Kirk, Lindsay Christine2013-09-162013-09-162013-05https://hdl.handle.net/11299/156851University of Minnesota M.S. thesis. May 2013. Major: Aerospace Engineering and Mechanics. Advisor: Graham V. Candler. 1 computer file (PDF); vii, 54 pages, appendix A.The effects of geometric changes on the amplification of first mode instability waves in an external supersonic boundary layer were investigated using numerical techniques. Boundary layer stability was analyzed at Mach 6 conditions similar to freestream conditions obtained in quiet ground test facilities so that results obtained in this study may be applied to future test article design to measure first mode instability waves. First, geometric parameters such as nose radius, cone half angle, vehicle length, and surface curvature for an axisymmetric cone geometry were examined separately to determine the individual effects on the first mode amplification. The DAKOTA optimization software package was then used to optimize the geometry to maximize the amplification of waves at first mode frequencies and to minimize the amplification of the waves at second mode frequencies, as computed by the 2D STABL hypersonic boundary layer stability analysis tool. This was accomplished by allowing all geometric parameters in the sensitivity study to vary to produce a shape optimized to maximize the amplification of first mode instability waves while minimizing the amplification of second mode instability waves. During this process, boundary layer edge properties were recorded to investigate any correlations. Results of the sensitivity analysis indicate that an axisymmetric cone with a sharp nose or an axisymmetric cone with a high degree of concave curvature under the Mach 6 freestream conditions used here will cause the largest amplification of first mode instability waves.en-USAerothermodynamicsBoundary layer stabilityFirst modeHypersonicSupersonicThesis or Dissertation