The turboengine, turborocket and turboramjet engine were compared for the propulsion of flying devices with large flying range in the Mach number range between 2 and 4. Specific momentum, thrust characteristics, and air resistance were considered. It is shown that the turboengine is the most favorable type of propulsion for aircraft for Mach numbers of up to 3.5. Above this value, the turboramjet engine is the most favorable, and the turborocket interesting due to its high thrust density and in spite of its high specific momentum. For the turborocket, questions with respect to the gas generator, the turbine operation, the exhaust composition, and the exhaust mixture have to be investigated. For missiles, the turboramjet engine and the turborocket are favorable from a Mach number of 2 to 2.5.
Vergleich von Turbotriebwerk, Turborakete und Staustrahltriebwerk als Antrieb bei Grossen Reichweiten und Hohen Machzahlen (Comparison of Turboengine, Turborocket, and Turbojet Engine as Propulsion for Long Range and High Mach Numbers)
1976
29 pages
Report
No indication
English
Engineering Index Backfile | 1964
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