Selected Data Set from Static and Rolling Experiments on a 65 Deg. Delta Wing at High Incidence
Abstract
This data set is selected from an extensive set of experimental results obtained for configurations with a 650 delta wing under static as well as large-amplitude high-rate rolling or pitching conditions at high incidence. The experiments were performed under a joint research program on "Non-Linear Aerodynamics under Dynamic Maneuvers" by the National Research Council of Canada (NRC (IAR)), the U.S. Air Force (USAF (AFOSR, AFRL)) and the Canadian Dept. for National Defence (DND). NASA Ames informally participated in the program through its substantial CFD work on specific test conditions. The experimental results provide both detail pressure measurements and a wide range of flow conditions covering from simple attached flow, through fully developed vortex and vortex burst flow, up to fully-stalled flow at very high incidence. Since this data set includes different levels of physical difficulty, the computational researchers wording in unsteady aerodynamics can use it as a staircase approach to the problem of validating their corresponding code Four schematic and representative configurations' were selected in the experiments (Fig. 1 to Fig. 3):
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 2000
- Accession Number
- ADP010723
Entities
People
- X. Z. Huang
Organizations
- National Aeronautics and Space Administration