Flight and Test-Stand Investigation of High-Performance Fuels in Double- Row Radial Air-Cooled Engines. 1 - Determination of Cooling Characteristics of Flight Engine
Abstract
The cooling characteristics of a 14-cylinder double-row radial air-cooled engine installed in a four-engine airplane have been investigated. All cooling data were obtained during a single flight at a pressure altitude of 7000 feet. The investigation was conducted in such a manner that the effects of charge-air flow, cooling-air pressure drop, and fuel-air ratio on the engine cooling characteristics could be separately investigated. The flight cooling data were correlated by the method developed in NACA Report No. 612. Predictions of maximum engine temperatures and cooling-limited engine performance were then made from the correlation results for normal flight conditions of the airplane. Maximum temperatures at the rear middle of the cylinder barrel were greater than 350 deg F for all conditions investigated. Temperature-limited performance was predicted for head limits of 400 and 450 deg F. The temperature-limited performance predicted for 400 deg F and cowl flaps one-third open agreed very well with the manufacturer's specified maximum cruising power in combination with the carburetor-metering characteristic curve.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1944
- Accession Number
- ADB807261
Entities
People
- C. C. Blackman
- H. J. White
- P. C. Pragliola
Organizations
- National Advisory Committee for Aeronautics