Application of the pressure sensitive paint technique to steady and unsteady flow /

"June 1996."

The unsteady flow field about a right circular cone in unsteady flight.

"These studies were conducted by the General Electric Company, Reentry Systems Department, for the Stability and Control Section of the Flight Dynamics Laboratory of the Air Force Research and Technology Division."

Investigation of the need for discharge adjustments for unsteady flow at selected gaging stations on streams in Tennessee /

Shipping list no.: 86-295-P.

The method of characteristics in compressible flow.

Reproduced from typewritten copy.

Hypersonic dynamic stability.

pt. 1. Summary [by] L. A. Marshall.--pt. 2. Conical body experimental program [by] R. B. Hobbs, Jr.--pt. 3. Unsteady flow field program [by] H. Rie, E. A. Linkiewicz [and] F. D. Bosworth.

A method for computing nonsteady, incompressible, viscous fluid flows /

"Contract W-7405-ENG. 36 with the U.S. Atomic Energy Commission."

The calculation of three-dimensional supersonic flows around spherically-capped smooth bodies and wings

"Work performed for the Air Force Flight Dynamics Laboratory...by the Aerodynamics Research Department of the Northrup Corporation, Aircraft Division."

On local flat-plate similarity in the hypersonic boundary layer,

Mode of access: Internet.

An experimental investigation of the unsteady aerodynamics of passing highway vehicles. Final report.

National Highway Traffic Safety Administration, Washington, D.C.

An experimental investigation of the unsteady aerodynamics of passing highway vehicles. Final summary.

National Highway Traffic Safety Administration, Washington, D.C.

Unsteady stall of axial flow compressors

"Contract no. DA-49-186-AM-13 (X)"

Computation of rapidly varied unsteady, free-surface flow /

Shipping list no.: 87-677-P.

Unsteady, one-dimensional flow over a plane; the rising hydrograph

Caption title.

Investigation of the flow over simple bodies at Mach numbers of the order of 20 /

"It is shown that adequate means are available for calculating inviscid direct and induced pressures on simple axisymmetric bodies at zero angle of attack. The extent to which viscous effects can alter these predictions is indicated. It is also shown that inviscid induced pressures can significantly affect the stability of blunt, two-dimensional flat wings at low angles of attack. However, at high angles of attack, the inviscid induced pressure effects are negligible."

An investigation of the exact solutions of the linearized equations for the flow past conical bodies,

Reproduced from type-written copy.