An Elliptic Grid Generation Method for Cropped Delta Wings
Abstract
The solution of the Euler equations for aircraft flow fields involves two major problems: grid generation and flow equation solution. A grid must be generated for each new configuration to be studied. The grid must accurately model the configuration surface geometry and provide sufficient grid resolution in the region around the configuration to capture the flow details. Grid generation methods should be tailored according to both the physics of the flow and the flow equation solution method. The primary flow characteristic of the delta wing is the leading edge separation that rolls up into a vortex. The vortex position, size and strength are dependent on many factors, one of which is the leading edge shape. The leading edge grid must be fine enough to permit the flow solver to capture the flow gradients contributing to leading edge separation in order to accurately predict vortex core position and strength. The Euler equation solver used in this work is FL057. While FL057 has previously been applied to delta wing configuration, the built-in grid generation in FL057 is inadequate delta wings. A few aspects of FL057 should be kept in mind when considering a grid topology to be coupled to the Euler equation solver. A finite-volume and central-difference scheme is used by the method.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1988
- Accession Number
- ADA199462
Entities
People
- James R. Sirbaugh
Organizations
- Wright Laboratory