Test Data Report, Low-Speed Wind Tunnel Drag Test of a 2/5 Scale Lockheed AH-56 Cheyenne Door-Hinge Hub
Abstract
The Aviation Development Directorate of the U.S. Army Aviation and Missile Research, Development and Engineering Center (AMRDEC) conducted a drag test of a non-rotating 2/5 scale Lockheed AH-56 Cheyenne main rotor hub in the U.S. Army 7 by 10foot Wind Tunnel located at NASA Ames Research Center in Moffett Field, CA. The purpose of the test was to quantify the drag reduction on the Cheyennes unique door hinge style hub when the mechanical control gyro is removed, with the implicit assumption that the control and stabilization functions of the gyro could be replaced by a modern flight control system located somewhere within the aircrafts outer mold line. The model was tested in a number of non-rotating configurations, orientations, and tunnel conditions. Baseline results compared favorably with historical drag measurements, and showed approximately a 50 percent reduction in hub drag with the gyro removed, with an additional 10 percent reduction due to rudimentary streamlining of the bluff outer hub arm.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 2016
- Accession Number
- AD1011994
Entities
People
- Gerardo Nunez
- Robert Iii D. Vocke