Serial/Series Title

Transonic Aerodynamic Characteristics of a 1/15-Scale Model of the Convair B-58 Airplane (open access)

Transonic Aerodynamic Characteristics of a 1/15-Scale Model of the Convair B-58 Airplane

Report presenting an investigation of a model of the Convair B-58 airplane weapons system in the transonic tunnel for a range of Mach and Reynolds numbers. Results regarding drag characteristics, lift-curve slope, and longitudinal stability parameter are provided.
Date: October 19, 1956
Creator: Swihart, John M.
System: The UNT Digital Library
An Experimental Investigation at Large Scale of Several Configurations of an NACA Submerged Air Intake (open access)

An Experimental Investigation at Large Scale of Several Configurations of an NACA Submerged Air Intake

"An investigation of an NACA submerged air intake was conducted on a full-scale model of a fighter-type airplane. This study was made to determine the large-scale aerodynamic characteristics of a submerged air intake proposed as the result of small-scale tests and to compare the pressure-recovery characteristics of the large- and small-scale installations. Additional tests were made to determine the effect on pressure recovery of a systematic variation of ramp divergence" (p. 1).
Date: October 19, 1948
Creator: Martin, Norman J. & Holzhauser, Curt A.
System: The UNT Digital Library
Investigation at a Mach Number of 1.93 to Determine Lift, Drag, Pitching-Moment, and Average Downwash Characteristics for Several Missile Configurations Having Rectangular Wings and Tails of Various Spans (open access)

Investigation at a Mach Number of 1.93 to Determine Lift, Drag, Pitching-Moment, and Average Downwash Characteristics for Several Missile Configurations Having Rectangular Wings and Tails of Various Spans

Memorandum presenting an investigation made at a Mach number of 1.93 to determine lift, drag, pitching-moment, and average downwash characteristics of several missile configurations. Five configurations with rectangular wings and tails of various spans were tested; each of the configurations had two locations of the wing relative to the tail.
Date: October 19, 1950
Creator: Grigsby, Carl E.
System: The UNT Digital Library
Some considerations of the influence of body cross-sectional shape on the lifting efficiency of wing-body combinations at supersonic speeds (open access)

Some considerations of the influence of body cross-sectional shape on the lifting efficiency of wing-body combinations at supersonic speeds

From Summary: "Linearized theory is used to estimate the order of magnitude of the beneficial effects that can be obtained by shaping the body of a wing-body configuration to generate lift indirectly at supersonic speeds. The analysis applies to a class of wing-body configurations which is believed to exhibit the essential features of this type of interference; the body is cylindrical upstream of a wing which has supersonic edges and the parts of the body above and below the wing are each semicircular and of different radii. Calculations are presented for a Mach number of the square root of 2 for a particular family of bodies and a sonic-edge delta wing."
Date: October 19, 1956
Creator: Klunker, E. B. & Harder, Keith C.
System: The UNT Digital Library
Effect of Camber on the Drag of a Body of Revolution (open access)

Effect of Camber on the Drag of a Body of Revolution

Memorandum presenting an investigation to determine the effect of camber on the drag of a body of revolution. The drag of a straight body of revolution was measured and compared with that of a body that differed only in that its center line was cambered in the form of a parabola. The addition of a small amount of camber was found to cause very little increase in the minimum foredrag of the model tested.
Date: October 19, 1956
Creator: Dickey, Robert R.
System: The UNT Digital Library
Effect of Blade-Section Camber on Aerodynamic Characteristics of Full-Scale Supersonic-Type Propellers at Mach Numbers to 1.04 (open access)

Effect of Blade-Section Camber on Aerodynamic Characteristics of Full-Scale Supersonic-Type Propellers at Mach Numbers to 1.04

Report presenting an investigation of the aerodynamic characteristics of two full-scale supersonic propellers with a 6000-horsepower propeller dynamometer. One propeller had symmetrical NACA 16-series airfoil sections and the other was similar except for a blade-section camber and a slight difference in pitch distribution.
Date: October 19, 1956
Creator: Maynard, Julian D.; Swihart, John M. & Norton, Harry T., Jr.
System: The UNT Digital Library
Theoretical Investigation of a Proportional-Plus-Flicker Automatic Pilot (open access)

Theoretical Investigation of a Proportional-Plus-Flicker Automatic Pilot

"The proportional-plus-flicker automatic pilot operates by a nonlinear principle whereby a fast-acting flicker servomotor response is combined with a low-speed proportional servomotor response for the purpose of obtaining supersonic stability and control. Essentially, the autopilot maintains a zero reference about which the output is proportional to the input. However, a flicker response overrides this proportional response at a fixed angle of gimbal displacement on either side of the zero gyroscope reference" (p. 1).
Date: October 19, 1950
Creator: Seaberg, Ernest C.
System: The UNT Digital Library
Transonic Aerodynamic Characteristics of a 1/15-Scale Model of the Convair B-58 Airplane (open access)

Transonic Aerodynamic Characteristics of a 1/15-Scale Model of the Convair B-58 Airplane

Report presenting an investigation of a model of the Convair B-58 airplane weapons system, including under conditions of long-range subsonic cruise and a supersonic dash. Results regarding drag characteristics, lift-curve slope, and longitudinal stability parameter are provided.
Date: October 19, 1956
Creator: Swihart, John M.
System: The UNT Digital Library