Aerodynamic design integration of supersonic aircraft

Baals, Donald D.; Harris, R. V.; Robins, A. W.

doi:10.2514/6.1968-1018

Cited by 13 publications

(1 citation statement)

References 7 publications

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“…Far-field methods 1 ' 2 have been widely used for this purpose for many years. The application of these techniques is relatively straightforward, and the required computer resources are modest* These far-field methods are most successful, however, when applied to slender configurations, 3 and problems are often encountered when analyzing nonslender fighter concepts. 4 To assess more accurately the zerolift wave drag of such configurations, the aerodynamic designer must look to the nonlinear aerodynamic methodologies.…”

Section: Introductionmentioning

confidence: 98%

Wave drag analysis of realistic fighter aircraft using a full-potential method

Walkley

Smith

1987

Journal of Aircraft

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Wave drag coefficients for several aircraft configurations have been computed using a full-potential method and have been compared with the results of parallel far-field (area rule) analyses and experimental zero-lift drag data. The aircraft analyzed included a supersonic cruise configuration, an advanced fighter concept, and the F-16 aircraft. The results of these studies indicate that the full-potential method generally gives wave drag levels that agree more closely with test data than do the far-field values. The full-potential method does not encounter problems when components such as wing or tail leading edges or canopy forward faces are at sonic conditions, as does the far-field technique. The full-potential code does, however, encounter problems in generating computational grids in deeply recessed areas such as diverters.

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Section: Introductionmentioning

confidence: 98%

Wave drag analysis of realistic fighter aircraft using a full-potential method

Walkley

Smith

1987

Journal of Aircraft

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Supersonic Aircraft Shape Optimization

Velden¹

1997

New Design Concepts for High Speed Air Transport

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Computer aided aircraft project design

Hitch¹

1977

Aeronaut. j.

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The computer can be used in many ways to assist in the project and design stages of aircraft development. As would be expected it was used first to assist in the more unwieldy calculations of the design stage. Massive calculation sequences which previously involved much tedious labour, or were effectively beyond the capacity of a design office to perform, suddenly became a few hours work for one or two technicians. Project analysis, being concerned with an earlier stage of development where calculations are simpler and more approximate, tended to remain largely unaffected. However, it became clear that the very simplicity of the preliminary project calculations would, at least in principle, allow the entire project analysis phase to be computerised, so allowing many parametric variations to be done in a short time with minimum effort. The natural follow-on to this was the optimising project analysis program of which examples now exist. With such programs one is able to predict an optimum configuration to meet a given requirement, given only the basic data to define the scope of the calculation.

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Aerodynamic design integration of supersonic aircraft

Cited by 13 publications

References 7 publications

Wave drag analysis of realistic fighter aircraft using a full-potential method

Wave drag analysis of realistic fighter aircraft using a full-potential method

Supersonic Aircraft Shape Optimization

Computer aided aircraft project design

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