Semi-Empirical Prediction of Airfoil Hysteresis

Traub, Lance W.

doi:10.3390/aerospace3020009

Cited by 11 publications

(4 citation statements)

References 14 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Figure 28 also shows that the area enclosed by the hysteresis loop of the wing with NACA 4415 section is larger than the wing with NACA 0012 section at every α which ascertains more loss of aerodynamic efficiency in the post-stall region which is also shown by Traub. 33…”

Section: Resultsmentioning

confidence: 99%

“…Figure 28 also shows that the area enclosed by the hysteresis loop of the wing with NACA4415 section is larger than the wing with NACA0012 section at every a which ascertains more loss of aerodynamic efficiency in the post-stall region which is also shown by Traub. 33 It is common to observe hysteresis of C L with the angle of attack, a; in this work, however, experimentally, the authors are looking at hysteresis of the lift force with Re at a particular angle of attack. That is, we allow the flow to become stable at that angle of attack.…”

Section: Hysteresis At Post-stall Regimementioning

confidence: 99%

See 1 more Smart Citation

Experimental validation of numerical decambering approach for flow past a rectangular wing

Roy

Kumar

Mukherjee

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

Experimental investigation on two rectangular wings with NACA0012 and NACA4415 profiles is performed at different Reynolds numbers to understand their aerodynamic behaviours at a high α regime. In-house developed numerical code VLM3D is validated using this experimental result in predicting the aerodynamic characteristics of a rectangular wing with cambered and symmetrical wing profile. The sectional coefficient of lift ([Formula: see text]) obtained from the numerical approach is used to study the variation in spanwise lift distribution. The lift and moment characteristics obtained from wind tunnel experiments are plotted, and change in the maximum coefficient of lift ([Formula: see text]) and stall angle ( α stall) are studied for both of the wing sections. A significant addition to the novelty of the present experiments is to provide some comparison of the numerical induced drag coefficient, [Formula: see text] with experimentally fitted model coefficients using least square technique. A novel method is used to examine the aerodynamic hysteresis at high angles of attack. The area included in the lift- Re curve loop is a measure of aerodynamic efficiency, and its variation with angle of attack and wing plan forms is studied.

show abstract

Section: Resultsmentioning

confidence: 99%

Section: Hysteresis At Post-stall Regimementioning

confidence: 99%

Experimental validation of numerical decambering approach for flow past a rectangular wing

Roy

Kumar

Mukherjee

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…One of the main factors characterizing the aerodynamic performance of wings is the lift coefficient, C L , and its slope versus the angle of attack, C Lα . This latter parameter has been studied in the literature for different wing shapes due to its connection to flight requirements and their influence on induced drag computation [17][18][19]. A recent study has provided correlations of the C Lα of a straight flat plate for any aspect ratio (between 1 and 8) and Reynolds number (ranging from 40 to 200×10 3 ) [20].…”

Section: Introductionmentioning

confidence: 99%

Influence of passive deformation in the lift coefficient of a NACA0012 wing model

Duran,

Lorite-Díez,

Konovalov-Shishov

et al. 2024

European Journal of Mechanics - B/Fluids

View full text Add to dashboard Cite

“…The flow around a wing can have a transonic behaviour which, at high angles of attack, may be supplemented by flow separation, strong crossflow gradients as well as a hysteresis in the lift slope [1,2]. Traub [3] highlighted further that at low Reynolds number flows, laminar separation bubbles exist which have an inherently unsteady behaviour. These separation bubbles may reattach to the wing or transition into a fully turbulent flow, depending on the pressure gradient.…”

Section: Introductionmentioning

confidence: 99%

Predicting Non-Linear Flow Phenomena through Different Characteristics-Based Schemes

2018

View full text Add to dashboard Cite

The present work investigates the bifurcation properties of the Navier-Stokes equations using characteristics-based schemes and Riemann solvers to test their suitability to predict non-linear flow phenomena encountered in aerospace applications. We make use of a single-and multi-directional characteristics-based scheme and Rusanov's Riemann solver to treat the convective term through a Godunov-type method. We use the Artificial Compressibility (AC) method and a unified Fractional-Step, Artificial Compressibility with Pressure-Projection (FSAC-PP) method for all considered schemes in a channel with a sudden expansion which provides highly non-linear flow features at low Reynolds numbers that produces a non-symmetrical flow field. Using the AC method, our results show that the multi-directional characteristics-based scheme is capable of predicting these phenomena while the single-directional counterpart does not predict the correct flow field. Both schemes and also Riemann solver approaches produce accurate results when the FSAC-PP method is used, showing that the incompressible method plays a dominant role in determining the behaviour of the flow. This also means that it is not just the numerical interpolation scheme which is responsible for the overall accuracy. Furthermore, we show that the FSAC-PP method provides faster convergence and higher level of accuracy, making it a prime candidate for aerospace applications.

show abstract

Semi-Empirical Prediction of Airfoil Hysteresis

Cited by 11 publications

References 14 publications

Experimental validation of numerical decambering approach for flow past a rectangular wing

Experimental validation of numerical decambering approach for flow past a rectangular wing

Influence of passive deformation in the lift coefficient of a NACA0012 wing model

Predicting Non-Linear Flow Phenomena through Different Characteristics-Based Schemes

Contact Info

Product

Resources

About