Date of Award


Access Type

Thesis - Open Access

Degree Name

Master of Science in Aerospace Engineering


Graduate Studies

Committee Chair

Dr. Eric Royce Perrell

First Committee Member

Dr. Reda Mankbadi

Second Committee Member

Dr. Anastasio Lyrintzis


Thermal Protection systems (TPS) are used as shields in space vehicles which encounter high heat and temperatures at the reentry altitudes. Among them, the cooling techniques and the ablative coatings are most popular. However, they have their own weight limitations. In the recent decade, another classification of TPS called the Non-Ablative Thermal Protection systems (NaTPS) have gained significance. The spike-lateral jet method is an NaTPS concept proposed for drag and heat flux reduction in hypersonic nose cones. Numerical simulations are conducted to analyze the effectiveness of spike-lateral jet concept at re-entry altitudes. The spike attached to the hemispherical nose has two circular orifices which eject air. The freestream conditions include Mach number 6 and standard atmospheric conditions at 30km altitude. The k-w turbulent model is used to model the case. It is apparent from the results that the lateral jet reconstructs the flow field by pushing the conical shock away and creating a large recirculation zone in front of the blunt body. This pushes the reattachment region rearward thus decreasing peak pressure and heat transfer to the body. The peak pressure at the flow reattachment point on the blunt body can be reduced by 35.9% for the laminar case and 30.0% for the turbulent case. The heat flux can be reduced by 54.1% for laminar case and 64.3% for the turbulent case. Lateral jet injection did not reduce drag as proposed, instead it increased drag by 65.7% and 59.1% for laminar and turbulent cases respectively. Base drag is not included in drag calculations. Results show that it might be promising for future applications of heat flux reduction and peak pressure reduction in reentry vehicles.

Included in

Astrodynamics Commons