Improvement of aileron effectiveness by the prevention of air leakage through the hinge gap as determined in flight (open access)

Improvement of aileron effectiveness by the prevention of air leakage through the hinge gap as determined in flight

"A flight investigation was made of the increase in effectiveness of ailerons that can be obtained by preventing flow of air through the wing at the hinges and of the possibility of reducing the aileron operating force by replacing ailerons having normal open hinge gaps with narrower but equally effective ailerons having sealed hinge gaps. Tests were made with a Fairchild 22 airplane with two sizes of plain unbalanced ailerons, one set having a chord equal to 0.18c, and the other chord equal to 0.09c. The results of the investigation show that improvement of the lateral-control effectiveness is obtained by completely preventing the flow of air through the wing at the hinge axis of conventional ailerons" (p. 1).
Date: January 1938
Creator: Soulé, H. A. & Gracey, W.
System: The UNT Digital Library
The N.A.C.A. Optical Engine Indicator (open access)

The N.A.C.A. Optical Engine Indicator

An optically recording engine-pressure indicator of simple and rugged construction has been developed for use in high-pressure and high temperature combustion research. This instrument is of the diaphragm type and has a natural frequency of about 10,000 cycles per second.
Date: January 1938
Creator: Tozier, Robert E.
System: The UNT Digital Library
Spinning characteristics of wings 5: N.A.C.A. 0009, 23018, and 6718 monoplane wings (open access)

Spinning characteristics of wings 5: N.A.C.A. 0009, 23018, and 6718 monoplane wings

Three rectangular monoplane wings having rounded tips were tested on the N.A.C.A. spinning balance in the 5-foot vertical wind tunnel. The airfoil sections used were the N.A.C.A. 0009, 23018, and 6718. The aerodynamic characteristics of the models and a prediction of the angles of sideslip for steady spins are given. There is included an estimate of the yawing moment that must be furnished by parts of the airplane to balance the inertia couples and wing yawing moments for spinning equilibrium. The predicted angles of sideslip and yawing moments required for spinning equilibrium for a Clark Y wing with the same form are included for comparison.
Date: January 1938
Creator: Bamber, M. J. & House, R. O.
System: The UNT Digital Library
Wind-Tunnel Tests of Carburetor-Intake Rams (open access)

Wind-Tunnel Tests of Carburetor-Intake Rams

"An investigation was conducted in the NACA 20-foot wind tunnel of the ramming effect of three general types of carburetor intake rams for radial engines, namely, the internal constant area type, the external constant area type, and the external expanding type. The rams were installed on a radial air- cooled engine nacelle, and tests were made with and without the propeller operating. The results indicated that the external types having entrances near the front of the engine cowling gave the greatest ramming effect" (p. 1).
Date: January 1938
Creator: Highley, Frank H.
System: The UNT Digital Library