Publication:
Low-speed wind tunnel testing of the NPS/NASA Ames Mach 6 optimized waverider

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Authors
Cedrun, Mark E.
Subjects
NA
Advisors
Newberry, Conrad F.
Bowles, Jeffrey V.
Date of Issue
1994-06
Date
June, 1994
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
Low-speed wind tunnel tests were conducted to determine the subsonic aerodynamic characteristics of an optimized supersonic (Mach 6) conical-flow waverider designed for a deck-launched intercept mission. These tests are part of the continuing waverider research being conducted by the Naval Postgraduate School and the NASA Ames Research Center. The tests consisted of performing Alpha and Beta sweeps, at different dynamic pressures, with a 15 inch aluminum waverider model in the NPS low-speed wind tunnel. Force and moment data were then collected using a six-degree-of-freedom sting balance. Coefficients of lift, drag and pitch were calculated from the data and compared to theory and existing waverider subsonic aerodynamic performance data. Flow visualization using tufts was also done. The results of the experiments show that waverider exhibits high lift characteristics at positive angles of attack. The design also compares favorably with both subsonic thin airfoil theory and the results of the delta wing and subsonic waverider analysis done by Vanhoy. However, flow visualization showed that vortex bursting occurred at a dynamic pressure of 12. llbf at +/-15 degrees angle of attack. Based upon the data collected in this analysis, the development of an actual waverider aircraft using the NPS/NASA ames waverider design as a baseline is a plausible endeavor.
Type
Thesis
Description
Series/Report No
Department
Aeronautical Engineering
Organization
NA
Identifiers
NPS Report Number
Sponsors
Funder
NA
Format
96 p.;28 cm.
Citation
Distribution Statement
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.
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