A natural flow wing design employing 3-D nonlinear analysis applied at supersonic speedsA wing-design study has been conducted on a 65-deg-swept leading-edge delta wing in which a near-conical geometry was employed to take advantage of the naturally occurring conical flow which arises over such a wing in a supersonic flow field. Three-dimensional nonlinear analysis methods were used in the study. In preliminary design, wing planform, design conditions, and near-conical concept were derived and a baseline standard wing (conventional airfoil distribution) and a baseline near-conical wing were chosen. During the initial analysis, a full-potential solver was employed to determine the aerodynamic characteristics of the baseline standard delta wing and the near-conical delta wing. Modifications due to airfoil thickness, leading-edge radius, and camber were then applied to the baseline near-conical wing. The final design employed a Euler solver to analyze the best wing configurations found in the initial design, and to extend this study to develop a more refined wing. Benefits due to each modification are discussed, and a final natural flow wing geometry is chosen and its aerodynamic characteristics are compared with the baseline wings.
Document ID
19890062306
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bauer, Steven X. S. (NASA Langley Research Center Hampton, VA, United States)
Wood, Richard M. (NASA Langley Research Center Hampton, VA, United States)
Brown, S. Melissa (NASA Langley Research Center Hampton, VA, United States)