Three Dimensional Transonic Model Testing on a Rocket Sled Track.
Abstract
This report presents the results of several rocket sled runs which were conducted on the Holloman High Speed Test Track facility. The objective of these runs was to collect aerodynamic and vibratory data on a rocket test sled which was specifically designed to test large three dimensional models at Mach numbers up to 1.5. The vehicle design emphasizes aerodynamic cleanliness and minimum frontal area while attempting to incorporate maximum stiffness in order to provide a relatively rigid testing platform in an undisturbed transonic flow field. Flow angularity measurements were made by three different methods. One method used pressure data obtained from a five hole direction probe, another used pressure data measured on a wing-body model which had been previously tested in wind tunnels, and the third method determined flow field angularity from model sting strain gage data. Mach number was calculated in two ways: from electro-optical space-time measurements and also using dynamic pressure readings. Vibration information on the sled/model interface was collected by triaxial accelerometer measurements obtained during several sled runs. Model and sting dynamics were measured with strain gage bridges installed on the model sting. Pressure measurements were taken on a wing-body model which was originally designed for wind tunnel use. The results are compared with wind tunnel data up to Mach 0.9. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1978
- Accession Number
- ADA054831
Entities
People
- Daniel J. Krupovage
Organizations
- Air Armament Center