<p dir="ltr">Prediction of boundary-layer transition is a critical element of hypersonic vehicle design</p><p dir="ltr">due to the impact transition has on boundary-layer separation, heat transfer, and aerodynamic</p><p dir="ltr">control. Transition is affected by many factors including surface roughness. The</p><p dir="ltr">roughness on a hypersonic vehicle can cause a boundary-layer to become turbulent. However,</p><p dir="ltr">there is a limited understanding of the impacts that roughness can have, and the conditions</p><p dir="ltr">under which it is important.</p><p dir="ltr">The rocket-sled track at Holloman Air Force Base was selected as a ground-test facility</p><p dir="ltr">for transition measurements. The present work is about understanding the mechanism of</p><p dir="ltr">transition on blunt ogives or blunt cones with moderate nose radii, as it appears that nosetip</p><p dir="ltr">roughness affects boundary-layer transition on the afterbody for moderate nose radii. A</p><p dir="ltr">single test-track shot is to be executed for a blunt ogive to determine if the test track can</p><p dir="ltr">make useful measurements of boundary-layer transition.</p><p dir="ltr">Initially, the present research used a boundary-layer solver to estimate target roughnesses</p><p dir="ltr">that would be applied to the nose tip. Preliminary analysis was conducted on test cases for</p><p dir="ltr">sharp cones and blunt cones. However, due to time constraints, the target roughnesses were</p><p dir="ltr">then estimated with a higher fidelity code by Brad Wheaton of JHU APL. Two separate</p><p dir="ltr">roughness targets were established for the upper and lower sides of the hemispherical nosetip.</p><p dir="ltr">The focus of this work then shifted to measurements of the roughness that was applied</p><p dir="ltr">by others to the hemisphere nose tip for a blunt ogive. Utilizing the Zygo ZeGage 3D optical</p><p dir="ltr">profiler, roughness scans were collected both directly under the profiler head and indirectly</p><p dir="ltr">using rubber molds. Profilometer measurements were also recorded. Twelve iterations were</p><p dir="ltr">completed to allow the polisher to develop appropriate procedures for applying the roughness,</p><p dir="ltr">given the material and curvature. The first five iterations involved roughness applied to</p><p dir="ltr">cylindrical-shaped test areas. After achieving the target roughnesses on these test areas,</p><p dir="ltr">the hemispherical ends of test specimens were then polished and measured until both the</p><p dir="ltr">rough and smooth halves met the roughness target. During this time, the three roughness measurement</p><p dir="ltr">techniques were refined until good agreement was reached between them. When the roughness-application and </p><p dir="ltr">roughness-measurement techniques were sufficiently mature,</p><p dir="ltr">the actual blunt-ogive nose tip was then polished until the roughness target was achieved.</p>
| Identifer | oai:union.ndltd.org:purdue.edu/oai:figshare.com:article/25665543 |
| Date | 23 April 2024 |
| Creators | Owen States (18422706) |
| Source Sets | Purdue University |
| Detected Language | English |
| Type | Text, Thesis |
| Rights | CC BY 4.0 |
| Relation | https://figshare.com/articles/thesis/Hypersonic_Boundary-Layer_Transition_on_a_Blunt_Ogive_Measuring_Controlled_Nose_Tip_Roughness/25665543 |
Page generated in 0.0021 seconds