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Tests of NACA 65(216)-420 and 66(218)-420 Airfoils at High Speeds
Report presenting wind tunnel tests of NACA 65(216)-420 and 66(218)-420 airfoils at speeds up to and slightly above the critical. Section coefficients of lift, drag, and pitching-moment and extensive pressure-distribution data are presented. The critical speed for these airfoils at their design life coefficient of 0.4 is shown to be about 460 miles per hour at seal level and about 415 miles per hour at 25,000 feet altitude.
Date:
April 10, 1944
Creator:
Anderson, Joseph L.
System:
The UNT Digital Library
The Effect of Compression Ratio on Knock Limits of High-Performance Fuels in a CFR Engine 3: Blends of 2,3-Dimethylpentane With 28-R
Report discussing the knock-limited performance of blends of 2,3-dimethylpentane and 23-R fuel in an F-4 engine at three sets of conditions and three compression ratios. The knock-limited performance of 2,3-dimethylpentane has about the same sensitivity to compression ratio and inlet-air temperature as 28-R fuel.
Date:
February 10, 1945
Creator:
Alquist, Henry E. & Tower, Leonard K.
System:
The UNT Digital Library
Investigation of Slipstream Effects on a Wing-Inlet Oil-Cooler Ducting System of a Twin-Engine Airplane in the Ames 40- by 80-Foot Wind Tunnel
Report discussing an investigation of wing-inlet oil-cooler ducts on a twin-engine airplane to determine internal and external-flow characteristics of the ducting installation. Testing was also performed on revised inlets to attempt to develop a ducting system with low overall losses throughout the operating range.
Date:
March 10, 1945
Creator:
Chapman, Dean R.
System:
The UNT Digital Library