Ballistic Tube for Drag Measurement on Models in Free Flight at Hypersonic Speeds,
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 04, 1972
- Accession Number
- AD0749839
Entities
People
- A. P. Krasilshchikov
- L. P. Guryashkin
- V. P. Podobin
Organizations
- National Air and Space Intelligence Center