Investigation of Operating Characteristics of an Engine Equipped with Modifications to Eliminate Fuel-Evaporation Icing Page: 4 of 21
This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided to UNT Digital Library by the UNT Libraries Government Documents Department.
Extracted Text
The following text was automatically extracted from the image on this page using optical character recognition software:
NACA RM No. E6LO4a
Ground and flight tests. - A detailed description of the instal-
lation and instrumentation of the V-type, liquid-cooled aircraft
engine used in the twin-engine fighter airplane for a previous inves-
tigation of induction-system icing is given in reference 3 and much
of the same instrumentation and equipment was used for this investi-
gation. In addition, thermocouples were installed in the cylinder
heads approximately three-sixteenths inch from the inner surface of
the combustion chamber between the exhaust-valve seats. (See fig. 3,)
Instrumentation was provided to measure free-air temperature,
pressure altitude, and airspeed. For the engine, instrumentation was
installed to measure engine speed, carburetor-inlet-air temperature
and pressure, manifold mixture temperature and pressure, cylinder-
head temperatures, compensated and uncompensated metering suction
differential pressure, mixture setting, coolant temperature, and
cooling-air temperature.
Pressures and temperatures were recorded by standard NACA pres-
sure recorders and a recording potentiometer, respectively.
The uncompensated metering suction differential pressure of the
specially calibrated carburetor was used to determine the charge-air
flow through the carburetor, and the compensated metering suction
differential pressure to determine fuel flow. A special mixture-
control disk was installed on the carburetor to obtain accurate fuel-
air-ratio control and a differential-pressure gage was installed in
the cockpit to indicate the compensated metering suction differential
and thus enable the pilot to set desired fuel-air ratios.
Prior to flight, a ground check was made of engine performance
with spinner fuel injection throughout the power range from idling
to take-off power in order to insure smooth and detonation-free
operation.
Comparative flights were made at an altitude of approximately
10,000 feet with the spinner fuel-injection system and the standard
system. The drilled-inducer fuel-injection system was not investi-
gated in flight.
The program included flights at low-cruise and high-cruise power
conditions with varying fuel-air ratio and flights at various powers
up to rated engine power with specified fuel-air ratios. Ease of
starting and acceleration were noted throughout the investigation.
1
Data were recorded for each 3--minute period after conditions were
stabilized,3
Upcoming Pages
Here’s what’s next.
Search Inside
This report can be searched. Note: Results may vary based on the legibility of text within the document.
Tools / Downloads
Get a copy of this page or view the extracted text.
Citing and Sharing
Basic information for referencing this web page. We also provide extended guidance on usage rights, references, copying or embedding.
Reference the current page of this Report.
Mulholland, Donald R. & Zlotowski, Edward D. Investigation of Operating Characteristics of an Engine Equipped with Modifications to Eliminate Fuel-Evaporation Icing, report, December 24, 1946; (https://digital.library.unt.edu/ark:/67531/metadc64024/m1/4/: accessed April 26, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.