Exhaust-Stack Nozzle Area and Shape for Individual Cylinder Exhaust-Gas Jet-Propulsion System
Abstract
An investigation was conducted on the effect of exhaust-stack nozzle area, shape, and length on engine power, jet thrust, and gain in net thrust (engine propeller plus jet). Single-cylinder engine data were obtained using three straight stacks 25, 44, and 108 inches in length; and S-shaped stack, and 90 degree bend, a 180 degree bend, and a short straight stack having a closed branch faired into it. Each stack was fitted with nozzles varying in exit area from 0.91 square inch to the unrestricted area of the stack of 4.20 square inches. The engine was generally operated over a range of engine speeds from 1300 to 2100 rpm, inlet-manifold pressures from 22 to 36 inches of mercury absolute, exhaust pressures from 12 to 30 inches of mercury absolute, and a fuel-air ratio of 0.08. The loss in engine power, the just thrust, and the gain in net thrust are correlated in terms of several simple parameters. An example is given for determining the optimum nozzle ares and the over-all net thrust.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1943
- Accession Number
- ADA800898
Entities
People
- Benjamin Pinkel
- Fred Voss
- L. Richard Turner
- Leroy V. Humble
Organizations
- Langley Research Center