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An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability Below the Mach Number of Lift Divergence

Description: An analysis is presented of the influence of wing aspect ratio and tail location on the effects of compressibility upon static longitudinal stability. The investigation showed that the use of reduced wing aspect ratios or short tail lengths leads to serious reductions in high-speed stability and the possibility of high-speed instability.
Date: January 9, 1948
Creator: Axelson, John A. & Crown, J. Conrad
Item Type: Report
Partner: UNT Libraries Government Documents Department

Free-flight performance of 16-inch-diameter supersonic ram-jet units III : four units designed for combustion-chamber-inlet Mach number of 0.245 at free-stream Mach number of 1.8 (Units D-1, D-2, D-3, and D-4)

Description: Performance of four 16-inch-diameter ram-jet units was determined at free-stream Mach numbers of 0.49 to 1.78 over range of gas total-temperature ratios of 1.0 to 6.1. Time histories of each flight and data on thrust, drag, diffuser efficiency, and combustion are presented. A maximum thrust coefficient of 0.88 and a maximum net acceleration of 5.13 g's were observed for the four units.
Date: June 28, 1950
Creator: Disher, John H & Rabinowitz, Leonard
Item Type: Report
Partner: UNT Libraries Government Documents Department

Extension of boundary-layer heat-transfer theory to cooled turbine blades

Description: An equation for average heat transfer of a surface was derived when the boundary layer changed from laminar to turbulent. Influences on the heat transfer through a laminar boundary layer of Mach number, temperature ratio (gas temperature divided by wall temperature), and exponents of gas-property temperature relations were shown to be relatively small for air with Mach numbers less than 2 and temperature ratios between 1 and 4. Good agreement was obtained with experimental results from cylinders, an airfoil, and turbine blades.
Date: August 11, 1950
Creator: Brown, W Byron & Donoughe, Patrick L
Item Type: Report
Partner: UNT Libraries Government Documents Department

Investigation of altitude starting and acceleration characteristics of J47 turbojet engine

Description: An investigation was conducted on an axial-flow-compressor type turbojet engine in the NACA Lewis altitude wind tunnel to determine the operational characteristics of several ignition systems, cross-fire tube configurations and fuel systems over a range of simulated flight conditions. The opposite-polarity-type spark plug provided the most satisfactory ignition. Increasing the cross-fire-tube diameter improved intercombustor flame propagation. At high windmilling speeds, accelerations to approximately 6200 rpm could be made at a preset constant throttle position. The use of a variable-area nozzle reduced acceleration time.
Date: January 10, 1951
Creator: Golladay, Richard L & Bloomer, Harry E
Item Type: Report
Partner: UNT Libraries Government Documents Department

Investigation of blade-row flow distributions in axial-flow-compressor stage consisting of guide vanes and rotor-blade row

Description: A 30-inch tip-diameter axial-flow compressor stage was investigated with and without rotor to determine individual blade-row performance, interblade-row effects, and outer-wall boundary-layer conditions. Velocity gradients at guide-vane outlet without rotor approximated design assumptions, when the measured variation of leaving angle was considered. With rotor in operation, Mach number and rotor-blade effects changed flow distribution leaving guide vanes and invalidated design assumption of radial equilibrium. Rotor-blade performance correlated interpolated two-dimensional results within 2 degrees, although tip stall was indicated in experimental and not two-dimensional results. Boundary-displacement thickness was less than 1.0 and 1.5 percent of passage height after guide vanes and after rotor, respectively, but increased rapidly after rotor when tip stall occurred.
Date: November 28, 1950
Creator: Mahoney, John J; Dugan, Paul D; Budinger, Raymond E & Goelzer, H Fred
Item Type: Report
Partner: UNT Libraries Government Documents Department

Free-flight performance of 16-inch-diameter supersonic ram-jet units II : five units designed for combustion-chamber-inlet Mach number of 0.16 at free-stream Mach number of 1.60 (units B-1, B-2, B-3, B-4, and B-5) /c Wesley E. Messing and Scott H. S

Description: Free-flight performance of five 16-inch-diameter ram-jet units was determined over range of free-stream Mach numbers of 0.50 to 1.86 and gas total-temperature ratios between 1.0 and 6.1 Time histories of performance data are presented for each unit. Correlations illustrate effect of free-stream Mach number and gas total-temperature ratio on diffuser total-pressure recovery, net-thrust coefficient, and external drag coefficient. One unit had smooth steady burning throughout the entire flight and encountered a maximum free-stream Mach number of 1.86 with a net acceleration of approximately 4.2 g's.
Date: May 5, 1950
Creator: Messing, Wesley E & Simpkinson, Scott H
Item Type: Report
Partner: UNT Libraries Government Documents Department