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  Partner: UNT Libraries Government Documents Department
 Resource Type: Report
 Decade: 1950-1959
Thrust and drag characteristics of a convergent-divergent nozzle with various exhaust jet temperatures

Thrust and drag characteristics of a convergent-divergent nozzle with various exhaust jet temperatures

Date: March 11, 1954
Creator: Hearth, Donald P & Wilcox, Fred A
Description: An investigation was conducted in the 8-by-6 foot supersonic wind tunnel on the effect of exhaust-gas temperatures on the external and internal characteristics of a convergent-divergent nozzle having an area expansion ratio of 1.83. Data were obtained over a pressure-ratio range from 1 to 20 at free-stream Mach numbers of 1.6 and 2.0 for exhaust temperatures of 860 degrees, 1650 degrees, and 2000 degrees R. Results of this investigation indicated that generally both the internal and external performance characteristics were only slightly affected by a large change in jet temperature. The small differences in performance which did occur were predicted satisfactorily from theoretical considerations.
Contributing Partner: UNT Libraries Government Documents Department
Thrust and drag characteristics of simulated variable-shroud nozzles with hot and cold primary flows at subsonic and supersonic speeds

Thrust and drag characteristics of simulated variable-shroud nozzles with hot and cold primary flows at subsonic and supersonic speeds

Date: February 18, 1955
Creator: Beke, Andrew & Simon, Paul C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Thrust and pumping characteristics of a series of ejector-type exhaust nozzles at subsonic and supersonic flight speeds

Thrust and pumping characteristics of a series of ejector-type exhaust nozzles at subsonic and supersonic flight speeds

Date: November 17, 1954
Creator: Hearth, Donald P & Valerino, Alfred S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Thrust and Pumping Characteristics of a Series of Ejectortype Exhaust Nozzles at Subsonic and Supersonic Flight Speeds

Thrust and Pumping Characteristics of a Series of Ejectortype Exhaust Nozzles at Subsonic and Supersonic Flight Speeds

Date: November 17, 1954
Creator: Hearth, D. P. & Valerino, A. S.
Description: Thrust and pumping characteristics of ejector-type exhaust nozzles at subsonic and supersonic speeds.
Contributing Partner: UNT Libraries Government Documents Department
Thrust Augmentation of a Turbojet Engine at Simulated Flight Conditions by Introduction of a Water-Alcohol Mixture into the Compressor

Thrust Augmentation of a Turbojet Engine at Simulated Flight Conditions by Introduction of a Water-Alcohol Mixture into the Compressor

Date: August 18, 1952
Creator: Useller, James W.; Auble, Carmon M. & Harvey, Ray W., Sr.
Description: An investigation was conducted at simulated high-altitude flight conditions to evaluate the use of compressor evaporative cooling as a means of turbojet-engine thrust augmentation. Comparison of the performance of the engine with water-alcohol injection at the compressor inlet, at the sixth stage of the compressor, and at the sixth and ninth stages was made. From consideration of the thrust increases achieved, the interstage injection of the coolant was considered more desirable preferred over the combined sixth- and ninth-stage injection because of its relative simplicity. A maximum augmented net-thrust ratio of 1.106 and a maximum augmented jet-thrust ratio of 1.062 were obtained at an augmented liquid ratio of 2.98 and an engine-inlet temperature of 80 F. At lower inlet temperatures (-40 to 40 F), the maximum augmented net-thrust ratios ranged from 1.040 to 1.076 and the maximum augmented jet-thrust ratios ranged from 1.027 to 1.048, depending upon the inlet temperature. The relatively small increase in performance at the lower inlet-air temperatures can be partially attributed to the inadequate evaporation of the water-alcohol mixture, but the more significant limitation was believed to be caused by the negative influence of the liquid coolant on engine- component performance. In general, it is concluded that ...
Contributing Partner: UNT Libraries Government Documents Department
Thrust augmentation of a turbojet engine by the introduction of liquid ammonia into the compressor inlet

Thrust augmentation of a turbojet engine by the introduction of liquid ammonia into the compressor inlet

Date: August 13, 1952
Creator: Harp, James L , Jr; Useller, James W & Auble, Carmon M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Thrust characteristics of a series of convergent-divergent exhaust nozzles at subsonic and supersonic flight speeds

Thrust characteristics of a series of convergent-divergent exhaust nozzles at subsonic and supersonic flight speeds

Date: March 12, 1954
Creator: Fradenburgh, Evan A; Gorton, Gerald C & Beke, Andrew
Description: An experimental investigation of a series of four convergent-divergent exhaust nozzles was conducted in the Lewis 8-by-6 foot supersonic wind tunnel at Mach numbers of 0.1, 0.6, 1.6, and 2.0 over a range of nozzle pressure ratios. The thrust characteristics of these nozzles were determined by a pressure-integration technique. From a thrust standpoint, a nozzle designed to give uniform parallel flow at the exit had no advantage over the simple geometric design with conical convergent and divergent sections. The rapid-divergent nozzles might be competitive with the more gradual-divergent nozzles since the relatively short length of these nozzles would be advantageous from a weight standpoint and might result in smaller thrust losses due to friction. The thrusts, with friction losses neglected, were predicted satisfactorily by one-dimensional theory for the nozzles with relatively gradual divergence. The thrusts of the rapid-divergent designs were several percentages below the theoretical values at the design pressure ratio or above, while at low pressure ratios there was a considerable effect of free-stream Mach number, with thrusts considerably above theoretical values at subsonic speeds and somewhat above theoretical values at supersonic speeds. This Mach numb effect appeared to be related to the variation of the model base pressure ...
Contributing Partner: UNT Libraries Government Documents Department
Thrust loading of the NACA 3-(3)(05)-05 eight-blade dual-rotating propeller as determined from wake surveys

Thrust loading of the NACA 3-(3)(05)-05 eight-blade dual-rotating propeller as determined from wake surveys

Date: October 30, 1952
Creator: Platt, Robert J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Time correlator for problems in aerodynamics

Time correlator for problems in aerodynamics

Date: June 1, 1956
Creator: Skinner, George Tolmie
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Time-dependent buckling of a uniformly heated column

Time-dependent buckling of a uniformly heated column

Date: January 1, 1954
Creator: Ness, Nathan
Description: None
Contributing Partner: UNT Libraries Government Documents Department