Supersonic Airfoils of Minimum Total Drag,
Abstract
Minimum drag airfoil shapes in supersonic flow for a given chord length are considered. The shapes are assumed to be two-dimensional and symmetric. In order to relate the drag of the airfoil to its geometry, it is assumed that the airfoil is slender. The boundary layer is specified to be entirely turbulent. Two cases are solved: (a) minimum drag shape for a given chord and (b) minimum drag shape for a given chord and heat transfer rate. For each case, the minimal shape is obtained by employing the calculus of variations in one independent and dependent variable to the drag expression. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1970
- Accession Number
- AD0726767
Entities
People
- Don James Hull
Organizations
- University of Texas at Austin