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NASA-TR-D-860
Analysis of cooling limitations and effect of engine-cooling improvements on level-flight cruising performance of four-engine heavy bombe
Year: 1946
Abstract: The 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.
Subject: AIR COOLING
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:57:31Z | |
| date available | 2017-09-04T15:57:31Z | |
| date copyright | 01/01/1946 | |
| date issued | 1946 | |
| identifier other | RAPNEEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/60820 | |
| description abstract | The 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. | |
| language | English | |
| title | NASA-TR-D-860 | num |
| title | Analysis of cooling limitations and effect of engine-cooling improvements on level-flight cruising performance of four-engine heavy bombe | en |
| type | standard | |
| page | 13 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1946 | |
| contenttype | fulltext | |
| subject keywords | AIR COOLING | |
| subject keywords | AIRCRAFT ENGINES | |
| subject keywords | AIRCRAFT PERFORMANCE | |
| subject keywords | BAFFLES | |
| subject keywords | BOMBER AIRCRAFT | |
| subject keywords | COOLING SYSTEMS | |
| subject keywords | CRUISING FLIGHT | |
| subject keywords | CYLINDERS | |
| subject keywords | FUEL INJECTION | |
| subject keywords | HORIZONTAL FLIGHT | |
| subject keywords | IMPELLERS | |
| subject keywords | INTERNAL COMBUSTION ENGINES | |
| subject keywords | PRESSURE DROP | |
| subject keywords | VALVES |