Wave Drag Reduction Approach for Lattice Wings at High Speeds

Schülein, Erich; Guyot, Daniel

doi:10.1007/978-3-540-74460-3_41

Cited by 3 publications

(5 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Results on the drag coefficient for these two fins are presented in figure 14, along with experimental results obtained by other researchers on globally 12, 41 and locally 40 swept back grid fins with sharp leading edges. The evolution of the drag for the standard grid fin is in good agreement with the two experiments carried out by Debiasi 41 and Schuleïn and Guyot, 40 whereas the drag of the "Busemann" grid fin is consistent with the 2D numerical calculations performed by Hu et al 22 on the original Busemann biplane geometry. Although the drag is not decreased in the transonic regime due to the choking occurring in the cells in all cases, it is significantly reduced at higher Mach numbers for the "Busemann" grid fin, where a partial wave cancellation effect is observed.…”

Section: The "Busemann" Grid Finsupporting

confidence: 80%

“…10 Few non-conventional designs have been proposed by other researchers to reduce wave drag, using swept-back fins. 12,7,40 An alternative to the swept-back fin, investigated in this work, is based on the application of the Busemann biplane concept to grid fins. This concept consists in generating favourable wave interactions between two separated airfoil components at a specific Mach number, leading to the socalled "wave cancellation" effect.…”

Section: The "Busemann" Grid Finmentioning

confidence: 99%

See 1 more Smart Citation

Numerical analysis of static and dynamic performances of grid fin controlled missiles

Despeyroux

Desaulnier

Luciano

et al. 2014

32nd AIAA Applied Aerodynamics Conference

View full text Add to dashboard Cite

Grid fins have found different applications over the last three decades, from control surfaces in missiles and projectiles to emergency brakes and stabilization devices in space vehicles. Particularly, lattice fins provide a higher maneuverability to agile high-speed missiles in supersonic flow due to their capacity to maintain lift at higher angles of attack, while improving yaw and roll stability. The aerodynamic data available for such configurations includes static aerodynamic coefficients and stability derivatives, but there is only scarce information concerning dynamic stability derivatives such as the pitch damping derivative. Dynamic simulations have been carried out using the Stanford University Unstructured (SU 2 ) CFD code to investigate dynamic stability and maneuverability properties of a grid fin tail controlled generic missile in supersonic (Ma = 2) and transonic regimes (Ma = 0.9) at angles of attack up to 30˚. The pitch damping derivative is shown to be independent from the type of fin in supersonic regime whereas grid fins provide a lower damping in pitch than planar fins in transonic regime. The high drag generated by grid fins is also investigated numerically in this work. The Busemann biplane concept is applied to lattice fins and is shown to reduce significantly their drag in supersonic regime while maintaining their lift characteristics. The high drag in transonic flow can be reduced by using an "optimized Busemann" profile having a higher inlet-to-throat area ratio.

show abstract

Section: The "Busemann" Grid Finsupporting

confidence: 80%

Section: The "Busemann" Grid Finmentioning

confidence: 99%

Numerical analysis of static and dynamic performances of grid fin controlled missiles

Despeyroux

Desaulnier

Luciano

et al. 2014

32nd AIAA Applied Aerodynamics Conference

View full text Add to dashboard Cite

show abstract

“…Results for the drag coefficient for these two fins are presented in Fig. 27, along with experimental results obtained by other researchers for globally [16,19] and locally [46] sweptback grid fins with sharp leading edges. The evolution of the drag for the standard grid fin is in good agreement with the two experiments carried out by Debiasi [19] and Schuleïn and Guyot [46], whereas the drag of the Busemann grid fin is consistent with the two-dimensional numerical calculations performed by Hu et al [27] on the original Busemann biplane geometry.…”

Section: Drag Reduction Using the Busemann Biplane Conceptmentioning

confidence: 88%

“…Few nonconventional designs have been proposed by other researchers to reduce wave drag using sweptback fins [7,16,46]. An alternative to the sweptback fin, investigated in this work, is based on the application of the Busemann biplane concept to grid fins.…”

Section: Drag Reduction Using the Busemann Biplane Conceptmentioning

confidence: 99%

Numerical Analysis of Static and Dynamic Performances of Grid Fin Controlled Missiles

Despeyroux

Hickey

Desaulnier

et al. 2015

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

Grid fins provide good maneuverability to missiles in supersonic flow because they can maintain lift at a higher angle of attack. Although static aerodynamic data exist, very little quantitative dynamic performance information is available for grid fin controlled missiles. The high drag associated with grid fins is also a concern. Dynamic simulations are carried out using computational fluid dynamics to investigate the dynamic stability of a generic missile, controlled by grid fins or planar fins, in supersonic and transonic regimes at angles of attack up to 30 deg. In supersonic flow, the pitch-damping derivative is found to be insensitive to the control fin type; however, in transonic flow, grid fins provide a lower damping in pitch than planar fins due to the blockage effect induced by its choked cells. The reduction of the high drag associated with grid fins is also investigated by comparing the performances of two isolated grid fin geometries with and without the use of a Busemann biplane configuration. The application of this concept to grid fins reduces its drag in the supersonic regime while maintaining its beneficial lift characteristics. Furthermore, the drag of grid fins in transonic flow can be reduced by using an optimized profile with a higher inletto-throat area ratio.

show abstract

“…Using additive technology, it is now also possible to create complex compositions of metallic and ceramic materials that are difficult or impossible to obtain in other ways [12]. The peculiarities of gas-dynamic processes in creating lattice wings [13][14][15] and aircraft [16][17][18] have been studied. Parts of modern turbines experience high thermal loads [19][20][21], which require finding new solutions for designing cooled blades.…”

Section: Introductionmentioning

confidence: 99%

Simulation of Hybrid Mesh Turbomachinery using CFD and Additive Technologies

Sazonov

Mokhov²,

Gryaznova³

et al. 2022

Civ Eng J

View full text Add to dashboard Cite

This paper develops schematics and evaluates the performance of hybrid mesh turbomachinery at the patenting stage of individual technical solutions. This type of turbomachine uses reduced-sized blades and also forms flow channels with a mesh structure between the blades. The research methods are based on simulations using computational fluid dynamics (CFD) and additive technologies. An intermediate conclusion is that a new scientific direction for investigating and creating hybrid mesh turbomachinery equipped with mesh jet control systems was formed to develop Euler's ideas. This paper describes new possibilities for the simultaneous implementation of two workflows in a single impeller: 1) Turbine workflow, and 2) Compressor workflow. Calculation methods showed possible improvements in the performance of the new turbomachines. This paper considers options for mesh turbomachine operation in the two-stage gas generator mode with partial involvement of atmospheric air in the workflow. Preliminary calculations based on examples show that it is possible to expect a two- to four-times increase in thrust when using hybrid mesh turbomachines. Ongoing studies mainly focus on developing multi-mode turbomachinery that works in complicated conditions, such as offshore oil and gas fields, but some research results are applicable in other industries, for example, in developing hybrid propulsion systems or propulsors. Doi: 10.28991/CEJ-2022-08-12-011 Full Text: PDF

show abstract

Wave Drag Reduction Approach for Lattice Wings at High Speeds

Cited by 3 publications

References 1 publication

Numerical analysis of static and dynamic performances of grid fin controlled missiles

Numerical analysis of static and dynamic performances of grid fin controlled missiles

Numerical Analysis of Static and Dynamic Performances of Grid Fin Controlled Missiles

Simulation of Hybrid Mesh Turbomachinery using CFD and Additive Technologies

Contact Info

Product

Resources

About