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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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Airframe installation effects on exhaust nozzle systems mounted on underwing engine nacelles at transonic speeds
Instruction procedures for training military personnel to install and operate omnidirectional sound locating set
Production and installation variables for titanium 6Al-4V fasteners and wing bolts assembled in titanium 8Al-1Mo-1V sheet material
Direct view storage tube /DVST/ as graphical display unit for small digital computer installation
Airframe installation effects at transonic speeds on underwing supersonic cruise exhaust nozzles, using flight and wind tunnel tests
Tool is devised which holds BNC connector during installation and permits tightening nut without damaging connector.
Two variations of gas generator method to calculate thrust of afterburning turbofan engines installed in F-111A aircraft
Investigation of variables affecting joint preload properties of installed structural bolts and nuts used in fabrication and construction of spacecraft components
Cross flow wind tunnel performance tests of 15 in. wing installed lift fan with coaxial drive turbine for VTOL transport aircraft
Training and installation procedures for NASTRAN program
Methods and procedures for evaluating, forming, and installing small diameter thermocouple wire and sheathed thermocouples
Bonded and weldable strain gages for aircraft flight loads measurements at high temperatures, discussing installation, calibration and performance tests
Turn rate gyro installation angle and airspeed effects on instrument reliability, presenting in-flight investigation results relative to turn rate information usefulness under various flight conditions
Aircraft flight load measurements in high temperature environment, determining optimal strain gage installation and calibration
Wing installed VTOL coaxial drive lift fan model in wind tunnel test, investigating performance in crosswind environment
Computer installations on photometric telescope control system for astronomical observations
A modified F-106B aircraft with underwing engine nacelles was flight tested to investigate airframe installation effects on ejector nozzles. Nozzle thrust coefficients, boattail drag coefficients, and boundary layer characteristics were obtained for the three nozzles. All the nozzles were geometrically similar and had 15 deg conical boattails with juncture radii of curvature equal to 0.5 maximum nozzle diameter. The effects of boattail location relative to the wing trailing edge and the ejector to primary nozzle exit diameter ratio were investigated. Shortening the length by 0.48 nozzle diameter lowered the transonic boattail drag rise Mach number from 0.97 to 0.95. Decreasing the nozzle exit diameter, which reduced the ejector to primary nozzle exit diameter ratio from 1.30 to 1.18, increased the gross thrust coefficient 4.8 percent.
Test data are presented for a 38-cm (15-in.) diameter, 1.28 pressure ratio model VTOL lift fan installed in a two-dimensional wing and tested in a 2.74-by 4.58-meter (9-by 15-ft)V/STOL wind tunnel. Tests were run with and without exit louvers over a wide range of crossflow velocities and wing angle of attack. Tests were also performed with annular-inlet vanes, inlet bell-mouth surface disconuities, and fences to induce fan windmilling. Data are presented on the axial force of the fan assembly and overall wing forces and moments as measured on force balances for various static and crossflow test conditions. Midspan wing surface pressure coefficient data are also given.