Accession Number:

AD0749839

Title:

Ballistic Tube for Drag Measurement on Models in Free Flight at Hypersonic Speeds,

Descriptive Note:

Corporate Author:

FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO

Report Date:

1972-08-04

Pagination or Media Count:

12.0

Abstract:

A brief description is presented of a wind tunnel, the underlying principle of operation of which is firing model bodies into an oncoming supersonic flow. The wind tunnel was designed for measurements of the drag coefficient and for studies of the characteristics of flow past axisymmetric bodies in the range of supersonic and hypersonic flight velocities. Author

Subject Categories:

  • Test Facilities, Equipment and Methods

Distribution Statement:

APPROVED FOR PUBLIC RELEASE