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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Boundary-layer and stalling characteristics of the NACA 63-009 airfoil section

Boundary-layer and stalling characteristics of the NACA 63-009 airfoil section

Date: June 1, 1949
Creator: Gault, Donald E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : aerodynamic characteristics in sideslip of a large-scale model having a 63 degree swept-back vertical tail

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : aerodynamic characteristics in sideslip of a large-scale model having a 63 degree swept-back vertical tail

Date: October 7, 1949
Creator: Mccormack, Gerald M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic principles for the design of jet-engine induction systems

Aerodynamic principles for the design of jet-engine induction systems

Date: February 27, 1956
Creator: Davis, Wallace F & Scherrer, Richard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics at a Mach number of 1.53 including effect of small variations of sweep

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics at a Mach number of 1.53 including effect of small variations of sweep

Date: January 26, 1949
Creator: Madden, Robert T
Description: Measured values of lift, drag, and pitching moment at a Mach number of 1.53 and Reynolds numbers of 0.31, 0.62, and 0.84 million are presented for a wing-fuselage combination having a wing leading-edge sweep angle of 63 degrees, an aspect ratio of 3.42, a taper ratio of 0.25, and an NACA 64A006 section in the stream direction. Data are also presented for sweep angles of 57.0 degrees, 60.4 degrees, 67.0 degrees, and 69.9 degrees. The experimentally determined characteristics were less favorable than indicated by the linear theory but the experimental and theoretical trends with sweep were in good agreement. Boundary-layer-flow tests showed that laminar boundary-layer separation was the primary cause of the differences between experiment and theory.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics for symmetrical wing sections at high subsonic and moderate supersonic Mach numbers

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics for symmetrical wing sections at high subsonic and moderate supersonic Mach numbers

Date: July 7, 1949
Creator: Mas, Newton A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics throughout the subsonic speed range with the wing cambered and twisted for a uniform load at a lift coefficient of 0.25

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : characteristics throughout the subsonic speed range with the wing cambered and twisted for a uniform load at a lift coefficient of 0.25

Date: August 15, 1949
Creator: Jones, J Lloyd & Demele, Fred A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effect of Reynolds number at supersonic Mach numbers on the longitudinal characteristics of a wing twisted and cambered for uniform load

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effect of Reynolds number at supersonic Mach numbers on the longitudinal characteristics of a wing twisted and cambered for uniform load

Date: October 9, 1950
Creator: Heitmeyer, John C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effect of sideslip on aerodynamic characteristics at a Mach number of 1.4 with the wing twisted and cambered

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effect of sideslip on aerodynamic characteristics at a Mach number of 1.4 with the wing twisted and cambered

Date: September 29, 1950
Creator: Lessing, Henry C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effectiveness at supersonic speeds of a 30-percent chord, 50-percent semispan elevon as a lateral control device

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effectiveness at supersonic speeds of a 30-percent chord, 50-percent semispan elevon as a lateral control device

Date: January 18, 1951
Creator: Olson, Robert N & Mead, Merrill H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effectiveness of an elevon as a longitudinal control and the effects of camber and twist on the maximum lift-drag ratio at supersonic speeds

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effectiveness of an elevon as a longitudinal control and the effects of camber and twist on the maximum lift-drag ratio at supersonic speeds

Date: May 8, 1950
Creator: Olson, Robert N & Mead, Merrill H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effects of split flaps, elevons, and leading-edge devices at low speed

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effects of split flaps, elevons, and leading-edge devices at low speed

Date: May 19, 1949
Creator: Hopkins, Edward J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics including pressure distribution of a fuselage and three combinations of the fuselage with swept-back wings at high subsonic speeds

Aerodynamic characteristics including pressure distribution of a fuselage and three combinations of the fuselage with swept-back wings at high subsonic speeds

Date: February 6, 1951
Creator: Sutton, Fred B & Martin, Andrew
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics including scale effect of several wings and bodies alone and in combination at a Mach number of 1.53

Aerodynamic characteristics including scale effect of several wings and bodies alone and in combination at a Mach number of 1.53

Date: December 20, 1946
Creator: Van Dyke, Milton D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 1/8-scale powered model of a high-speed bomber with a dual pusher propeller aft of the empennage

Aerodynamic characteristics of a 1/8-scale powered model of a high-speed bomber with a dual pusher propeller aft of the empennage

Date: October 12, 1945
Creator: Schnurbusch, Alfred W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of a Portion of the Horizontal Tail from a Douglas C-74 Airplane with Fabric-Covered Elevators

Aerodynamic Characteristics of a Portion of the Horizontal Tail from a Douglas C-74 Airplane with Fabric-Covered Elevators

Date: May 6, 1947
Creator: Perone, Angelo & Berthold, Cecil L.
Description: A Douglas C-74 airplane, during a test dive at about 0.525 Mach number, experienced uncontrollable longitudinal oscillations sufficient to cause shedding of the outer wing panels and the subsequent crash of the airplane. Tests of a section of the horizontal tail plane from a C-74 airplane were conducted in the Ames 16-foot high-speed wind tunnel to investigate the possibility of the tail as a contributing factor to the accident. The results of the investigations of fabric-covered elevators in various conditions of surface deformation are presented in this report.
Contributing Partner: UNT Libraries Government Documents Department
An Analytical Investigation of the Heat Losses from a U.S. Navy K-Type Airship

An Analytical Investigation of the Heat Losses from a U.S. Navy K-Type Airship

Date: December 20, 1946
Creator: Hillendahl, Wesley H. & George, Ralph E.
Description: The heat losses from the envelope surface of a U.S. Navy K-type airship are evaluated to determine if the use of heat is a feasible means of preventing ice and snow accumulations on lighter-than-air craft during flight and when moored uncovered. Consideration is given to heat losses in clear air (no liquid water present in the atmosphere) and in probable conditions of icing and snow. The results of the analysis indicate that the amount of heat required in flight to raise the surface temperature of the entire envelope to the extent considered adequate for ice protection, based on experience with tests of heavier-than-air craft, is very large. Existing types of heating equipment which could be used to supply this quantity of heat would probably be too bulky and heavy to provide a practical flight installation. The heat requirements to provide protection for the nose and stern regions in assumed mild to moderate icing conditions appear to be within the range of the capacity of current types of heating equipment suitable for flight use. The amount of heat necessary to prevent snow accumulations on the upper surface of the airship envelope when moored uncovered under all conditions appear to be excessive ...
Contributing Partner: UNT Libraries Government Documents Department
An analytical study of the comparative performance of four air-induction systems for turbojet-powered airplanes designed to operate at Mach numbers up to 1.5

An analytical study of the comparative performance of four air-induction systems for turbojet-powered airplanes designed to operate at Mach numbers up to 1.5

Date: June 17, 1952
Creator: Blackaby, James R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analytical study of the comparative performance of six air-induction systems for turbojet-powered airplanes designed to operate at Mach numbers up to 2.0

An analytical study of the comparative performance of six air-induction systems for turbojet-powered airplanes designed to operate at Mach numbers up to 2.0

Date: October 9, 1953
Creator: Watson, Earl C
Description: A study is presented of inlet designs and aerodynamic characteristics of air-induction systems intended for operation with a turbojet engine operating with a constant-volume air-flow process. Two-dimensional inlet designs similar to those discussed in NACA RM A52C14, plus a fixed-geometry inlet with a convergent-divergent diffuser, and an additional variable-geometry inlet are considered for Mach numbers from 0.85 to 2.0 from sea level to the stratosphere. For best performance throughout this range of Mach numbers and altitudes, it was shown that the geometry of the inlet must be such as to insure a high pressure recovery, as well as to provide for a variable entrance area. The inlets are compared on the basis of a drag evaluation neglecting viscosity.
Contributing Partner: UNT Libraries Government Documents Department
Analytical study of the comparative pitch-up behavior of several airplanes and correlation with pilot opinion

Analytical study of the comparative pitch-up behavior of several airplanes and correlation with pilot opinion

Date: June 12, 1957
Creator: Sadoff, Melvin; Stewart, John D & Cooper, George E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The boundary-layer and stalling characteristics of the NACA 64A010 airfoil section

The boundary-layer and stalling characteristics of the NACA 64A010 airfoil section

Date: November 1, 1950
Creator: Peterson, Robert F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An analytical investigation of thermal-electric means of preventing ice formations on a propeller blade

An analytical investigation of thermal-electric means of preventing ice formations on a propeller blade

Date: August 1, 1944
Creator: Scherrer, Richard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Boundary-layer measurements on several porous materials with suction applied

Boundary-layer measurements on several porous materials with suction applied

Date: June 18, 1952
Creator: Mccullough, G. B. & Gambucci, B. J.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Boundary-layer stability diagrams for electrically conducting fluids in the presence of a magnetic field

Boundary-layer stability diagrams for electrically conducting fluids in the presence of a magnetic field

Date: August 1, 1958
Creator: Rossow, Vernon J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Boundary-layer transition on a cooled 20 degree cone at Mach numbers of 1.5 and 2.0

Boundary-layer transition on a cooled 20 degree cone at Mach numbers of 1.5 and 2.0

Date: July 1, 1950
Creator: Scherrer, Richard
Description: None
Contributing Partner: UNT Libraries Government Documents Department