Temperature and flow measurements on near-freezing aviation fuels in a wing-tank model
- Author
- Stockemer, F. J.
- Published
- JAN 1, 1980.
- Physical Description
- 1 electronic document
- Additional Creators
- Friedman, R.
Online Version
- hdl.handle.net , Connect to this object online.
- Restrictions on Access
- Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access - Summary
- Freezing behavior, pumpability, and temperature profiles for aviation turbine fuels were measured in a 190-liter tank chilled to simulate internal temperature gradients encountered in commercial airplane wing tanks. When the bulk of the fuel was above the specification freezing point, pumpout of the fuel removed all fuel except a layer adhering to the bottom chilled surfaces, and the unpumpable fraction depended on the fuel temperature near these surfaces. When the bulk of the fuel was at or below the freezing point, pumpout ceased when solids blocked the pump inlet, and the unpumpable fraction depended on the overall average temperature.
- Other Subject(s)
- Collection
- NASA Technical Reports Server (NTRS) Collection.
- Note
- Document ID: 19800005013.
Accession ID: 80N13268.
E-156.
NASA-TM-79285.
Intern. Gas Turbine Conf.; 9-13 Mar. 1980; New Orleans. - Terms of Use and Reproduction
- No Copyright.
View MARC record | catkey: 15723995