WIND TUNNEL TESTS ON WEAPON CONTROLS FOR HIGH ALTITUDES AND SPEEDS
Abstract
Experimental results are presented on the effectiveness of various flight controls suitable for high altitudes and speeds. The controls include reaction jets, canard surfaces, and flaps. They were mounted on cylindrical, flared, finned, and split skirt afterbodies and near the vehicle nose. The tests were carried out in NOL Supersonic Tunnel No. 1 at a Mach number of 4.85. It was found that the controls were most effective when mounted on flared afterbodies, except for the reaction jet, which produced the largest interaction force on a finned body. Canard surfaces were superior to flaps for nosecontrolled weapons. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 09, 1964
- Accession Number
- AD0349439
Entities
People
- A. P. Leonas
- J. B. Eades Jr.
Organizations
- Naval Ordnance Laboratory