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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Collection: National Advisory Committee for Aeronautics Collection
Transonic Flutter Investigation of an All-movable Horizontal Tail for a Fighter Airplane

Transonic Flutter Investigation of an All-movable Horizontal Tail for a Fighter Airplane

Date: January 14, 1957
Creator: Abbott, F. T., Jr. & Land, N. S.
Description: Transonic flutter of all-movable horizontal tail - bending & pitching moments.
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, 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
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
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
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