An Engineering Evaluation of the AFATL Five-Percent-Scale Wind Tunnel Model of the F-4 Aircraft.
Abstract
Wind tunnel evaluation tests were conducted with a five-percent-scale wind tunnel model of the F-4C/D/E aircraft to determine how well the model represents the aerodynamic characteristics of the full scale aircraft. The tests simulated flight from Mach 0.5 to 1.3 with aircraft angles of attack from -4 to +15 degrees. Force and moment coefficients and incremental drag data obtained with this model were in excellent agreement with data presented by the aircraft manufacturer. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1971
- Accession Number
- AD0888046
Entities
People
- John L. Holmberg
- Victor E. Studwell