Wave drag extraction from profile drag based on a wake-integral method

Kusunose, Kazuhiro; Crowder, J. P.; Watzlavick, Robert

doi:10.2514/6.1999-275

Cited by 17 publications

(10 citation statements)

References 7 publications

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“…In 1972, the work of Maskell [14] defined a complete drag formulation, in particular for the induced drag. During the 1990s, Brune [15] and Kusunose et al [16][17][18] generalized the far-field approach for the compressible flows. In particular, Kusunose et al [17] proposed an original breakdown of the profile drag to obtain the wave drag.…”

Section: Drag Extraction From Wake Surveymentioning

confidence: 99%

Experimental and Numerical Methods for Transition and Drag Predictions of Laminar Airfoils

et al. 2015

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The friction component is responsible for more than 40% of typical civil aircraft drag. As a consequence, the issue of laminar flow has been of prime importance in aeronautics for many years now. This article is focused on TollmienSchlichting-induced transition and drag predictions of two-dimensional laminar airfoils obtained with experimental and numerical methods. In 2012, a test campaign in the ONERA-S2MA wind tunnel, including infrared acquisitions, pressure sensors, and wake analyses, allowed substantial data to be obtained on such airfoils in transonic conditions. To complete this study, two-dimensional fluid dynamics computations have been performed, either with a Reynoldsaveraged Navier-Stokes solver using transition criteria or with a boundary-layer code combined with direct stability analysis. Furthermore, experimental (wake survey) and numerical (far-field theory) techniques allowing airfoil drag breakdown have been employed. Wind-tunnel and computational fluid dynamics transition predictions have been compared. Good agreement has been observed but the transition criteria may show some limitations in particular situations, such as long separation bubble development. The gains in lift and drag due to laminar flow have been quantified (natural vs triggered transition). Concerning drag reduction, the importance of the viscous pressure component has been highlighted. Finally, the effects of parameters such as angle of attack, Mach number, and Reynolds number on transition location and drag have been investigated.subscript for local state value f = frequency of boundary-layer instability M = freestream Mach number N T = value of factor N at transition onset P i = stagnation pressure Re = freestream Reynolds number based on the airfoil chord T i = stagnation temperature Tu = turbulence level U, V, W = x, y, z velocity components x, y, z = x, y, z coordinates Y = normalized first cell height Λ 2 = mean Pohlhausen parameter ρ = density Subscript 0 = freestream state value

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Section: Drag Extraction From Wake Surveymentioning

confidence: 99%

Experimental and Numerical Methods for Transition and Drag Predictions of Laminar Airfoils

et al. 2015

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“…It can be seen that the same physical phenomena is captured by both methods. Moreover, for transonic cases the farfield method performs a drag breakdown of the profile drag into the wave and viscous drag by using the Kusunose technique [16,20], but this is not as complete as the exergetic-based drag breakdown.…”

Section: Fig 39 Profile Drag Density and Exergy-based Drag Density Dmentioning

confidence: 99%

2D Flow Field Analysis by the Exergetic Method

Aguirre

Duplaa

Carbonneau

2019

AIAA Aviation 2019 Forum

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“…The profile drag breakdown proposed by Kusunose [18] uses a physic-based approach to extract the wave drag from the measured profile drag at the survey plane. An example of the profile drag density distribution is shown in the In order to extract this wave component, a physical analysis is done.…”

Section: A Kusunose Methodsmentioning

confidence: 99%

“…The far-field method allows performing a profile drag breakdown by using the Kusunose approach [18]. It decomposes the profile drag in the transonic range into its pure viscous, pure wave and wave-boundary layer interaction components as shown in the Fig.…”

Section: Fig 9 Near-field Drag Breakdownmentioning

confidence: 99%

Exergetic Drag Characteristic Curves

Aguirre

Duplaa

2019

AIAA Journal

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This paper aims to perform a drag breakdown of an airfoil and a wing by using the exergetic method. Moreover, a new far-field wave anergy extraction method is presented. The resulting exergetic drag curves are proposed as additional characteristic curves for external aerodynamic assessment of airfoils or any other bodies. CFD analyses of a NACA 0012 airfoil and a rectangular wing at subsonic and transonic conditions were used as test cases to present the concept. This new approach allows to deeply understand the aerodynamic behavior of a body and provides an alternative point of view to the classical near-field and far-field based drag curves.

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Wave drag extraction from profile drag based on a wake-integral method

Cited by 17 publications

References 7 publications

Experimental and Numerical Methods for Transition and Drag Predictions of Laminar Airfoils

Experimental and Numerical Methods for Transition and Drag Predictions of Laminar Airfoils

2D Flow Field Analysis by the Exergetic Method

Exergetic Drag Characteristic Curves

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