Three-axis finger tip controller for switches Patent
Remote control device operated by movement of finger tips for manual control of spacecraft attitude
Lopez, A. E.↗
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Results for “TiP”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Subsonic aerodynamic characteristics of a model of HL-10 flight research vehicle with basic and modified tip pins
Subsonic aerodynamic characteristics of model of HL-10 flight research vehicle with basic and modified tip fins
Huffman, J. K.↗
Static-pressure contours in the blade passage at the tip of several high Mach number rotors
Static pressure contours of turbine rotor blade tips at high Mach numbers
Bailey, E. E.↗
Computer program for preliminary design and analysis of V/STOL tip-turbine fans
Computer program for design and analysis of V/STOL tip turbine fans
Auer, B. M.↗
An experimental investigation and evaluation of a Doppler radar technique for the measurement of the flow generated by wing tip vortices Final summary report
Doppler radar measurements of flow generated by wing tip vortices using reflective chaff dispensed into vortices
Easterbrook, C. C.↗
Arc electrode of graphite with ball tip Patent
Arc electrode of graphite with tantalum ball tip
Gordon, W. A.↗
High-loading low-speed fan study. 3 - Data and performance slotted blades and vanes and rotor tip treatment
Slotted blades and vanes and rotor tip design for highly loaded, low speed fan stage applicable to low noise aircraft engines
Burdsall, E. A.↗
Static aerodynamic characteristics of a Scout fin with an enlarged tip control at Mach numbers from 0.40 to 4.63
Static aerodynamic characteristics of Scout fin with enlarged tip control at Mach numbers from 0.40 to 4.63
Keynton, R. J.↗
Tip vortices: Velocity distributions
Hot-wire anemometer measurements of streamwise magnitudes and normal velocity components of wing tip vortex
Chigier, N. A.↗
Tip vortices - Velocity distributions
Flow field velocity distribution at rotating wing devices tip vortices
Chigier, N. A.↗
The influence of curvature on stress intensity at the tip of a circumferential crack in a cylindrical shell
Curvature effect on cylindrical shell circumferential crack tip stress intensity, using fatigue crack growth tests
Adams, N. J. I.↗
The effect of a drooped wing tip on its trailing vortex system
Drooped wing tip effects on trailing vortex sheet structure and position from spanwise load distribution determination by vortex lattice theory
Mccormick, B. W.↗
Acoustic testing of a 1.5 pressure ratio, low tip speed fan (QEP fan B scale model)
A scale model (0.484 scale factor) of a single stage fan designed for a 1.5 pressure ratio and 1160 ft/sec tip speed was tested to determine its noise characteristics. The fan had 26 blades and 60 outlet guide vanes, with vanes spaced two rotor blade aerodynamic chords from the blades. The effects of speed, exhaust nozzle area and fan frame acoustic treatment on the scale model's noise characteristics were investigated.
Kazin, S. B.↗
High-loading, 1800 ft/sec tip speed transonic compressor fan stage. 1: Aerodynamic and mechanical design
A single stage fan with a tip speed of 1800 ft/sec (548.6m/sec) and hub/tip ratio of 0.5 was designed to produce a pressure ratio of 2.285:1 with an adiabatic efficiency of 84.0%. The design flow per inlet annulus area is 38.7 lbm/sq ft-sec (188.9KG/sqm-sec). Rotor blades have modified multiple-circular-arc and precompression airfoil sections. The stator vanes have multiple-circular-arc airfoil sections.
Morris, A. L.↗
Finite elements for determination of crack tip elastic stress intensity factors.
A new type of finite element is introduced which embodies the inverse square root singularity of the stress distribution arising near a crack in an elastic medium. Using this element near the crack tip in two typical cracked configurations, stress intensity factors within 5% of accepted values were obtained, with meshes having as few as 250 degrees of freedom.
Tracey, D. M.↗
Investigation of the stability of the tip vortex generated by hovering propellers and rotors.
The objective of this experimental and theoretical investigation was to determine what factors and mechanisms are involved in vortex interaction and instability and how these phenomena manifest themselves. To answer these questions, the schlieren method of flow visualization was used to observe the wakes generated by two- and four-bladed model propellers and rotors. A concurrent free-wake analysis was conducted for comparative purposes. Schlieren pictures showing wake asymmetry, interaction, and instability are presented. Various factors and mechanisms believed to be responsible for these are discussed along with the effects produced by the number of blades, collective pitch, and tip speed. Free-wake calculations that qualitatively confirm those factors responsible for wake asymmetry and interaction are also presented.
Tangler, J. L.↗
Performance of a single-stage transonic compressor with a blade-tip solidity of 1.3
The design and experimental performance of a 50-centimeter-diameter, single stage, axial flow, transonic compressor with a blade tip solidity of 1.3 are presented. Radial surveys were made of the flow conditions for both the rotor and stator. At design speed, peak efficiencies for both rotor and stage were 0.87 and 0.82, respectively, and occurred at an equivalent weight flow of 29.6 kilograms per second (202 kg/sec/sq m of annulus area). At peak efficiency, the total pressure ratios for both rotor and stage were 1.79 and 1.73, respectively. Stall margin for the stage was 17 percent.
Urasek, D. C.↗