducted at α = 0°, for a range of 4.76 × 105 ≤ Re ≤ 1.36 × 106 and at 10 non-dimensional surface wrap locations − 0.62 ≤ (S/c) ≤ + 0.87. Later, a rotor setup is used to build the novel heat transfer correlation, tests are conducted at two pitch angles ((θ) = 0° and 6°) for a range of rotor speeds (500 RPM ≤ (Ω) ≤ 1500 RPM), three different radial positions ((r/R) = 0.6, 0.75 and 0.95), and 0 ≤ S/c ≤ + 0.58. Results indicate that the fixed-wing Frx at the stagnation point was in the range of literature experimental data, and within 8% of fully turbulent CFD simulations. The FrAvg also agrees with CFD predictions, with an average discrepancy of 1.4%. For the rotor, the Ω caused a similar increase of Frx for the tests at θ = 0° and those at θ = 6°. Moreover, the Frx behavior changed significantly with r/R, suggesting the αEff had a significant effect on the Frx . Finally, the rotor data are first correlated with Rem (at each S/c) for θ = 0° to establish the correlation parameters, and a term for the αEff is then added to also account for the tests at θ = 6°. The correlations fit the data with an error between 2.1% and 14%, thus justifying the use of a coupled approach for the BEMT–RHT and UVLM–RHT.
Abdallah Samad; Eric Villeneuve; François Morency; Christophe Volat. A Numerical and Experimental Investigation of the Convective Heat Transfer on a Small Helicopter Rotor Test Setup. Aerospace 2021, 8, 53 .
AMA StyleAbdallah Samad, Eric Villeneuve, François Morency, Christophe Volat. A Numerical and Experimental Investigation of the Convective Heat Transfer on a Small Helicopter Rotor Test Setup. Aerospace. 2021; 8 (2):53.
Chicago/Turabian StyleAbdallah Samad; Eric Villeneuve; François Morency; Christophe Volat. 2021. "A Numerical and Experimental Investigation of the Convective Heat Transfer on a Small Helicopter Rotor Test Setup." Aerospace 8, no. 2: 53.
Aircraft contrails contribute to climate change through global radiative forcing. As part of the general effort aimed at developing reliable decision-making tools, this paper demonstrates the feasibility of implementing a Lagrangian ice microphysical module in a commercial CFD code to characterize the early development of near-field contrails. While engine jets are highly parameterized in most existing models in a way that neglects the nozzle exit-related aspects, our model accounts for the geometric complexity of modern turbofan exhausts. The modeling strategy is based on three-dimensional URANS simulations of an aircraft nozzle exit involving a bypass and a core jet (Eulerian gas phase). Solid soot and ice particles (dispersed phase) are individually tracked using a Lagrangian approach. The implemented microphysical module accounts for the main process of water-vapor condensation on pre-activated soot particles known as heterogeneous condensation. The predictive capabilities of the proposed model are demonstrated through a comprehensive validation set based on the jet-flow dynamics and turbulence statistics in the case of compressible, turbulent coaxial jets. Simulations of contrail formation from a realistic nozzle-exit geometry of the CFM56-3 engine (short-cowl nozzle delivering a dual stream jet with a bypass rate of 5.3) were also carried out in typical cruise flight conditions ensuring contrail formation. The model provides reliable predictions in terms of the plume dilution and ice-particle properties as compared to available in-flight and numerical data. Such a model can then be used to characterize the impact of nozzle-exit parameters on the optical and microphysical properties of near-field contrails.
Sébastien Cantin; Mohamed Chouak; François Morency; François Garnier. Eulerian–Lagrangian CFD-microphysics modeling of a near-field contrail from a realistic turbofan. International Journal of Engine Research 2021, 1 .
AMA StyleSébastien Cantin, Mohamed Chouak, François Morency, François Garnier. Eulerian–Lagrangian CFD-microphysics modeling of a near-field contrail from a realistic turbofan. International Journal of Engine Research. 2021; ():1.
Chicago/Turabian StyleSébastien Cantin; Mohamed Chouak; François Morency; François Garnier. 2021. "Eulerian–Lagrangian CFD-microphysics modeling of a near-field contrail from a realistic turbofan." International Journal of Engine Research , no. : 1.
Calculating the unsteady convective heat transfer on helicopter blades is the first step in the prediction of ice accretion and the design of ice-protection systems. Simulations using Computational Fluid Dynamics (CFD) successfully model the complex aerodynamics of rotors as well as the heat transfer on blade surfaces, but for a conceptual design, faster calculation methods may be favorable. In the recent literature, classical methods such as the blade element momentum theory (BEMT) and the unsteady vortex lattice method (UVLM) were used to produce higher fidelity aerodynamic results by coupling them to viscous CFD databases. The novelty of this research originates from the introduction of an added layer of the coupling technique to predict rotor blade heat transfer using the BEMT and UVLM. The new approach implements the viscous coupling of the two methods from one hand and introduces a link to a new airfoil CFD-determined heat transfer correlation. This way, the convective heat transfer on ice-clean rotor blades is estimated while benefiting from the viscous extension of the BEMT and UVLM. The CFD heat transfer prediction is verified using existing correlations for a flat plate test case. Thrust predictions by the implemented UVLM and BEMT agree within 2% and 80% compared to experimental data. Tip vortex locations by the UVLM are predicted within 90% but fail in extreme ground effect. The end results present as an estimate of the heat transfer for a typical lightweight helicopter tail rotor for four test cases in hover, ground effect, axial, and forward flight.
Abdallah Samad; Gitsuzo. B. S. Tagawa; François Morency; Christophe Volat. Predicting Rotor Heat Transfer Using the Viscous Blade Element Momentum Theory and Unsteady Vortex Lattice Method. Aerospace 2020, 7, 90 .
AMA StyleAbdallah Samad, Gitsuzo. B. S. Tagawa, François Morency, Christophe Volat. Predicting Rotor Heat Transfer Using the Viscous Blade Element Momentum Theory and Unsteady Vortex Lattice Method. Aerospace. 2020; 7 (7):90.
Chicago/Turabian StyleAbdallah Samad; Gitsuzo. B. S. Tagawa; François Morency; Christophe Volat. 2020. "Predicting Rotor Heat Transfer Using the Viscous Blade Element Momentum Theory and Unsteady Vortex Lattice Method." Aerospace 7, no. 7: 90.
F. Morency; H. Beaugendre. Comparison of turbulent Prandtl number correction models for the Stanton evaluation over rough surfaces. International Journal of Computational Fluid Dynamics 2020, 34, 278 -298.
AMA StyleF. Morency, H. Beaugendre. Comparison of turbulent Prandtl number correction models for the Stanton evaluation over rough surfaces. International Journal of Computational Fluid Dynamics. 2020; 34 (4):278-298.
Chicago/Turabian StyleF. Morency; H. Beaugendre. 2020. "Comparison of turbulent Prandtl number correction models for the Stanton evaluation over rough surfaces." International Journal of Computational Fluid Dynamics 34, no. 4: 278-298.
Ice shedding represents a threat to aircraft safety because ice blocks can strike rear components or be ingested by engines. The accuracy of current numerical methods for predicting ice block paths in the design phase of an aircraft still needs improvement. For the verification and validation of new trajectory calculation methods, shed blocks can be modeled for simplification as sphere or six-degree-of-freedom (6-DOF) plates. The objective of this paper is to propose a mathematical model for the dynamic moments of the plates and use it to numerically simulate ice block paths. The results will be useful for verifying high-fidelity methods. Equations of motion in a Lagrangian frame are presented together with the correlations to be used for the aerodynamic coefficients of the ice blocks. The plate model involves the quaternions and a dynamic moment coefficient function of the angular velocity. After the model is validated with test cases obtained from the literature, the trajectories around the blended wing body are plotted. The sensitivity of the trajectories and footprints to the chosen dynamic moment model is highlighted.
Kevin Ignatowicz; François Morency; Pierre Lopez. Dynamic Moment Model for Numerical Simulation of a 6-DOF Plate Trajectory around an Aircraft. Journal of Aerospace Engineering 2019, 32, 04019069 .
AMA StyleKevin Ignatowicz, François Morency, Pierre Lopez. Dynamic Moment Model for Numerical Simulation of a 6-DOF Plate Trajectory around an Aircraft. Journal of Aerospace Engineering. 2019; 32 (5):04019069.
Chicago/Turabian StyleKevin Ignatowicz; François Morency; Pierre Lopez. 2019. "Dynamic Moment Model for Numerical Simulation of a 6-DOF Plate Trajectory around an Aircraft." Journal of Aerospace Engineering 32, no. 5: 04019069.
The present Paper investigates the heat transfer and momentum created by a hot turbulent propylene glycol jet impinging on a horizontal plate at below the freezing-point temperature. A model for the simulation of the initial formation of liquid film at the beginning of an aircraft ground deicing process is proposed. The volume of fluid model coupled with the film formulation is employed using computational fluid dynamics to capture the interface in multiphase flow (liquid propylene glycol/liquid water/air). The three-dimensional Reynolds averaged Navier–Stokes equations are numerically solved using a finite volume discretization under unsteady conditions. The ground deicing case consists of a 1 m3 box and a convergent divergent nozzle installed inside the box. Approximately 512,000 rectangular cells with 0.006 m of thickness are used to refine the mesh of the liquid film on the wall. Flow conditions set are 60°C for the propylene glycol inlet temperature and 0°C for the static ambient temperature. The computed impinged surface skin Nusselt number gives the most noticeable discrepancies at the stagnation point, where the analysis results in a lower skin Nusselt number compared to the experimental results. The magnitudes of heat transfer for the ground deicing case study are found to be in good agreement with experimental hot jet data obtained from the literature.
Saleh Yakhya; Sami Ernez; François Morency. Computational Fluid Dynamics Investigation of Transient Effects of Aircraft Ground Deicing Jets. Journal of Thermophysics and Heat Transfer 2019, 33, 117 -127.
AMA StyleSaleh Yakhya, Sami Ernez, François Morency. Computational Fluid Dynamics Investigation of Transient Effects of Aircraft Ground Deicing Jets. Journal of Thermophysics and Heat Transfer. 2019; 33 (1):117-127.
Chicago/Turabian StyleSaleh Yakhya; Sami Ernez; François Morency. 2019. "Computational Fluid Dynamics Investigation of Transient Effects of Aircraft Ground Deicing Jets." Journal of Thermophysics and Heat Transfer 33, no. 1: 117-127.
Immersed boundary methods (IBM) are alternative methods to simulate fluid flows around complex geometries. The grid generation is fast as it does not need to conform to the fluid-solid interface. However, special treatments are needed in the flow equations to properly take into account the wall proximity. The penalization method is a particular case of the IBM in which the wall boundary conditions are imposed via continuous forcing terms into the governing equations. Reynolds Averaged Navier–Stokes (RANS) equations completed with a turbulence model are still the most common way to model turbulence in engineering applications. However, RANS turbulence model implementation with penalization into a vortex formulation is not straight forward, in part because of the variable turbulent viscosity and partly because of the boundary conditions. This paper extends the penalization technique to turbulent flows. The objective of this paper is to validate the use of the Spalart–Allmaras turbulence model in the context of penalization and vortex formulation. Details of the resolution using a Vortex In Cell (VIC) numerical scheme are given. The proposed scheme is based on the advection of particles of vorticity and particles of turbulent viscosity. A Lagrangian framework is chosen to solve the advection part. The remaining parts of the system of equations are solved with an Eulerian framework using a Cartesian uniform grid. To avoid fine meshes near the wall, a wall function compatible with the penalization method and the vortex formulation is proposed. The formulation and the coding are validated against the well-known periodic channel flow. Velocity profiles are computed without and with the wall function. Results agree with analytic law of the wall solutions, showing that RANS simulations can be conducted with VIC schemes and penalization.
H. Beaugendre; F. Morency. Penalization of the Spalart–Allmaras turbulence model without and with a wall function: Methodology for a vortex in cell scheme. Computers & Fluids 2018, 170, 313 -323.
AMA StyleH. Beaugendre, F. Morency. Penalization of the Spalart–Allmaras turbulence model without and with a wall function: Methodology for a vortex in cell scheme. Computers & Fluids. 2018; 170 ():313-323.
Chicago/Turabian StyleH. Beaugendre; F. Morency. 2018. "Penalization of the Spalart–Allmaras turbulence model without and with a wall function: Methodology for a vortex in cell scheme." Computers & Fluids 170, no. : 313-323.
Abdallah Samad; Francois Morency; Christophe Volat. A Numerical Model of the Blade Element Momentum Method for Rotating Airfoils with Heat Transfer Calculation. 2018 Joint Thermophysics and Heat Transfer Conference 2018, 1 .
AMA StyleAbdallah Samad, Francois Morency, Christophe Volat. A Numerical Model of the Blade Element Momentum Method for Rotating Airfoils with Heat Transfer Calculation. 2018 Joint Thermophysics and Heat Transfer Conference. 2018; ():1.
Chicago/Turabian StyleAbdallah Samad; Francois Morency; Christophe Volat. 2018. "A Numerical Model of the Blade Element Momentum Method for Rotating Airfoils with Heat Transfer Calculation." 2018 Joint Thermophysics and Heat Transfer Conference , no. : 1.
Gitsuzo D. Tagawa; Francois Morency; Héloïse Beaugendre. CFD study of airfoil lift reduction caused by ice roughness. 2018 Applied Aerodynamics Conference 2018, 1 .
AMA StyleGitsuzo D. Tagawa, Francois Morency, Héloïse Beaugendre. CFD study of airfoil lift reduction caused by ice roughness. 2018 Applied Aerodynamics Conference. 2018; ():1.
Chicago/Turabian StyleGitsuzo D. Tagawa; Francois Morency; Héloïse Beaugendre. 2018. "CFD study of airfoil lift reduction caused by ice roughness." 2018 Applied Aerodynamics Conference , no. : 1.
Flying debris is generated in several situations: when a roof is exposed to a storm, when ice accretes on rotating wind turbines, or during inflight aircraft deicing. Four dimensionless parameters play a role in the motion of flying debris. The goal of the present paper is to investigate the relative importance of four dimensionless parameters: the Reynolds number, the Froude number, the Tachikawa number, and the mass moment of inertia parameters. Flying debris trajectories are computed with a fluid-solid interaction model formulated for an incompressible 2D laminar flow. The rigid moving solid effects are modelled in the Navier-Stokes equations using penalization. A VIC scheme is used to solve the flow equations. The aerodynamic forces and moments are used to compute the acceleration and the velocity of the solid. A database of 64 trajectories is built using a two-level full factorial design for the four factors. The dispersion of the plate position at a given horizontal position decreases with the Froude number. Moreover, the Tachikawa number has a significant effect on the median plate position.
Francois Morency; Héloïse Beaugendre. Parametric Studies of Flat Plate Trajectories Using VIC and Penalization. Modelling and Simulation in Engineering 2018, 2018, 1 -14.
AMA StyleFrancois Morency, Héloïse Beaugendre. Parametric Studies of Flat Plate Trajectories Using VIC and Penalization. Modelling and Simulation in Engineering. 2018; 2018 ():1-14.
Chicago/Turabian StyleFrancois Morency; Héloïse Beaugendre. 2018. "Parametric Studies of Flat Plate Trajectories Using VIC and Penalization." Modelling and Simulation in Engineering 2018, no. : 1-14.
Saleh Yakhya; François Morency. Numerical Study of Momentum and Heat Transfer in Propylene Glycol Jets used for Aircraft Ground Deicing. 23rd AIAA Computational Fluid Dynamics Conference 2017, 1 .
AMA StyleSaleh Yakhya, François Morency. Numerical Study of Momentum and Heat Transfer in Propylene Glycol Jets used for Aircraft Ground Deicing. 23rd AIAA Computational Fluid Dynamics Conference. 2017; ():1.
Chicago/Turabian StyleSaleh Yakhya; François Morency. 2017. "Numerical Study of Momentum and Heat Transfer in Propylene Glycol Jets used for Aircraft Ground Deicing." 23rd AIAA Computational Fluid Dynamics Conference , no. : 1.
Oliverio Velazquez; Julien Weiss; François Morency. Preliminary investigation on stall characteristics of a Regional BWB for low speed approach. 35th AIAA Applied Aerodynamics Conference 2017, 1 .
AMA StyleOliverio Velazquez, Julien Weiss, François Morency. Preliminary investigation on stall characteristics of a Regional BWB for low speed approach. 35th AIAA Applied Aerodynamics Conference. 2017; ():1.
Chicago/Turabian StyleOliverio Velazquez; Julien Weiss; François Morency. 2017. "Preliminary investigation on stall characteristics of a Regional BWB for low speed approach." 35th AIAA Applied Aerodynamics Conference , no. : 1.
Alvaro Toledano; Julien Weiss; François Morency; Cabot Broughton; Ali Benmeddour. Study of the Subsonic Wall Interference in Stall of the NASA CRM at the NRC 1.5 m Trisonic Wind Tunnel. 33rd AIAA Aerodynamic Measurement Technology and Ground Testing Conference 2017, 1 .
AMA StyleAlvaro Toledano, Julien Weiss, François Morency, Cabot Broughton, Ali Benmeddour. Study of the Subsonic Wall Interference in Stall of the NASA CRM at the NRC 1.5 m Trisonic Wind Tunnel. 33rd AIAA Aerodynamic Measurement Technology and Ground Testing Conference. 2017; ():1.
Chicago/Turabian StyleAlvaro Toledano; Julien Weiss; François Morency; Cabot Broughton; Ali Benmeddour. 2017. "Study of the Subsonic Wall Interference in Stall of the NASA CRM at the NRC 1.5 m Trisonic Wind Tunnel." 33rd AIAA Aerodynamic Measurement Technology and Ground Testing Conference , no. : 1.
Yaniel Torres; Sylvie Nadeau; François Morency. Study of fatigue and workload among aircraft de-icing technicians. Occupational Ergonomics 2016, 13, 79 -90.
AMA StyleYaniel Torres, Sylvie Nadeau, François Morency. Study of fatigue and workload among aircraft de-icing technicians. Occupational Ergonomics. 2016; 13 (2):79-90.
Chicago/Turabian StyleYaniel Torres; Sylvie Nadeau; François Morency. 2016. "Study of fatigue and workload among aircraft de-icing technicians." Occupational Ergonomics 13, no. 2: 79-90.
Luc Védie; François Morency; Nicolas Kubler. Sensitivity analysis of ice piece trajectory calculation. 8th AIAA Atmospheric and Space Environments Conference 2016, 1 .
AMA StyleLuc Védie, François Morency, Nicolas Kubler. Sensitivity analysis of ice piece trajectory calculation. 8th AIAA Atmospheric and Space Environments Conference. 2016; ():1.
Chicago/Turabian StyleLuc Védie; François Morency; Nicolas Kubler. 2016. "Sensitivity analysis of ice piece trajectory calculation." 8th AIAA Atmospheric and Space Environments Conference , no. : 1.
Quentin Schwaab; Julien Weiss; Christian Belleau; François Morency. Low-Cost Arduino-Based Data Acquisition System with Android Mobile Interface for Undergraduate Aerodynamics Laboratories. 32nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference 2016, 1 .
AMA StyleQuentin Schwaab, Julien Weiss, Christian Belleau, François Morency. Low-Cost Arduino-Based Data Acquisition System with Android Mobile Interface for Undergraduate Aerodynamics Laboratories. 32nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference. 2016; ():1.
Chicago/Turabian StyleQuentin Schwaab; Julien Weiss; Christian Belleau; François Morency. 2016. "Low-Cost Arduino-Based Data Acquisition System with Android Mobile Interface for Undergraduate Aerodynamics Laboratories." 32nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference , no. : 1.