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Performance characteristics of cylindrical target-type thrust reversers

Description: From tests on cylindrical target-type thrust reversers, it was found that the reverser frontal area, lip angle, end-plate angle, and end-plate depth had important effects on reverse-thrust performance. Frontal area, reverser depth, lip angle, and end-plate angele had important effects on the spacing required for unrestricted nozzle flow. For reverse-thrust ratios greater than 64 percent, the reversed flow attached to the 7 degree cowl in quiescent air. Swept-type cylindrical reversers were generally unstable. The thrust-modulation characteristics of a cylindrical target-type thrust reverser were found to be satisfactory.
Date: January 11, 1956
Creator: Steffen, Fred W & Mcardle, Jack G
Partner: UNT Libraries Government Documents Department

Comparison of performance and component frontal areas of hypothetical two-spool and one-spool turbojet engines

Description: For constant-mechanical-speed operation, the two-spool thrust values are as great as or greater than the one-spool thrust values over the entire flight range considered, while the specific fuel consumption for the two engines agrees within 1 percent. The maximum difference in thrust occurs at Mach 2.8 in the stratosphere, where the two-spool thrust advantage is about 9 percent for operation with the after burning.
Date: January 17, 1956
Creator: Dugan, James F , Jr
Partner: UNT Libraries Government Documents Department

Effects of a J34 turbojet engine on supersonic diffuser performance

Description: Report presenting testing of a translating cone inlet with a variable bypass at Mach numbers 1.6, 1.8, and 2.0 with both a choked exit plug and a J34 turbojet engine. The main difference between the two options was increased inlet subcritical stability with the engine. Results regarding basic diffuser performance, inlet stability, buzz amplitude and frequency, and diffuser-exit profiles are provided.
Date: January 4, 1956
Creator: Beheim, Milton A. & Englert, Gerald W.
Partner: UNT Libraries Government Documents Department

Performance of a high-solidity high-pressure-ratio transonic rotor

Description: A high-solidity low-aspect-ratio transonic rotor with an inlet hub-tip ratio of 0.52 was investigated experimentally. The rotor developed a total-pressure tatio of 1.93 and an efficiency of 92 percent at an equivalent wheel tip speed of 1036 feet per second. The feasibility of using this rotor as a component of an inlet stage of an axial-flow compressor was investigated.
Date: November 8, 1955
Creator: Neumann, Harvey E
Partner: UNT Libraries Government Documents Department

Effect of an adjustable supersonic inlet on the performance up to Mach number 2.0 of a J34 turbojet engine

Description: A J34 turbojet engine was investigated at free-stream Mach numbers of 0.12 and 1.6 to 2.0 to determine the effect of supersonic inlet operation on engine performance. With the excepetion of ideal jet thrust, the use of generalized engine parameters correlated the engine data satisfactorily when the exit nozzle was choked. Large total-pressure distortations did not affect compressor efficiency. During inlet pulsing, the engine operated with compressor-inlet total-pressure variations as large as 18 percent of the local average and at frequnecies of 17 plus or minus 2 cycles per second. Total-pressure amplitudes propagated through the engine and caused ideal-gross-thrust changes up to 12 percent.
Date: January 4, 1956
Creator: Beke, Andrew; Englert, Gerald & Beheim, Milton
Partner: UNT Libraries Government Documents Department

Experimental investigation of a surge control on a turbojet engine

Description: The action of a surge control that reduced fuel flow after receiving an indication of surge initiation was investigated. The control system could successfully limit surge to only 1 cycle but could not completely eliminate surge. Inability to interrupt a surge cycle before its completion was attributed to the conclusion that a surge cycle is irreversible.
Date: November 18, 1955
Creator: Novik, David; Heppler, Herbert & Stiglic, Paul M
Partner: UNT Libraries Government Documents Department

Transportation of liquid fluorine

Description: In tests of a portable tank specially designed and constructed under Air Force Contract AF 33(616)-2229, liquid fluorine was safely transported and stored. The investigation included 82 hours of transportation in a total storage time of 2570 hours.
Date: November 8, 1955
Creator: Ordin, Paul M
Partner: UNT Libraries Government Documents Department

Factors that affect operational reliability of turbojet engines

Description: The problem of improving operational reliability of turbojet engines is studied in a series of papers. Failure statistics for this engine are presented, the theory and experimental evidence on how engine failures occur are described, and the methods available for avoiding failure in operation are discussed. The individual papers of the series are Objectives, Failure Statistics, Foreign-Object Damage, Compressor Blades, Combustor Assembly, Nozzle Diaphrams, Turbine Buckets, Turbine Disks, Rolling Contact Bearings, Engine Fuel Controls, and Summary Discussion.
Date: January 31, 1956
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at transonic speeds of a jet control on a 35 degree swept wing: transonic-bump method

Description: Report presenting an investigation in the high-speed tunnel using the transonic-bump method to determine the characteristics of a jet control consisting of numerous holes located at the 65-percent chord line of a 35 degree swept semispan wing with an NACA 65A006 airfoil section. Testing occurred over a range of Mach numbers, angles of attack, and ejection-pressure ratios. Results regarding rolling-moment coefficients and aerodynamic characteristics in pitch are provided.
Date: February 8, 1956
Creator: Vogler, Raymond D. & Turner, Thomas R.
Partner: UNT Libraries Government Documents Department