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

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Authors
Garcia, Karl
Subjects
Advisors
Newberry, Conrad F.
Date of Issue
2001-09
Date
Publisher
Monterey, California. Naval Postgraduate School
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Abstract
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.
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Thesis
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Department
Aeronautical Engineering
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Format
xvi, 91 p. ;bills. :
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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.
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