2026-09-22T09:57:05Z https://www.ideals.illinois.edu/oai-pmh

oai:www.ideals.illinois.edu:2142/120412 2023-09-05 col_2142_5131 col_2142_14800 com_2142_5130 com_2142_14799 com_2142_234

Levin, Deborah A 2023-05 application/pdf en text Submission published under a 24 month embargo labeled 'U of I Access', the embargo will last until 2025-05-01 The student, Nathan Thomas, accepted the attached license on 2023-04-24 at 13:04. The student, Nathan Thomas, submitted this Thesis for approval on 2023-04-24 at 13:12. This Thesis was approved for publication on 2023-04-26 at 10:11. DSpace SAF Submission Ingestion Package generated from Vireo submission #19139 on 2023-09-01 at 17:14:45 Infrared radiation profiles of a hypersonic glide vehicle during re-entry Thomas, Nathan Robert 2023-04-26 Ir Profiles Hypersonic Vehicle Hgv Cfd Hvbets An HGV trajectory was calculated for a waverider configuration boosted to an altitude of 60 (km) with a ∆V of 3.7 ( km/s ). For the hypersonic vehicle the total downrange distance was 3250 (km) over a flight time of 21.75 minutes. Using a semi-empirical model for the stagnation point heat flux it was found that the maximum along the trajectory was ̇Q = 4x106 ( W/m2 ). CFD simulations of the HIFiRE-5 flight test vehicle were completed at chosen points along the trajectory and it was found that the semi-empirical model under-predicted the simulated stagnation point values at every location. It is hypothesized that the ratio of wall to total enthalpy plays a significant role in this under prediction and it is shown that as this ratio approaches 0 the results have much better agreement with the semi-emperical model. An in-house CFD post-processing software package (HVBETS) is validated and used to measure the IR signature profile of the vehicle and the high temperature wake. The vehicle surface signature varies between 0.5 and 6.4 ( kW/Sr ) and the wakesignature varies between 8.27x10−5 and 9.97x10−5 ( W/Sr/cm2 ). It is hypothesized that the orders of magnitude difference between the two IR sources is due to the conditions imposed on the wake at an altitude of 70 (km). The ground work for future analysis is laid where the parameters of the wake are changed to increase the total contribution and determine which variables are most important for the IR wake signature. Thesis eng https://hdl.handle.net/2142/120412 Copyright 2023 Nathan Thomas M.S. Thesis Aerospace Engineering University of Illinois at Urbana-Champaign Aerospace Engineering