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Analysis of cooling limitations and effect of engine-cooling improvements on level-flight cruising performance of four-engine heavy bombe

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T15:57:31Z
date available2017-09-04T15:57:31Z
date copyright01/01/1946
date issued1946
identifier otherRAPNEEAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/60820
description abstractThe 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.
languageEnglish
titleNASA-TR-D-860num
titleAnalysis of cooling limitations and effect of engine-cooling improvements on level-flight cruising performance of four-engine heavy bombeen
typestandard
page13
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1946
contenttypefulltext
subject keywordsAIR COOLING
subject keywordsAIRCRAFT ENGINES
subject keywordsAIRCRAFT PERFORMANCE
subject keywordsBAFFLES
subject keywordsBOMBER AIRCRAFT
subject keywordsCOOLING SYSTEMS
subject keywordsCRUISING FLIGHT
subject keywordsCYLINDERS
subject keywordsFUEL INJECTION
subject keywordsHORIZONTAL FLIGHT
subject keywordsIMPELLERS
subject keywordsINTERNAL COMBUSTION ENGINES
subject keywordsPRESSURE DROP
subject keywordsVALVES


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