Computation of supersonic flows over three-dimensional configurations

Szema, K. Y.; Riba, W.; Shankar, Vijaya; Gorski, Joseph J.

doi:10.2514/3.45253

Cited by 6 publications

(1 citation statement)

References 3 publications

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“…12 The SIMP code has been applied to fighter configurations, the space shuttle orbiter, and the space shuttle orbiter/external fuel tank assembly. 13 The purpose of this paper is to present and discuss the results of several zero-lift wave drag analyses conducted using the SIMP full-potential methodology. 11 The primary emphasis in these studies has been to apply the full-potential methodology to complex and realistic configurations at zerolift and to compare these results with similar analyses conducted using the far-field (area rule) methodology.…”

Section: Introductionmentioning

confidence: 99%

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: 99%