Scramjet motorunun değişen irtifa ve Mach sayılarında incelenmesi.

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Bibliographic Details
Title:	Scramjet motorunun değişen irtifa ve Mach sayılarında incelenmesi.
Alternate Title:	Investigation of a scramjet engine at varying altitudes and Mach numbers.
Authors:	Turmuş, Ahmet^1,2 91220000062@ogrenci.ege.edu.tr, Özdamar, Aydoğan³ aydogan.ozdamar@ege.edu.tr
Source:	Journal of the Faculty of Engineering & Architecture of Gazi University / Gazi Üniversitesi Mühendislik Mimarlık Fakültesi Dergisi,. Mar2026, Vol. 41 Issue 1, p47-62. 16p.
Subjects:	Scramjet engines, Mach number, Hydrogen as fuel, Thermodynamics, Combustion efficiency, Fluid dynamics, Geopotential height
Abstract (English):	Scramjet, a type of airbreathing engine used in high-speed atmospheric flights in which the reactive fluid enters the combustion chamber at supersonic speeds, is of critical importance for hypersonic aerial vehicles. In this study, a scramjet engine with a rectangular cross-sectional area and a symmetric internal compression system, using hydrogen (H2) as fuel, is thermodynamically analyzed using analytical and numerical methods within the altitude range of 20-30 km and Mach number range of 5-8. The aim of the study is to determine the flow characteristics under different operating conditions and their effects on engine performance, and at the same time to evaluate the validity of the analytical approach based on ideal assumptions by comparing analytical and numerical results. The obtained results show that when the Mach number increases from 5 to 8, there is an approximately 50% decrease in total pressure recovery (TPR). In addition, the TPR values obtained by the analytical method are approximately 25% higher than the numerical results. This discrepancy arises from the analytical model's neglect of realistic losses. Another important result is that at speeds below Mach 6, the transition of the flow at the combustor inlet to the subsonic regime leads to a choking risk in the engine. [ABSTRACT FROM AUTHOR]
Abstract (Turkish):	Yüksek hızlı atmosferik uçuşlarda kullanılan ve yakıcı akışkanın yanma odasına süpersonik hızlarda girdiği bir hava soluyan motor türü olan scramjet, hipersonik hava araçları için kritik öneme sahiptir. Bu çalışmada, dikdörtgen kesit alanına ve simetrik iç sıkıştırma sistemine sahip, yanıcı olarak hidrojen (H2) kullanan bir scramjet motoru; 20-30 km irtifa ve 5-8 Mach sayısı aralığında analitik ve nümerik yöntemlerle termodinamik açıdan incelenmiştir. Çalışmanın amacı, farklı çalışma koşullarındaki akış özelliklerini ve bu özelliklerin motor performansına etkisini belirlemek, aynı zamanda analitik ve nümerik sonuçları karşılaştırarak ideal varsayımlara dayanan analitik yaklaşımın geçerliliğini değerlendirmektir. Elde edilen sonuçlar, Mach sayısının 5'ten 8'e çıkması durumunda toplam basınç geri kazanımında (TPR) yaklaşık %50 azalma olduğunu göstermektedir. Ayrıca, analitik yöntemle elde edilen TPR değerleri, nümerik sonuçlara göre yaklaşık %25 daha yüksek olmaktadır. Bu fark, analitik modelin gerçekçi kayıpları ihmal etmesinden kaynaklanmaktadır. Bir diğer önemli sonuç, 6 Mach altındaki hızlarda, yanma odası girişindeki akışın sesaltı rejime geçmesiyle motorda boğulma riskinin oluşmasıdır. [ABSTRACT FROM AUTHOR]
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Database:	Engineering Source

Description
Abstract:	Scramjet, a type of airbreathing engine used in high-speed atmospheric flights in which the reactive fluid enters the combustion chamber at supersonic speeds, is of critical importance for hypersonic aerial vehicles. In this study, a scramjet engine with a rectangular cross-sectional area and a symmetric internal compression system, using hydrogen (H2) as fuel, is thermodynamically analyzed using analytical and numerical methods within the altitude range of 20-30 km and Mach number range of 5-8. The aim of the study is to determine the flow characteristics under different operating conditions and their effects on engine performance, and at the same time to evaluate the validity of the analytical approach based on ideal assumptions by comparing analytical and numerical results. The obtained results show that when the Mach number increases from 5 to 8, there is an approximately 50% decrease in total pressure recovery (TPR). In addition, the TPR values obtained by the analytical method are approximately 25% higher than the numerical results. This discrepancy arises from the analytical model's neglect of realistic losses. Another important result is that at speeds below Mach 6, the transition of the flow at the combustor inlet to the subsonic regime leads to a choking risk in the engine. [ABSTRACT FROM AUTHOR]
ISSN:	13001884
DOI:	10.17341/gazimmfd.1676375