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American Institute of Aeronautics and Astronautics

    Thermal Modeling and Regenerative Cooling of Liquid Rocket Engines

    6 April 2018.  1300-1430 Eastern Daylight Time
    Member Price: $99
    Non-Member Price: $149
    Student Member Price: $9.99 USD

    Register Here


    Thermal analysis is an essential and integral part in the design of rocket engines. In the high-pressure engines hot-gas temperatures are very high (they can reach 7000R at the throat area). It is therefore essential to be able to estimate the wall temperature and ensure that the material can withstand such high temperature. Furthermore, an accurate thermal model enables an engine designer to modify the cooling channel configuration for the optimum cooling at high temperature areas. This course presents an overview of various methods for thermal modeling of cooling liquid engines. The cooling methods include: regenerative, film, transpiration, radiative and dump cooling. Simple as well comprehensive computer models are discussed. The participant at the end of this webinar will be able to develop their own rocket thermal analysis model using available public domain software or use existing comprehensive computer programs.


    Learning Objectives

    • An understanding of various cooling methods for liquid rocket engines
    • Importance of regenerative cooling
    • Various coolants and propellants
    • Heat transfer enhancement
    • Cooling circuit design
    • Computer models for thermal analysis of liquid rocket engines


    Who Should Attend

    This webinar is intended for students and professionals in the aerospace industry working on Liquid Rocket Engines. Aerospace engineering students and others in the aerospace industry who want to learn more about the topic of thermal modeling.



    Mohammad-NaraghiDr. Mohammad Naraghi.
    Dr. Mohammad Naraghi is a Professor Mechanical Engineering at Manhattan College, and an adjunct Professor of Mechanical Engineering at Columbia University. Prior to joining Manhattan College, he was a Visiting Assistant Professor of Mechanical Engineering at University of Akron where he received his Ph.D. in Mechanical Engineering. Dr. Naraghi in collaboration with NASA Glenn Research Center developed a comprehensive Rocket Thermal Evaluation code (RTE), which is used by NASA research centers and aerospace companies. Dr. Naraghi's research is in Thermal/Fluids area and he has published more than eighty articles in ASME, AIAA and international journals and conferences. He is recipient of a number of research grants from NASA and Air Force. Dr. Naraghi is a Fellow of ASME, Associate Fellow of AIAA, and a member of AIAA’s Liquid Propulsion Technical Committee.


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