Development of Spoiler Controls for Remote Control of Flying Missiles
Abstract
A discussion is presented on the aerodynamic, structural, and instrumental development of a spoiler control for guided missiles. The spoiler was made to operate satisfactorily up to a Mach number 0.9 by increasing the airfoil trailing-edge thickness, thereby reducing the boundary layer; and by projecting the spoiler from a faired "step" which eliminated the dead spot at low deflections. There is no indication that the spoiler will be effective at supersonic speeds. Details of the construction and instrumentation are outlined.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1949
- Accession Number
- ADB810240
Entities
People
- G. Ernst
- Michael Kramer
Organizations
- National Advisory Committee for Aeronautics