Cooling aerospace plane using hydrogen, ammonia and kripton

Ahmed Z. Al-Garni; Ahmet Z. Sahin; Amro M. Al-Qutub

Cooling aerospace plane using hydrogen, ammonia and kripton

Ahmed Z. Al-Garni
, Ahmet Z. Sahin
, Amro M. Al-Qutub

King Fahd University of Petroleum and Minerals

Araştırma sonucu: Konferansa katkı › Yazı › bilirkişi

2 Atıf (Scopus)

Özet

In this paper, a comparative study is made for cooling aerospace plane, using liquid HZ, NHs, and Kr. The study includes the cooling for the stagnation point, the leading edges for wings, engine and other parts of the aerospace plane that are close to the leading edges. Laminar case for the stagnation point and both laminar and turbulent cases for the leading edge heating have been considered. The amount of heat rate (total, radiative and convective) and the mass of liquid coolant needed for cooling are calculated. A design of minimum inlet-outlet areas for the amount of liquid needed for cooling, is made with the consideration of the coolant's physical constraints in liquids and gaseous states. When compared to the other coolants, hydrogen is found to be the superior candidate for cooling aerospace plane.

Orijinal dil	İngilizce
Yayın durumu	Yayınlandı - 1997
Harici olarak yayınlandı	Evet
Etkinlik	32nd Thermophysics Conference, 1997 - Atlanta, United States Süre: 23 Haz 1997 → 25 Haz 1997

???event.eventtypes.event.conference???

???event.eventtypes.event.conference???	32nd Thermophysics Conference, 1997
Ülke/Bölge	United States
Şehir	Atlanta
Periyot	23/06/97 → 25/06/97

Bibliyografik not

Publisher Copyright:
© by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

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Alıntı Yap

@conference{c8956912dc594e6dac953e11916a0416,

title = "Cooling aerospace plane using hydrogen, ammonia and kripton",

abstract = "In this paper, a comparative study is made for cooling aerospace plane, using liquid HZ, NHs, and Kr. The study includes the cooling for the stagnation point, the leading edges for wings, engine and other parts of the aerospace plane that are close to the leading edges. Laminar case for the stagnation point and both laminar and turbulent cases for the leading edge heating have been considered. The amount of heat rate (total, radiative and convective) and the mass of liquid coolant needed for cooling are calculated. A design of minimum inlet-outlet areas for the amount of liquid needed for cooling, is made with the consideration of the coolant's physical constraints in liquids and gaseous states. When compared to the other coolants, hydrogen is found to be the superior candidate for cooling aerospace plane.",

author = "Al-Garni, \{Ahmed Z.\} and Sahin, \{Ahmet Z.\} and Al-Qutub, \{Amro M.\}",

note = "Publisher Copyright: {\textcopyright} by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.; 32nd Thermophysics Conference, 1997 ; Conference date: 23-06-1997 Through 25-06-1997",

year = "1997",

language = "English",

}

TY - CONF

T1 - Cooling aerospace plane using hydrogen, ammonia and kripton

AU - Al-Garni, Ahmed Z.

AU - Sahin, Ahmet Z.

AU - Al-Qutub, Amro M.

PY - 1997

Y1 - 1997

N2 - In this paper, a comparative study is made for cooling aerospace plane, using liquid HZ, NHs, and Kr. The study includes the cooling for the stagnation point, the leading edges for wings, engine and other parts of the aerospace plane that are close to the leading edges. Laminar case for the stagnation point and both laminar and turbulent cases for the leading edge heating have been considered. The amount of heat rate (total, radiative and convective) and the mass of liquid coolant needed for cooling are calculated. A design of minimum inlet-outlet areas for the amount of liquid needed for cooling, is made with the consideration of the coolant's physical constraints in liquids and gaseous states. When compared to the other coolants, hydrogen is found to be the superior candidate for cooling aerospace plane.

AB - In this paper, a comparative study is made for cooling aerospace plane, using liquid HZ, NHs, and Kr. The study includes the cooling for the stagnation point, the leading edges for wings, engine and other parts of the aerospace plane that are close to the leading edges. Laminar case for the stagnation point and both laminar and turbulent cases for the leading edge heating have been considered. The amount of heat rate (total, radiative and convective) and the mass of liquid coolant needed for cooling are calculated. A design of minimum inlet-outlet areas for the amount of liquid needed for cooling, is made with the consideration of the coolant's physical constraints in liquids and gaseous states. When compared to the other coolants, hydrogen is found to be the superior candidate for cooling aerospace plane.

UR - https://www.scopus.com/pages/publications/84964018942

M3 - Paper

AN - SCOPUS:84964018942

T2 - 32nd Thermophysics Conference, 1997

Y2 - 23 June 1997 through 25 June 1997

ER -

Cooling aerospace plane using hydrogen, ammonia and kripton

Özet

???event.eventtypes.event.conference???

Bibliyografik not

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