Airfoil Optimization through the Adaptive Control of Camber and Thickness. Phase II: Transonic Wind Tunnel Test and Program Summary.
Abstract
A new interactive wind tunnel technique for optimizing airfoil shape has been demonstrated satisfactorily under both low speed and transonic flow conditions. The transonic program reported herein, was conducted in the two-dimensional section of the General Dynamics High Speed Tunnel (GDHST) of blow-down type at a nominal Mach number of 0.75. The program utilized a flexible airfoil model whose shape could be conformally varied during a run (of approximately one minute duration) by means of five pair of hydraulic actuators. The airfoil shape and angle of attack were controlled by a link-up of three analog and digital computers which analyzed the wind tunnel balance data 'on-line' and adjusted the airfoil shape and angle of attack to optimize a given merit function.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1975
- Accession Number
- ADA020326
Entities
People
- E. S. Levinsky
- R. H. Schappelle
- S. Pountney
Organizations
- General Dynamics