Measurement of Air Flow Through an Aircraft Generator During Flight. Part 2 Analysis of Flight Test Data for F7F-3 Aircraft
Abstract
Although the rating of an electrical generator is a function of its electromagnetic design, the rating can be increased considerably by providing added means of heat dissipation, while still retaining the same size and weight in the generator. In aircraft installations this is usually accomplished by forcing an air blast through the generator, which thus makes its maximum safe rating a function of atmospheric ambient conditions, the particular installation and aircraft speed. Since adequate information was not available for accurately rating aircraft generators, this project was initiated to supply additional data in order that existing theoretical rating charts might be checked and extended. In addition, it was desired to obtain more accurate information on which to base the design of future air duct systems and aircraft generators as higher speeds and altitudes are reached, and to provide a system for checking the adequacy of a particular blast tube installation in new types of aircraft. In order to accomplish this an instrumentation system was needed which would measure the air flow through the generator during flight under varying conditions of altitude, air speed, inlet air temperature, and blast tube configuration. It had to be small and rugged enough to be installed in an aircraft, should not change appreciably the air flow through the generator, and should be applicable to a large number of installations. An instrumentation system (1), which met these requirements by measuring the static air pressure drop across a previously calibrated generator, was installed in an F7F-3 aircraft (Bureau of Aeronautics No. 80430) and provided the data for this report.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 12, 1952
- Accession Number
- AD1218921
Entities
People
- Daniel J. Friedman
- J. M. Marzolf
Organizations
- United States Naval Research Laboratory