Accession Number:

AD0757273

Title:

Fundamental Research on Advanced Techniques for Sonic Boom Suppression

Descriptive Note:

Final rept.

Corporate Author:

TENNESSEE UNIV SPACE INST TULLAHOMA

Report Date:

1972-11-01

Pagination or Media Count:

201.0

Abstract:

A multiphase theoretical investigation on predicting and alleviating sonic boom intensity is described. A new theory to predict sonic boom intensity on the ground from wind tunnel tests using normal size models as opposed to the very small models presently used was developed. A relatively easy method to determine aircraft contours with desirable finite pressure rise times is presented, as is a method to determine phantom body shapes with desirable pressure rise times which can be simulated by heat addition to the flow upstream of the aircraft. It is shown that a slotted nozzle engine exhaust has the unique capability to shift lift from the solid surface of the wing to the region behind the wing, with a resulting reduction in sonic boom intensity.

Subject Categories:

  • Acoustics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE