By Loren E. Bollinger, Martin Goldsmith, Alexis W. Lemmon Jr. (Eds.)

Show description

Read Online or Download Liquid Rockets and Propellants PDF

Best aeronautics & astronautics books

Aircraft performance

This publication describes the rules and equations required for comparing the functionality of an plane. After introductory chapters at the surroundings, simple flight concept, and drag, the booklet is going directly to ponder intimately the estimation of mountain climbing functionality, the suitable features of energy vegetation, takeoff and touchdown functionality, variety, and turning functionality.

Unmanned Air Systems: UAV Design, Development and Deployment

Unmanned plane structures gives you a far wanted creation to UAV procedure expertise, taking an built-in strategy that avoids compartmentalising the topic. prepared in 4 sections, elements 1-3 learn the best way a number of engineering disciplines have an effect on the layout, improvement and deployment of UAS.

The Aviation Maintenance Technician Handbook—Airframe (FAA-H-8083-31)

The Aviation upkeep Technician Handbook—Airframe (FAA-H-8083-31) is one in every of a chain of 3 handbooks for individuals getting ready for certification as an airframe or powerplant mechanic. it truly is meant that this instruction manual give you the simple details on ideas, basics, and technical approaches within the material components on the subject of the airframe score.

Extra resources for Liquid Rockets and Propellants

Sample text

Purchased from American Institute of Aeronautics and Astronautics LIQUID ROCKETS AND PROPELLANTS THE FULL-SCALE DIFFUSER The nominal diametrical scale factor between the model diffuser and the full-scale diffuser is ten. The fullscale diffuser is modelled after configuration 2 with some minor alterations 0 A sketch of the vacuum chamber,, which contains the engine3 and the diffuser is shown in Fig. 27 0 Note that the engine and the diffuser are not mechanically coupled but rather that the diffuser is attached to the vacuum chamber.

E. , with D^ = D e> and these tests indicated that there was a strong tendency for the nozzle flow to separate near the nozzle exit plane, even when the diffuser was started. This effect was sometimes noticed for constantarea-duct type diffusers when Dk/D e = 1. 0 as well as for second-throat type diffusers. The presence of a cavity with Dfo > De eliminated this problem, A limited number of tests were made with configurations 2 and 3 using a reduced cavity diameter, with Dk/D e = 1. 065 rather than the value listed in Fig.

40 Using a vacuum tank plus manifold and piping volume of approximately 4. 25 ft Purchased from American Institute of Aeronautics and Astronautics LIQUID ROCKETS AND PROPELLANTS Table 4. Results obtained with constant-area-duct type diffusers withy ~ 1. 6 16. 0516 1. 110 5. 1 20. 0626 1. 4 19. 0626 1. 0626 (1) Using an approximate one-dimensional flow theory. These parameters are a function of 7, € , and A/A e only. Table 5. Best results obtained with a vacuum-tank start using configuration 2 with y ~ 1.

Download PDF sample

Rated 4.11 of 5 – based on 6 votes