A singular perturbation analysis of two-dimensional wind tunnel interferences

Summary Wall interference on an airfoil model in a wind tunnel has been treated as a singular perturbation problem for both subsonic and transonic flows. This problem is formulated within the framework of small perturbation theory. It is shown that the classical interference solution consists of the outer boundary condition for the inner boundary value problem.

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Résumé Dans une étude de l'effet des écoulements subsonique et transsonique dans une soufflerie, on a traité l'interférence de la paroi de la soufflerie sur une maquette de profil aérodynamique comme une perturbation singulière dont la définition est donnée dans la théorie des petites perturbations. Il a été démontré que la solution classique au problème de l'interférence fait intervenir la condition aux limites extérieures du problème de la valeur aux limites intérieures.

     

Theoretical aspects of the calibration of transonic test sections

Zusammenfassung Es werden einige theoretische Betrachtungen zum Problem der Kalibrierung einer Windkanalme?strecke im Schallgeschwindigkeitsbereich angestellt. Zun?chst wird angenommen, die Ausbildung der W?nde der Me?strecke sollte so vorgenommen werden, dass das gr?sstm?gliche Modell bei Schallgeschwindigkeit darin untergebracht werden kann. Durch Anwendung des ?hnlichkeitsgesetzes für schallnahe Str?mung und der Fl?chenregel auf die Str?mung im Messquerschnitt scheint eine betr?chtliche Verminderung des Arbeitsaufwandes, die eine solche Kalibrierung der Me?strecke für schlanke Modelle erfordern würde, m?glich zu sein. Dies ist besonders zutreffend für Messquerschnitte mit L?ngsschlitzen konstanter Breite, wo die für den Wandeinfluss gleich Null bei Schallgeschwindigkeit erforderliche Anordnung der Schlitze sich auch brauchbar erweist für eine grosse Gruppe von Modellen verschiedener Gr?sse und Form (vorausgesetzt, dass der Einfluss der Wandgrenzschicht vernachl?ssigt werden kann). Die Ableitung ergibt, dass das Verh?ltnis des Modellquerschnittes zum Messquerschnitt kein brauchbares Mass für die Gr?sse des Wandeinflusses darstellt. Vielmehr scheint das gr?sste zul?ssige Fl?chenverh?ltnis, das zu einer vorgegebenen relativen Gr?sse des Wandeinflusses geh?rt, stark vom Dickenverh?ltnis des Modelles abh?ngig zu sein, so dass ein schlankeres Modell auch kürzer sein müsste. Die asymptotische Grundl?sung der Potentialgleichung für achsensymmetrische Schallstr?mung nachGuderley undYoshihara wurde zur Absch?tzung der genauen Spaltbreite für sehr kleine Modelle verwendet, und es ergibt sich, dass in diesem Falle die genaue Einstellung der Spaltbreite nicht besonders kritisch ist. Der Haupteffekt einer Ver?nderung der Spaltbreite besteht in einer ?nderung der Mach-Zahl-Korrektur stromaufw?rts vor der Me?strecke.      

On Transonic Marginal Separation

Laminar boundary‐layer separation near the leading edge of a thin airfoil is one of the principal factors that limits the lift force acting on the airfoil. Marginal separation, in particular, denotes the onset of separation which is accompanied by the formation of a short separation bubble. Using asymptotic analysis this effect is studied in the limit of high Reynolds number and for transonic external flow conditions. It is assumed that the fluid under consideration is a perfect gas and the airfoil surface is taken to be thermally insulated. Results to be presented include the analytical investigation of the emerging three layer structure, the associated transonic far field and the calculation of representative wall shear stress distributions. (© 2004 WILEY‐VCH Verlag GmbH & Co. KGaA, Weinheim)     

The Solution of Isentropic Transonic Flow

A general method for analysing mixed subsonic-supersonic flowshas been developed. It has been applied to the case of chokedisentropic flow in a convergent-divergent nozzle and the resultshave been compared with existing series solutions for simplegeometries; very good agreement has been found throughout theflow field. Good agreement has also been found with experimentalresults for the flow in nozzles of more complicated geometry.Some extensions of the method are mentioned such as the inclusionof boundary layer development and the analysis of flows withfree boundaries.     

Prediction of flow about an oscillating airfoil in a wind tunnel with timeaccurateinlet and outlet conditions

Non‐local inlet and outlet transparent boundary conditions (TBCs) are incorporated into the FLOWer code and tested for transonic flow problems about an oscillatingai rfoil in a non‐adapted wind tunnel. We show that TBCs require much smaller sizes of the computational domain for solvingt he problem comparingt he FLOWer type characteristic based boundary conditions (CBCFs). Moreover, solutions obtained with TBCs and CBCFs for the oscillatingai rfoil can strongly di.er from each other in the case of the “resonance” reduced frequencies.     

Transonic viscous inviscid interactions in narrow channels

Unsteady as well as steady transonic flows through channels which are so narrow that the classical boundary layer approach fails are considered. As a consequence the properties of the inviscid core and the viscosity dominated boundary layer region can no longer be determined in subsequent steps but have to be calculated simultaneously. The resulting interaction problem for laminar flows is formulated for both perfect and dense gases under the requirement that the channel is sufficiently narrow so that the flow outside the viscous wall layers becomes one-dimensional in the leading order approximation. The latter allows an interpretation of the flow in the core region by means of the theory of one-dimensional transonic inviscid flow through a Laval nozzle while preserving the essential features of the interaction problem associated with the internal structure of pseudoshocks. The sensitivity of a separation bubble caused by a pseudoshock of sufficient strength to perturbations under the condition of choked flow will be demonstrated. (© 2008 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim)     

Transonic flow on an axially symmetric torus

On a Riemannian manifold the existence (and uniqueness) of subsonic gas flows with prescribed circulation has been previously established (Acta Math.125 1970, 57–73). If the manifold is a torus of revolution then the gas dynamics equation reduces to a nonlinear ordinary differential equation and the flow can be described explicitly. We show that, as the circulations are increased, one obtains a complete family of solutions: smooth subsonic, smooth transonic, transonic with shocks, and smooth supersonic flows.     

Weakly 3D Transonic Flows in Narrow Channels

Steady transonic flows through channels so slender that the classical boundary layer approach fails are considered. The resulting viscous inviscid interaction problem for weakly three-dimensional laminar flows is formulated for perfect gases under the requirement that the channel is sufficiently narrow so that the flow outside the viscous wall layers becomes two-dimensional in the leading order approximation. The behavior of the flow upstream of a surface mounted three-dimensional obstacle will be demonstrated. (© 2010 Wiley-VCH Verlag GmbH & Co. KGaA, Weinheim)     

Real Gas Effects in Condensing Transonic Steam Flow

Considering the flow in the last stages of LP (low pressure) steam turbine the strong non‐linearity of the thermal parameters of state and the possibility of the two‐phase flow have to be taken into account in the numerical calculation of the flow field. In this paper a 3‐D numerical calculation of the steam condensing flow for the turbine geometry will be presented. The steam properties are described here on the basis of the IAPWS'97 formulation. The calculation of the condensation phenomenon allows one to determine the losses caused by the formation of the liquid phase and to predict the areas of erosion.     

Local Entropy Conditions in Transonic Potential Flow Problems

The transonic potential flow problem is handled as a variational problem over a closed convex set which is given by a bound for the gas velocity and by a local entropy condition. It can be shown that the minimum problem has a solution though the functional need not be convex and the given set is not compact. Furthermore, the convergence of an approximation method (KATCHANOV'S method) for the solution to the corresponding variational inequality is proved.     

Transonic potential flows in a convergent-divergent approximate nozzle

In this paper we prove existence, uniqueness and regularity of certain perturbed (subsonic-supersonic) transonic potential flows in a two-dimensional Riemannian manifold with “convergent-divergent” metric, which is an approximate model of the de Laval nozzle in aerodynamics. The result indicates that transonic flows obtained by quasi-one-dimensional flow model in fluid dynamics are stable with respect to the perturbation of the velocity potential function at the entry (i.e., tangential velocity along the entry) of the nozzle. The proof is based upon linear theory of elliptic-hyperbolic mixed type equations in physical space and a nonlinear iteration method.     

Verification of Complex Transonic Phenomena with CFD Codes

Classical analytic models for the theoretical behavior of transonic flows have guided the development of numerical simulation of practically relevant flows. But while operational successfully for the usual applications (conventional configuration high speed aerodynamics), CFD codes fail frequently once detailed information regarding even just inviscid flow structure for freestream Mach number close to unity is needed. In this contribution shock configurations are computed verifying analytical results for both the far field behavior of detached bow waves and the local structure of attaching bow waves. The first example is challenging the ability of a CFD code (DLR‐τ) to adapt its unstructured grid to a weak bow wave detached from the airfoil. Known analytical results for the asymptotic bow wave behavior at decreased Mach number → 1 serve for judging numerical results where practical case studies neither from CFD nor from experiment are available. In the second example the behavior of a bow wave attaching to a wedge for increased Mach number is studied, with grid adaption allowing for a verification of both the singular analytical model when attachment takes place and also the transition to plain supersonic wedge flow.     

Numerical Solution of Transonic Flow in SE1050 Cascade

The SE1050 cascade is an open test case (QNET network) of plane turbine cascade measured at the IT ASCR wind tunnel. The two regimes with subsonic and supersonic outletMach number were selected for numerical simulation. Several numerical methods have been developed and also several turbulence models have been implemented. Comparison of computed results and experimental data gives us opportunity to discuss main features of transonic flow field in well designed turbine cascade, possibilities of its numerical capturing (grid quality, numerical viscosity, turbulence model, boundary layer transition) and its influence on prediction of energy losses. (© 2005 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim)     

Transonic shocks for steady Euler flows with cylindrical symmetry

In this paper, we prove the existence of transonic shocks adjacent to a uniform one for the full Euler system for steady compressible fluids with cylindrical symmetry in a cylinder, and consequently show the stability of such uniform transonic shocks. Mathematically we solve a free boundary problem for a quasi-linear elliptic–hyperbolic composite system. This reveals that the boundary conditions and equations interact in a subtle way. The key point is to “separate” in a suitable way the elliptic and hyperbolic parts of the system. The approach developed here can be applied to deal with certain multidimensional problems concerning stability of transonic shocks for the full Euler system.     

Numerical Solution of Several Models of Internal Transonic Flow

The paper deals with numerical solution of internal flow problems. It mentions a long tradition of mathematical modeling of internal flow, especially transonic flow at our department. Several models of flow based on potential equation, Euler equations, Navier-Stokes and Reynolds averaged Navier-Stokes equations with proper closure are considered. Some mathematical and numerical properties of the model are mentioned and numerical results achieved by in-house developed methods are presented.     

Transonic viscous inviscid interactions in a slender Laval nozzle

Transonic, high Reynolds number flows through a Laval nozzle, which is so narrow that the classical boundary layer correction can no longer be considered to be an effect of higher order, are considered. As a consequence the properties of the inviscid core and the viscosity dominated boundary layer region can no longer be determined in subsequent steps but have to be calculated simultaneously. The resulting interaction problem for laminar flows in a small nozzle is presented for perfect gases. Representative solutions including the internal structure of pseudo-shocks forming in the diffuser part of the nozzle and being strongly associated with the chocking phenomenon will be presented. The linear stability of the various flow regimes observed in the nozzle will be discussed. (© 2010 Wiley-VCH Verlag GmbH & Co. KGaA, Weinheim)