9 Matching Results

Search Results

Advanced search parameters have been applied.

Investigation of a high-performance axial-flow compressor transonic inlet rotor designed for 37.5 pounds per second per square foot of frontal area: detailed blade-element performance

Description: Report presenting detailed blade-element-performance plots for a high-flow transonic inlet rotor. Information provided includes the effects of Mach number, blade loading, and angle of attack on element performance is provided.
Date: April 12, 1957
Creator: Felix, A. Richard & Savage, Melvyn
Partner: UNT Libraries Government Documents Department

Investigation of a high-performance axial-flow compressor transonic inlet rotor designed for 37.5 pounds per second per square foot of frontal area 1: aerodynamic design and overall performance

Description: Report presenting an investigation of the design and tests of a transonic inlet rotor with emphasis placed on increasing the design specific weight flow while maintaining reasonably high pressure ratio and efficiency. Information regarding peak efficiency and how to best achieve it through design is provided.
Date: March 24, 1955
Creator: Savage, Melvyn & Felix, A. Richard
Partner: UNT Libraries Government Documents Department

Investigation of a three-stage transonic research axial-flow compressor: aerodynamic design and overall performance

Description: Report discussing an investigation of the performance of a three-stage transonic compressor with high stage pressure ratios to investigate problems encountered when high-pressure-ratio transonic stages are grouped together to form a multistage compressor. Results are presented regarding overall performance in Freon, stage performance, and radial variation in overall stagnation pressure ratio.
Date: October 27, 1955
Creator: Savage, Melvyn & Beatty, Loren A.
Partner: UNT Libraries Government Documents Department

Transonic investigation of an axial-flow compressor rotor with a hub-tip ratio of 0.75 and blades having NACA A(sub 2)I(Sub 8b) mean lines

Description: Report presenting a blade-element analysis of a compressor rotor with blade sections with NACA A(sub 2)I(Sub 8b) mean lines and 65-series thickness distributions in Freon-12 gas. Results regarding blade loss, angle of attack associated with minimum loss, peak efficiencies, and comparison with other transonic rotors are provided.
Date: September 30, 1957
Creator: Bernot, Peter T. & Savage, Melvyn
Partner: UNT Libraries Government Documents Department

High-speed cascade tests of a blade section designed for typical hub conditions of high-flow transonic rotors

Description: Report discussing high-speed cascade tests made of a blade section designed for conditions typical of the hub section of high-flow transonic rotors. The intent of the testing is to provide information on the effects of local surface Mach numbers on blade performance. The test results, effect of more forward location on peak surface velocities, effect of increase in pressure-rise coefficient, effect of Mach number and pressure rise on turning angle, and a comparison of variation in momentum-loss coefficient with surface pressure-rise coefficient are provided.
Date: September 28, 1955
Creator: Savage, Melvyn; Felix, A. Richard & Emery, James C.
Partner: UNT Libraries Government Documents Department

Investigation of an axial-flow compressor rotor having NACA high-speed blade sections (A(sub 2)I(sub 8b) series) at mean radius relative inlet Mach numbers up to 1.13

Description: Report presenting the results of testing on a high-pressure-ratio, axial-flow compressor rotor designed to operate efficiently at high speeds. High flows are needed to increase engine thrust without increasing engine front area. Results regarding the overall total-pressure ratio and adiabatic efficiency, effect of angle of attack on efficiency, determination of the effect of mean radius rotor inlet Mach number and Reynolds number on turning angle, and other information about ideal operation of the rotor are provided.
Date: November 30, 1953
Creator: Savage, Melvyn; Erwin, John R. & Whitley, Robert P.
Partner: UNT Libraries Government Documents Department

Low-speed cascade tests of two 45 degree swept compressor blades with constant spanwise loading

Description: Report discussing an investigation of two 45 degree swept blades in low-speed cascade tunnels at a range of angles of attack and various combinations of inlet-air angle and solidity. The isolated wing method used to design the blade predicted the twist distribution and camber shape necessary to obtain an almost uniform spanwise loading.
Date: March 15, 1954
Creator: Beatty, Loren A.; Savage, Melvyn & Emery, James C.
Partner: UNT Libraries Government Documents Department