Accession Number:

ADA024210

Title:

A Wind Tunnel Investigation of Impulse Effects on the Motion of an Impulse Correction Guidance Missile

Descriptive Note:

Final rept., 24 Jul 1975

Corporate Author:

ARO INC ARNOLD AFS TN

Personal Author(s):

Report Date:

1976-04-01

Pagination or Media Count:

46.0

Abstract:

Wind tunnel tests were conducted for the Air Force Armament Laboratory to obtain experimental data at Mach number 3 on an impulse correction guidance system. The guidance system is based on the principle of impulse correction. The purpose of the test program was to determine if the interaction of the impulse explosion with the supersonic airflow caused an effect on the model motion. The small-amplitude free-oscillation technique was used to obtain data on a 0.5 scale model at angles of attack from 1 to 4.4 deg at Reynolds numbers, based on model length, of 12.2 x 100,000 and 23.1 x 100,000. The explosion which produced the impulse affected the model flow field. However, this perturbed flow field did not produce any significant effects on the model motion, apparently because of the short action time involved.

Subject Categories:

  • Guided Missile Dynamics, Configurations and Control Surfaces
  • Air- and Space-Launched Guided Missiles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE