A Conceptual Design Methodology to Predict the Wave Drag of a Transonic Wing
Abstract
A conceptual design methodology to predict the wave drag of a transonic wing for use within multisdisciplinary aircraft design was developed. To achieve this, a database of cross section designs optimized with respect to total drag was set up varying the design parameters Ma, t/c, C(L) and Re Mathematical formulations for the aerodynamic cross section characteristics total drag, viscous drag and the local shock location were derived from the database as functions of the design parameters. The cross section wave drag was then derived using these formulations. A locally infinite swept wing is assumed and simple sweep theory using the shock sweep angle is used to transform the wave drag. The wave drag of a 3-D wing is predicted summing locally infinite swept wing sections in spanwise direction. The achieved drag prediction is accurate enough for use within conceptual aircraft design.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 2000
- Accession Number
- ADP010522
Entities
People
- T. Kribler