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  Partner: UNT Libraries Government Documents Department
 Collection: National Advisory Committee for Aeronautics Collection
Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems-effect of Method of Positioning the Radar Antenna on the Speed of Response

Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems-effect of Method of Positioning the Radar Antenna on the Speed of Response

Date: August 13, 1952
Creator: Abramovitz, M.
Description: Proportional navigation guidance systems - radar antenna positioning effects on speed of response.
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of the performance of proportional navigation guidance systems : effect of method of positioning the radar antenna on the speed of response

Theoretical investigation of the performance of proportional navigation guidance systems : effect of method of positioning the radar antenna on the speed of response

Date: August 13, 1952
Creator: Abramovitz, Marvin
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical investigation of the performance of proportional navigation guidance systems : effect of missile configuration on the speed of response

Theoretical investigation of the performance of proportional navigation guidance systems : effect of missile configuration on the speed of response

Date: January 19, 1953
Creator: Abramovitz, Marvin
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of stick-force gradient and stick gearing on the tracking accuracy of a fighter airplane

The effect of stick-force gradient and stick gearing on the tracking accuracy of a fighter airplane

Date: December 17, 1954
Creator: Abramovitz, Marvin & Van Dyke, Rudolph D , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of the use of a stick force proportional to pitching acceleration for normal-acceleration warning

Investigation of the use of a stick force proportional to pitching acceleration for normal-acceleration warning

Date: August 14, 1953
Creator: Abramovitz, Marvin; Schmidt, Stanley F & Van Dyke, Rudolph D , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Theoretical Investigation of the Effects of the Artificial-Feel System on the Maneuvering Characteristics of the F-89 Airplane

Theoretical Investigation of the Effects of the Artificial-Feel System on the Maneuvering Characteristics of the F-89 Airplane

Date: December 31, 1952
Creator: Abramovitz, Marvin; Schmidt, Stanley F. & Belsley, Steven E.
Description: The possibility of overshooting the anticipated normal acceleration as a result of the artificial-feel characteristics of the F-89C airplane at a condition of minimum static stability was investigated analytically by means of an electronic simulator. Several methods of improving the stick-force characteristics were studied. It is shown that, due to the lag in build-up of the portion of the stick force introduced by the bobweight, it would be possible for excessive overshoots of normal acceleration to occur in abrupt maneuvers with reasonable assumed control movements. The addition of a transient stick force proportional to pitching acceleration (which leads the normal acceleration) to prevent this occurring would not be practical due to the introduction of an oscillatory mode to the stick-position response. A device to introduce a viscous damping force would Improve the stick-force characteristics so that normal acceleration overshoots would not be likely, and the variation of the maximum stick force in rapid pulse-type maneuvers with duration of the maneuver then would have a favorable trend.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of internal film cooling of exhaust nozzle of a 1000-pound-thrust liquid-ammonia liquid-oxygen rocket

Investigation of internal film cooling of exhaust nozzle of a 1000-pound-thrust liquid-ammonia liquid-oxygen rocket

Date: June 17, 1952
Creator: Abramson, Andrew E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Variation in the number of revolutions of air propellers

Variation in the number of revolutions of air propellers

Date: March 1, 1923
Creator: Achenbach, W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Natural icing of an axial-flow turbojet engine in flight for a single icing condition

Natural icing of an axial-flow turbojet engine in flight for a single icing condition

Date: August 12, 1948
Creator: Acker, L. W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary results of natural icing of an axial-flow turbojet engine

Preliminary results of natural icing of an axial-flow turbojet engine

Date: August 6, 1948
Creator: Acker, L. W.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of a liquid hydrogen fuel system

Flight investigation of a liquid hydrogen fuel system

Date: August 19, 1957
Creator: Acker, L. W.; Christenson, H. H.; Gough, W. V. & Mulholland, D. R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary results of natural icing of an axial-flow turbojet engine

Preliminary results of natural icing of an axial-flow turbojet engine

Date: August 6, 1948
Creator: Acker, Loren W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of flight performance of AN-F-58 and AN-F-32 fuels in J35 turbojet engine

Comparison of flight performance of AN-F-58 and AN-F-32 fuels in J35 turbojet engine

Date: April 7, 1949
Creator: Acker, Loren W & Kleinknecht, Kenneth S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of inlet icing on performance of axial-flow turbojet engine in natural icing conditions

Effects of inlet icing on performance of axial-flow turbojet engine in natural icing conditions

Date: May 25, 1950
Creator: Acker, Loren W & Kleinknecht, Kenneth S
Description: A flight investigation in natural icing conditions was conducted to determine the effect of inlet ice formations on the performance of axial-flow turbojet engines. The results are presented for icing conditions ranging from a liquid-water content of 0.1 to 0.9 gram per cubic meter and water-droplet size from 10 to 27 microns at ambient-air temperature from 13 to 26 degrees F. The data show time histories of jet thrust, air flow, tail-pipe temperature, compressor efficiency, and icing parameters for each icing encounter. The effect of inlet-guide-vane icing was isolated and shown to account for approximately one-half the total reduction in performance caused by inlet icing.
Contributing Partner: UNT Libraries Government Documents Department
Flight Comparison of Performance and Cooling Characteristics of Exhaust-Ejector Installation with Exhaust-Collector-Ring Installation

Flight Comparison of Performance and Cooling Characteristics of Exhaust-Ejector Installation with Exhaust-Collector-Ring Installation

Date: February 14, 1947
Creator: Acker, Loren W. & Kleinknecht, Kenneth S.
Description: Flight and ground investigations have been made to compare an exhaust-ejector installation with a standard exhaust-collector-ring installation on air-cooled aircraft engines in a twin-engine airplane. The ground investigation allowed that, whereas the standard engine would have overheated above 600 horsepower, the engine with exhaust ejectors cooled at take-off operating conditions at zero ram. The exhaust ejectors provided as much cooling with cowl flaps closed as the conventional cowl flaps induced when full open at low airspeeds. The propulsive thrust of the exhaust-ejector installation was calculated to be slightly less than the thrust of the collector-ring-installation.
Contributing Partner: UNT Libraries Government Documents Department
Accelerations in fighter-airplane crashes

Accelerations in fighter-airplane crashes

Date: November 4, 1957
Creator: Acker, Loren W; Black, Duglad O & Moser, Jacob C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air forces on airfoils moving faster than sound

Air forces on airfoils moving faster than sound

Date: June 1, 1925
Creator: Ackeret, J
Description: We are undertaking the task of computing the air forces on a slightly cambered airfoil in the absence of friction and with an infinite aspect ratio. We also assume in advance that the leading edge is very sharp and that its tangent lies in the direction of motion.
Contributing Partner: UNT Libraries Government Documents Department
Drag measurements of two thin wing sections at different index values

Drag measurements of two thin wing sections at different index values

Date: June 1, 1927
Creator: Ackeret, J
Description: It is stated that the index value 6000, as found in normal tests of wing sections with a 20 cm chord, falls in the same region where the transition of laminar to turbulent flow takes place on thin flat plates. It is to be expected that slightly cambered, thin wing sections will behave similarly. The following test of two such wing sections were made for the purpose of verifying this supposition.
Contributing Partner: UNT Libraries Government Documents Department
Experiments on airfoils with trailing edge cut away

Experiments on airfoils with trailing edge cut away

Date: September 1, 1927
Creator: Ackeret, J
Description: Airfoils with their trailing edge cut away are often found on aircraft, as the fins on the hulls of flying boats and the central section of the wings for affording better visibility. It was therefore of some interest to discover the effect of such cutaways on the lift and drag and on the position of the center of pressure. For this purpose, systematic experiments were performed on two different airfoils, a symmetrical airfoil and an airfoil of medium thickness, with successive shortenings of their chords.
Contributing Partner: UNT Libraries Government Documents Department
High-speed wind tunnels

High-speed wind tunnels

Date: November 1, 1936
Creator: Ackeret, J
Description: Wind tunnel construction and design is discussed especially in relation to subsonic and supersonic speeds. Reynolds Numbers and the theory of compressible flows are also taken into consideration in designing new tunnels.
Contributing Partner: UNT Libraries Government Documents Department
Present and future problems of airplane propulsion

Present and future problems of airplane propulsion

Date: May 1, 1941
Creator: Ackeret, J
Description: Some of the problems considered in this report include: thermodynamics of surface friction, application of thick wing sections, special applications of controllable propellers, and gas turbines for aircraft.
Contributing Partner: UNT Libraries Government Documents Department
Recent experiments at the Gottingen Aerodynamic Institute

Recent experiments at the Gottingen Aerodynamic Institute

Date: July 1, 1925
Creator: Ackeret, J
Description: This report presents the results of various experiments carried out at the Gottingen Aerodynamic Institute. These include: experiments with Joukowski wing profiles; experiments on an airplane model with a built-in motor and functioning propeller; and the rotating cylinder (Magnus Effect).
Contributing Partner: UNT Libraries Government Documents Department
Removing boundary layer by suction

Removing boundary layer by suction

Date: January 1, 1927
Creator: Ackeret, J
Description: Through the utilization of the "Magnus effect" on the Flettner rotor ship, the attention of the public has been directed to the underlying physical principle. It has been found that the Prandtl boundary-layer theory furnishes a satisfactory explanation of the observed phenomena. The present article deals with the prevention of this separation or detachment of the flow by drawing the boundary layer into the inside of a body through a slot or slots in its surface.
Contributing Partner: UNT Libraries Government Documents Department
Experimental and Theoretical Investigations of Cavitation in Water

Experimental and Theoretical Investigations of Cavitation in Water

Date: May 1, 1945
Creator: Ackeret, J.
Description: The cavitation in nozzles on airfoils of various shape and on a sphere are experimentally investigated. The limits of cavitation and the extension of the zone of the bubbles in different stages of cavitation are photographically established. The pressure in the bubble area is constant and very low, jumping to high values at the end of the area. The analogy with the gas compression shock is adduced and discussed. The collapse of the bubbles under compression shock produces very high pressures internally, which must be contributory factors to corrosion. The pressure required for purely mechanical corrosion is also discussed.
Contributing Partner: UNT Libraries Government Documents Department