By J. Mattingly, H. von Ohain
This article offers a whole advent to gasoline turbine and rocket propulsion for aerospace and mechanical engineers. development at the very profitable Elements of gasoline Turbine Propulsion, textbook assurance has been increased to incorporate rocket propulsion and the fabric on gasoline dynamics has been dramatically more desirable. The textual content is split into 4 components: uncomplicated ideas and gasoline dynamics; research of rocket propulsion platforms; parametric (design element) and function (off-design) research of air respiring propulsion platforms; and research and layout of significant fuel turbine engine elements (fans, compressors, generators, inlets, nozzles, major burners, and afterburners).
Design suggestions are brought early (aircraft and rocket functionality in an introductory bankruptcy) and built-in all through. Written with huge pupil enter at the layout of the publication, the booklet builds upon definitions and progressively develops the thermodynamics, gasoline dynamics, rocket engine research, and fuel turbine engine rules. The e-book comprises over a hundred labored examples and various homework difficulties so recommendations are utilized once they are brought. Over six hundred illustrations and images express easy suggestions, tendencies, and layout examples.
Eight laptop courses accompany the textual content, which permit for quick calculation of tendencies, “what if” questions, conceptual layout, homework difficulties, and homework verification. The software program runs within the home windows working process on PC-compatible structures.
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Additional info for Elements of Propulsion: Gas Turbines and Rockets (Aiaa Education Series)
Afterburners . . . . . . . . . . . . . . . . . . Problems . . . . . . . . . . . . . . . . . . . 685 499 524 ........................... 685 685 686 695 726 744 757 769 779 A p p e n d i x A. Altitude Tables . . . . . . . . . . . . . . 785 A p p e n d i x B. Gas Turbine E n g i n e D a t a . . . . . . . . . . 793 A p p e n d i x C. D a t a for S o m e L i q u i d - P r o p e l l a n t R o c k e t E n g i n e s .
8521 x 10 - 2 slug 1 slug = 1 lbf. 38 k g / m 3 1 N = 1 kg. 448 N 1 J = 1 N. m = lkg. 16 ft. 23884 kcal 1 W = 1 J / s -- I k g . 696 lb/in. 2 i n H 2 0 1 ksi = 1000 psi 1 m m H g = 0 . 4299 B t u / l b m 1 k J / ( k g . 23884 B t u / ( l b m . 3 Operational Envelopes and Standard Atmosphere Each engine type will operate only within a certain range of altitudes and Mach numbers (velocities). Similar limitations in velocity and altitude exist for airframes. It is necessary, therefore, to match airframe and propulsion system capabilities.
C o m p r e s s i b l e Flow Properties . . . . . . . . . . . . . O n e - D i m e n s i o n a l G a s D y n a m i c s - - F i n i t e Control Volume A n a l y s i s a n d the H - K D i a g r a m . . . . . . . . . . . . N o z z l e D e s i g n a n d N o z z l e Operating Characteristics . . . . . O n e - D i m e n s i o n a l G a s D y n a m i c s - - D i f f e r e n t i a l Control Volume Analysis ................................. C h e m i c a l Reactions . . .