Sting Interference Effects on the SDM Aircraft as Determined by Measurements of Dynamic Stability Derivatives and Base Pressure for Mach Numbers 0.3 through 1.3.
Abstract
An investigation was conducted to determine the effects of sting-support interference on the measurement of pitch damping, yaw-damping, pitching-moment slope, yawing-moment slope, pitching moment, and base pressure. The model was the Standard Dynamics Model (SDM). The forced oscillation technique was used to obtain data at Mach numbers 0.3 to 1.3 and Reynolds numbers, based on the model mean aerodynamic chord (MAC), of 0.3 million to 3.1 million. Amplitudes of oscillation were 1.0, 1.5, and 2.0 deg, and the reduced frequency parameter ranged from 0.009 to 0.032 radians.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1980
- Accession Number
- ADA110324
Entities
People
- F. B. Cyran
- M. J. Chaney
Organizations
- Arnold Engineering Development Complex