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Force and Pressure-Distribution Investigation to High Angles of Attack on All-Movable Triangular and Rectangular Wings in Combination With a Body at Supersonic Speeds
Force and pressure distribution studies to high angles of attack on all-movable triangular and rectangular wings in combination with body at supersonic speeds. The ranges of aspect ratios were, for the triangular wings, 3/8 to 4, and for the rectangular wings, 1 to 3.
Date:
July 10, 1956
Creator:
Hill, William A., Jr. & Kaattari, George E.
System:
The UNT Digital Library
The Use of Area Suction for Improving the Longitudinal Characteristics of a Thin Unswept Wing-Fuselage Model With Leading- and Trailing-Edge Flaps
"An investigation was conducted to determine the effect of porous area suction applied to the knees of full-span leading-edge and part-span trailing-edge flaps installed on an unswept-wing airplane model" (p. 1). The results obtained from an angle of attack of 0 degrees and greater than 0 degrees are compared. The effect of deflection, suction requirements, and stability characteristics are described.
Date:
July 10, 1956
Creator:
Koenig, David G.
System:
The UNT Digital Library
Static-thrust characteristics of the NACA 8.75-(5)(05)-037 dual-rotation propeller
Report presenting the static-thrust characteristics of the NACA 8.75-(5)(05)-037 dual-rotation propeller with six and eight blades as obtained on the static test stand in the course of an investigation set up primarily for studying blade vibratory stresses. Force data were obtained for a blade-angle range measured at the 0.75 radial station on the front propeller. Results regarding the effect of tip Mach number, effect of number of blades, and effect of blade angle are provided.
Date:
July 10, 1956
Creator:
Norton, Harry T., Jr.
System:
The UNT Digital Library
Free-Flight Aerodynamic-Heating Data to Mach Number 10.4 for a Modified Von Karman Nose Shape
Report presenting aerodynamic-heating data obtained on a modified-fineness-ratio-5.0 Von Karman nose shape at free-stream Mach numbers up to 10.4 with a rocket-propelled model. Transient skin temperatures were measured on the nose, and a maximum temperature of 1,663 degrees R was measured after maximum Mach number was obtained.
Date:
July 10, 1956
Creator:
Bland, William M., Jr. & Collie, Katherine A.
System:
The UNT Digital Library