Flight and Test-Stand Investigation of High-Performance Fuels in Double-Row Radial Air-Cooled Engines 1: Determination of Cooling Characteristics of Flight Engine Page: 3 of 22
This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided to Digital Library by the UNT Libraries Government Documents Department.
The following text was automatically extracted from the image on this page using optical character recognition software:
NACA MR No. E4L20
is being conducted at the NACA Cleveland laboratory. The first phase
of the flight -pro am - the determination of cooling characteristics
of the engine - is presented herein. .A correlation of the cooling
characteristics is necessary in orde to compare the cooling-limited
power of the engine with the knock-limited power and thereby evaluate
A flight was made with a 14-cylinder double-row radial air-cooled
engine installed in a four-engine airplane at a pressure altitude of
7000 feet, low blower ratio, an engine speed of 2230 rpm, and a spark
advance of 250 B .T .C. The fuel was 28-R. The installation of cylinder
thermocouples and cooling-air pressure tubes conformed to current NACA
practice. The results obtained are described herein and a correlation
of the engine cooling data based on the method developed in reference 1
. EQUITM E AD IhSTHMETATIDN
The investigation was conducted with an R-1i 30-900 engine mounted
in the left inboard nacelle of a B-24D airplane shown in figure 1. The
engine is a 14-cylinder double-row radial air-cooled engine with a
normal rated power of 1100 brake horsepower at 2550 rma end take-off
power of 1200 brake horsepower at 2700 rpm. The test engine differs
from the engines which are standard equipment in the airplane in that
it is equipped with a single-stage, two-epeed .supercharger having a
low blower ratio of .7.15:1 and a high blower ratio of 8.47:1. A
manual control was installed for the waste gate of the turbosuper-
charger to provide better boost control. The engine was equipped with
a three-blade propeller and was fitted with a hydraulc torqueseter
having a gear ratio of 16:9. A PD-12F2-16 injection carburetor, pro-
vided with a special mixture-control plate, was used on the test engine.
The airplane was so equipped that all data could be recorded within
10 seconds after stabilization. A 100-tube liquid mancmeter and a
60-cell NACA recording manometer were utilized for measuring the engine
cooling-air pressure . The temperatures were indicated by mens of - -
two NACA recording galvanometers capable of recording 100 temperatures
within a 10-second period. The carburetor was calibrated in an air
box in order that the rate of air flow could be determined in flight
by measuring the carburetor-air metering pressures. The air-baox cal-
ibration was corrected for installation effect by a recalibration with
the carburetor on the engine in the airplane and all ducting in .
place. Fuel flows were manually recorded from a rotameter and were
Here’s what’s next.
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.
Blackman, Calvin C.; White, H. Jack & Pragliola, Philip C. Flight and Test-Stand Investigation of High-Performance Fuels in Double-Row Radial Air-Cooled Engines 1: Determination of Cooling Characteristics of Flight Engine, report, December 20, 1944; (https://digital.library.unt.edu/ark:/67531/metadc62522/m1/3/: accessed April 18, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.