Efficient viscous design of realistic aircraft configurations

Campbell, Richard L.

doi:10.2514/6.1998-2539

Cited by 65 publications

(32 citation statements)

References 19 publications

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“…In addition, both flow solvers have been coupled for use with the CDISC design method (Ref. 13) developed at the NASA Langley Research Center. Since the research focuses on realistic flight Reynolds numbers, the simulated flow fields were assumed to be fully turbulent.…”

Section: Methodsmentioning

confidence: 99%

On the Application of Contour Bumps for Transonic Drag Reduction (Invited)

Milholen

Owens

2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

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The effect of discrete contour bumps on reducing the transonic drag at off-design conditions on an airfoil have been examined. The research focused on fully-turbulent flow conditions, at a realistic flight chord Reynolds number of 30 million. State-of-the-art computational fluid dynamics methods were used to design a new baseline airfoil, and a family of fixed contour bumps. The new configurations were experimentally evaluated in the 0.3-m Transonic Cryogenic Tunnel at the NASA Langley Research center, which utilizes an adaptive wall test section to minimize wall interference. The computational study showed that transonic drag reduction, on the order of 12% -15%, was possible using a surface contour bump to spread a normal shock wave. The computational study also indicated that the divergence drag Mach number was increased for the contour bump applications. Preliminary analysis of the experimental data showed a similar contour bump effect, but this data needed to be further analyzed for residual wall interference corrections.

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Section: Methodsmentioning

confidence: 99%

On the Application of Contour Bumps for Transonic Drag Reduction (Invited)

Milholen

Owens

2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

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“…In an unpublished study, the CDISC design method 11 coupled with the OVERFLOW overset grid Navier-Stokes flow solver 12 (OVERDISC) was applied to an early twin-engine version of the BWB. The design modified the wing and the outer nacelle surfaces, although the nacelle-wing intersection had to be fixed due to grid movement difficulties.…”

Section: A Design Methods Selectionmentioning

confidence: 99%

Designing and Testing a Blended Wing Body with Boundary-Layer Ingestion Nacelles

Carter¹,

Campbell²,

Pendergraft³

et al. 2006

Journal of Aircraft

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“…This approach has been successfully used with the CDISC design method 13 in the past and, though slightly less efficient than a more direct coupling of methods, allows users to select the flow solvers that they have experience with and confidence in, and provides a consistency of approach if multiple codes are used in the design project. In the development of the initial version of the system, the USM3D unstructured grid Navier-Stokes code, which, along with the VGRID grid generator and various utility codes, comprise the TetrUSS software system 14 , was used for 3-D configurations.…”

Section: B Overall Approachmentioning

confidence: 99%

Progress Toward Efficient Laminar Flow Analysis and Design

Campbell

Streit

2011

29th AIAA Applied Aerodynamics Conference

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A multi-fidelity system of computer codes for the analysis and design of vehicles having extensive areas of laminar flow is under development at the NASA Langley Research Center. The overall approach consists of the loose coupling of a flow solver, a transition prediction method and a design module using shell scripts, along with interface modules to prepare the input for each method. This approach allows the user to select the flow solver and transition prediction module, as well as run mode for each code, based on the fidelity most compatible with the problem and available resources. The design module can be any method that designs to a specified target pressure distribution. In addition to the interface modules, two new components have been developed: 1) an efficient, empirical transition prediction module (MATTC) that provides n-factor growth distributions without requiring boundary layer information; and 2) an automated target pressure generation code (ATPG) that develops a target pressure distribution that meets a variety of flow and geometry constraints. The ATPG code also includes empirical estimates of several drag components to allow the optimization of the target pressure distribution. The current system has been developed for the design of subsonic and transonic airfoils and wings, but may be extendable to other speed ranges and components. Several analysis and design examples are included to demonstrate the current capabilities of the system.

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Efficient viscous design of realistic aircraft configurations

Cited by 65 publications

References 19 publications

On the Application of Contour Bumps for Transonic Drag Reduction (Invited)

On the Application of Contour Bumps for Transonic Drag Reduction (Invited)

Designing and Testing a Blended Wing Body with Boundary-Layer Ingestion Nacelles

Progress Toward Efficient Laminar Flow Analysis and Design

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