NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Analysis of cooling limitations and effect of engine-cooling improvements on level-flight cruising performance of four-engine heavy bomberThe NACA has developed means, including an injection impeller and ducted head baffles, to improve the cooling characteristics of the 3350-cubic-inch-displacement radial engines installed in a four-engine heavy bomber. The improvements afforded proper cooling of the rear-row exhaust-valve seats for a wide range of cowl-flap angles, mixture strengths, and airplane speeds. The results of flight tests with this airplane are used as a basis for a study to determine the manner and the extent to which the airplane performance was limited by engine cooling. By means of this analysis for both the standard airplane and the airplane with engine-cooling modifications, comparison of the specific range at particular conditions and comparison of the cruising-performance limitations was made.
Document ID
19930091932
Document Type
Other
Authors
Marble, Frank E
Miller, Marlon A
Bell, E Barton
Date Acquired
September 6, 2013
Publication Date
January 1, 1946
Report/Patent Number
NACA-TR-860
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Available Downloads

NameType 19930091932.pdf STI