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Low-Speed Investigation of a Small Triangular Wing of Aspect Ratio 2.0 2: Flaps on Flat-Plate Models
Memorandum presenting low-speed wind-tunnel tests made of flat-plate wings with an aspect ratio of 2.0 and their leading edges swept back 63.4 degrees. Both plain and split flaps of several plan forms were investigated to provide qualitative information as to the relative merits of these flaps. The constant-chord flap was found to be the most effective and a skewed wing-tip flap the least effective.
Date:
August 9, 1948
Creator:
Rose, Leonard M.
System:
The UNT Digital Library
Pressure Recovery at Supersonic Speeds Through Annular Duct Inlets Situated in a Region of Appreciable Boundary Layer 2: Effect of an Oblique Shock Wave Immediately Ahead of the Inlet
Memorandum presenting an investigation of a model with a ramp that produced an oblique shock wave in front of an annular duct inlet, which was tested at Mach numbers between 1.36 and 2.01 to determine the effect of reducing the entrance Mach number on the total-pressure recovery after diffusion. The results showed that the maximum total-pressure recovery of the model investigated was considerably improved through the addition of a ramp.
Date:
August 9, 1948
Creator:
Brajnikoff, George B.
System:
The UNT Digital Library
Redox Equipment Testing Report No. 4
A report which covers progress on the testing of the General Engineering and Consulting Laboratory Turbine Pump No. 1 from June 16, 1948, to July 31, 1948.
Date:
August 9, 1948
Creator:
Cooper, V. R. & Allen, A. W.
System:
The UNT Digital Library