Supersonic flow field visualization studies of the MÅ = 6 price waverider planform
Newberry, Conrad F.
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Supersonic tests of the conical flow derived MÅ Ê» = 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 MÅ Ê» = 1.7, 2.8 and 4 were attempted but flowfield studies were only completed at MÅ Ê» = 4. Sting mount flow blockage (choked flow) prevented test section starting at freestream test Mach numbers of MÅ Ê» = 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 â Â¿ = 0Å Êº, 2Å Êº and 4Å Êº. 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 MÅ Ê» = 1.7 and 2.8 are discussed in detail; suggestions are given for future work in this Mach number test spectrum.
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