Study of Fuels in the Aeroresonator Motor
Abstract
As a preliminary to fuel studies, performance of a reference fuel (62 octane gasoline) has been studied in six inch aeroresonators. While no attempt has been made to depart from conventional motor design, dimensions have been varied in the design factors of chamber and tailpipe length, tailpipe diameter, valve box area and "throat" shape and area. Air intake valve tensions are also discussed. Measurements taken over the range of operating fuel values include thrust, air consumption, frequency and temperature. The minimum specific fuel consumption obtained was 2.64 lbs/hr/lb. (specific impulse = 1360) and the maximum thrust 33.5 lbs.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1946
- Accession Number
- AD1196232
Entities
People
- C. G. Lindquist
- D. S. Burgess
- K. J. Hayes
- S. H. Smith
- T. K. Rice
Organizations
- United States Naval Research Laboratory