Supersonic flow field visualization studies of the MÅ = 6 price waverider planform

Supersonic tests of the conical flow derived MŠʻ = 6 (design) Price waverider planform were conducted using the Naval Postgraduate School wind tunnel. These tests are part of a continuing effort to study the characteristics of waverider configured vehicles. Two sting-mounted, flat-plate stainless-steel Price waverider planform models were utilized for testing in the NPS 4-inch by 4-inch cross section supersonic blowdown wind tunnel. Tests at Mach numbers of MŠʻ = 1.7, 2.8 and 4 were attempted but flowfield studies were only completed at MŠʻ = 4. Sting mount flow blockage (choked flow) prevented test section starting at freestream test Mach numbers of MŠʻ = 1.7 and 2.8. Horizontal (side-view) and vertical (top-view) mounted shadowgraph pictures and pressure sensitive paint images were taken at pitch angles of ⠭¿ = 0Šʺ, 2Šʺ and 4Šʺ. The Mach 4 shadowgraph and pressure sensitive paint results correlate well with previous CFD results using the three-dimensional Price waverider model. The choked flow tests at MŠʻ = 1.7 and 2.8 are discussed in detail; suggestions are given for future work in this Mach number test spectrum.

Department dc:contributor.department

Aeronautical Engineering

Grantor dc:publisher

Monterey, California. Naval Postgraduate School

Year dc:date.issued

2001

Author dc:creator

• Garcia, Karl

Advisor dc:contributor.advisor

• Newberry, Conrad F.

Statement dc:rights

• This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.

Handle dc:identifier.uri

https://hdl.handle.net/10945/1639

OAI identifier oai:identifier

oai:calhoun.nps.edu:10945/1639