3 Matching Results

Search Results

Results: 1 - 3
open access

Operating Stresses in Aircraft-Engine Crankshafts and Connecting Rods 1: Slip-Ring and Bush Combinations for Dynamic-Strain Measurements

Description: "Tests were conducted to develop a slip-ring and brush system that will perform satisfactorily in aircraft-engine, dynamic-strain-measuring applications where resistance-wire strain gages are the means of measuring the strain and to correlate the data obtained from tests in order to provide a basis for predicting the performance of similar slip-ring and brush systems operating under conditions similar to those imposed by these tests." 24 combinations of materials were tested dry and 8 were test… more
Date: March 30, 1945
Creator: Dutee, Francis J.; Phillips, Franklyn W. & Kemp, Richard H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of J-33-A-21 Turbojet-Engine Compressor I - Over-All Performance Characteristics at Equivalent Impeller Speeds from 6000 to 13,400 RPM

Description: "The NACA is investigating a series of J-33 turbojet-engine compressors to determine the over-all and component performances and to improve theories of flow through large centrifugal compressors, The production model J-33-A-21 was operated over a range of inlet temperatures from 80 to -40 F and inlet pressures from 14 to 5 inches mercury absolute for equivalent impeller speeds from 6000 to 13,400 rpm. At the equivalent design speed of 11,500 rpm, the compressor had a peak pressure ratio of 3.98… more
Date: March 30, 1948
Creator: Beede, William L.; Kovach, Karl & Creagh, John W. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigations at supersonic speeds of 22 triangular wings representing two airfoil sections for each of 11 apex angles

Description: The results of tests of 22 triangular wings, representing two leading-edge shapes for each of 11 apex angles, at Mach numbers 1.62, 1.92, and 1.40 are presented and compared with theory. All wings have a common thickness ratio of 8 percent and a common maximum-thickness point at 18 percent chord. Lift, drag, and pitching moment are given for all wings at each Mach number. The relation of transition in the boundary layer, shocks on the wing surfaces, and characteristics of the pressure distribut… more
Date: March 30, 1949
Creator: Love, Eugene S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen