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April 6, 2017 | Aerospace | By admin | 0 Comments

By J.M.Bruce

;de Havilland D.H.9[Aircraft Profile 062] КНИГИ ;ВОЕННАЯ ИСТОРИЯ Название:de Havilland D.H.9 Автор: J.M.Bruce Серия: airplane Profile 062 Издательство: Profile courses Ltd Страниц:12 Формат: PDF в rarЯзык: английский Размер: 4.51 Мб Для сайта: Мир книгВ 1917 г. чтобы увеличить боевую мощь авиации Великобритании, потребовался новый бомбардировщик с большим радиусом действия, чем у D.H.4. Прототип самолета Airco D.H.9 был создан в результате модификации модели D.H.4. Он сохранил такие же крылья, хвостовое оперение и похожее шасси, но фюзеляж имел носовую часть более обтекаемой формы, а кабина пилота располагалась непосредственно над задней кромкой нижнего крыла. ifolder.ru.com zero

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This will be treated in two parts. Part I offers a status quo report on current calculation methods, and compiles and explains briefly the most important data on selected prominent rocket engines. Starting from the phenomenology of the dynamical and physico-chemical conversion processes in the fuel-oxidizer fluid mixture and in the burned gases, the ideal thermodynamic comparative process is then derived - as a defined sequential change of states in the system. In order to render this comparative process readily understandable, it is first applied to an appropriate model gas using algebraic equations for all relevant parameters.

One need not exaggerate like rocket pioneer R. " Yet a transparent, politically attainable, scientifically acceptable and quantitatively definable project is only possible when it is based on solid fundamentals of a few elementary design aspects. O. RUPPE (1985) has provided an exemplary illustration. In space technology and some other areas of so-called high-tech, the design optimization of a concrete propulsion project is usually undertaken with the help of the NASA-Lewis Code. Using such optimization -55- procedures D.

All other design phases, though of great importance, cannot yield great efficiency improvements. 807). The setting of the task is equivalent with the representation of all properties of state of the system (= given model gas) under the given set of constraints for the sequence of states £, ~, I and £ formulated with the aid of algebraic equations. Table 4 is a compilation of the relationships for solving this problem completely. These relationships will be described in greater detail below. The compilation should make clear that, for the known geometric parameters AT' Q and 0, the specification of the feed pressure PF already determines all other values of the steady isentropic flows with conversion processes.

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