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  • Other Sources  (1,152)
  • FACILITIES, RESEARCH, AND SUPPORT
  • 2020-2023
  • 1970-1974  (768)
  • 1960-1964  (384)
  • 1935-1939
Collection
  • Other Sources  (1,152)
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  • 1
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    The tracking system analytic calibration activity for Mariner Mars 1971: Its function and scope (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The functions of the Tracking System Analytic Calibration activity for Mariner Mars 1971 (MM'71), its objectives for this and future missions, and the support provided to the MM'71 Navigation Team during operations are described. Support functions encompass calibration of tracking data by estimating physical parameters whose uncertainties represent limitations to navigational accuracy, and detailed analysis of the tracking data to uncover and resolve any anomalies. Separate articles treat the activities and results of producing calibrations for the various error sources: Deep Space Station Locations, timing and polar motion, charged particles, and the troposphere. Two other articles are also included discussing the effects of the media error sources on orbit determination and the merits of the smoothing technique used for DRIVID.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Tracking System Analytic Calibration Activities for the Mariner Mars 1971 Mission; p 1-12
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  • 2
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    Concerns of the Institute of Transport Study and Research for reducing the sound level inside completely repaired buses (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Sound level measurements on noise sources on buses are used to observe the effects of attenuating acoustic pressure levels inside the bus by sound-proofing during complete repair. A spectral analysis of the sound level as a function of motor speed, bus speed along the road, and the category of the road is reported.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: The 4th Natl. Conf. on Acoustics, Vol. 1A (NASA-TT-F-15375); p 205-211
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  • 3
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    Calibration effects on orbit determination (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The effects of charged particle and tropospheric calibrations on the orbit determination (OD) process are analyzed. The calibration process consisted of correcting the Doppler observables for the media effects. Calibrated and uncalibrated Doppler data sets were used to obtain OD results for past missions as well as Mariner Mars 1971. Comparisons of these Doppler reductions show the significance of the calibrations. For the MM'71 mission, the media calibrations proved themselves effective in diminishing the overall B-plane error and reducing the Doppler residual signatures.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Tracking System Analytic Calibration Activities for the Mariner Mars 1971 Mission; p 83-96
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  • 4
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    Polynomial smoothing of DRVID data (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Charged particle calibrations based on differenced range versus integrated Doppler (DRVID) are smoothed and fitted with a polynomial prior to its application in the orbit determination process. A description is given of the results of the tests performed on the computer program performing these calculations to determine its characteristics and to evaluate the acceptability of its computations. This program, called MEDIA, is described.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Tracking System Analytic Calibration Activities for the Mariner Mars 1971 Mission; p 97-103
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  • 5
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    Charged particles (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Calibrations compensating for the effects of charged particles in the ionosphere and in the interplanetary medium were applied to the Doppler tracking data acquired during Mariner 9 missions on a demonstration basis. The combined effects of the space plasma and the ionosphere were measured by a comparison of the range and Doppler observables (Differenced Range Versus Integrated Doppler (DRVID). Independent measurements of the ionospheric effects were obtained from polarimeter devices located at the Goldstone, California, tracking complex.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Tracking System Analytic Calibration Activities for the Mariner Mars 1971 Mission; p 43-60
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  • 6
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    Time and polar motion (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The time and polar motion calibration support provided to the MM'71 mission is discussed. Specifically, a description is given of the data gathering system and the data processing system by which calibrations were obtained. An introductory discussion of the effects of timing and polar motion error on spacecraft navigation, along with a description of the system used to support Mariners 6 and 7, is given. A complete discussion of the way in which timing is used in orbit determination is also given.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Tracking System Analytic Calibration Activities for the Mariner Mars 1971 Mission; p 77-82
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  • 7
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    Station locations (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: The extended process of providing station location estimates for use in orbit determination at launch and during the course of the mission, is outlined. Station location sets provided for Mariner Mars 1971 navigation support are given. Data cover set construction, basis for construction, and a comparison of estimated sets with final sets.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Tracking System Analytic Calibration Activities for the Mariner Mars 1971 Mission; p 13-42
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  • 8
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    ERTS operations and data processing (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The overall communications and data flow between the ERTS spacecraft and the ground stations and processing centers are generally described. Data from the multispectral scanner and the return beam vidicon are telemetered to a primary ground station where they are demodulated, processed, and recorded. The tapes are then transferred to the NASA Data Processing Facility (NDPF) at Goddard. Housekeeping data are relayed from the prime ground stations to the Operations Control Center at Goddard. Tracking data are processed at the ground stations, and the calculated parameters are transmitted by teletype to the orbit determination group at Goddard. The ERTS orbit has been designed so that the same swaths of the ground coverage pattern viewed during one 18-day coverage cycle are repeated by the swaths viewed on all subsequent cycles. The Operations Control Center is the focal point for all communications with the spacecraft. NDPF is a job-oriented facility which processes and stores all sensor data, and which disseminates large quantities of these data to users in the form of films, computer-compatible tapes, and data collection system data.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Journal of Environmental Sciences; 17; Mar
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  • 9
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    Ground testing and simulation. II - Aerodynamic testing and simulation: Saving lives, time, and money (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The present work discusses in general terms the various kinds of ground facilities, in particular, wind tunnels, which support aerodynamic testing. Since not all flight parameters can be simulated simultaneously, an important problem consists in matching parameters. It is pointed out that there is a lack of wind tunnels for a complete Reynolds-number simulation. Using a computer to simulate flow fields can result in considerable reduction of wind-tunnel hours required to develop a given flight vehicle.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Astronautics and Aeronautics; 12; June 197
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  • 10
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    Four years of meteor spectra patrol (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The development of the NASA-Langley Research Center meteor spectra patrol is described in general terms. The recording of very faint meteors was made possible by three great strides in optical and photographic technology in the 1960's: (1) the availability of optical-grade fused silica at modest cost, (2) the development of large transmission gratings with high blaze efficiency, and (3) the development of a method for avoiding plate fogging due to background skylight, which consisted of using a photoelectric meteor detector which actuates the spectrograph shutter when a meteor occurs in the field. The classification scheme for meteor spectra developed by Peter M. Millman is described.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Sky and Telescope; 47; June 197
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  • 11
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    Anechoic chamber in industrial plants (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A light anechoic chamber for routine acoustical measurements in the machine building industry is reported. The outer housing of the chamber consists of modules cast in glass fiber reinforced polyester resin; the inner housing consists of pyramidal modules cut out of sound absorbing slates. The parameters of this anechoic chamber facilitate acoustical measurements according to ISO and CAEM recommendations.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: The 4th Natl. Conf. on Acoustic, Vol. 1, C (NASA-TT-F-15376); p 29-31
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  • 12
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    Stand for studying technological processes under conditions simulating space (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A test stand for conducting processing experiments under conditions simulating space is described. The most important units of the stand are discussed. Tests of the stand and research studies using the stand demonstrated that it is a reliable and universal research facility which makes it possible to study processes such as metal melting, welding, and deposition.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Space Studies in the Ukraine, No. 1 (NASA-TT-F-15535); p 1-8
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  • 13
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    Automated life-detection experiments for the Viking mission to Mars (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: As part of the Viking mission to Mars in 1975, an automated set of instruments is being built to test for the presence of metabolizing organisms on that planet. Three separate modules are combined in this instrument so that samples of the Martian surface can be subjected to a broad array of experimental conditions so as to measure biological activity. The first, the Pyrolytic Release Module, will expose surface samples to a mixture of C-14O and C-14O2 in the presence of Martian atmosphere and a light source that simulates the Martian visible spectrum. The assay system is designed to determine the extent of assimilation of CO or CO2 into organic compounds. The Gas Exchange Module will incubate surface samples in a humidified CO2 atmosphere. At specified times, portions of the incubation atmosphere will be analyzed by gas chromatography to detect the release or uptake of CO2 and several additional gases. The Label Release Module will incubate surface samples with a dilute aqueous solution of simple radioactive organic substrates in Martian atmosphere, and the gas phase will be monitored continuously for the release of labeled CO2.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Origin of Life; 5; July-Oct
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  • 14
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    The Langley cryogenic high Reynolds number wind-tunnel program (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A pilot version of a new type of transonic tunnel was placed in operation in the fall of 1973. In the tunnel the cryogenic method is used to obtain a high Reynolds number. The cryogenic concept employs low temperatures to increase the Reynolds number through reducing the viscous forces rather than increasing the inertia forces. The cryogenic approach offers the desired Reynolds-number increase with no increase in dynamic pressure, and therefore no increase in model loads. A series of aerodynamic experiments have been made in the pilot tunnel to confirm the cryogenic concept at transonic speeds. A brief description is given of the project for a large tunnel which has evolved from the investigations.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Astronautics and Aeronautics; 12; Oct. 197
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  • 15
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    Gas flow analysis during thermal vacuum test of a spacecraft (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The self-contamination of the IMP-H spacecraft, while it was undergoing thermal and solar vacuum tests, has been investigated in conjunction with the outgassing evaluation and detection of molecular flow anomalies occurring in the test chamber. The pressures indicated by two tubulated ionization gauges were used to calculate flow kinetics in the vacuum chamber. The fluxes of emitted molecules and chamber wall reflected molecules were monitored during the entire test. Representative equations and graphs are presented. Test results indicate that from 3 to 9 of every 100 emitted molecules returned to the spacecraft surface; that self-contamination by noncondensable gases was more severe than that by condensable gases; and that outgassing of the spacecraft was approximately 1.18 x 0.01 g/s after 10 hours and 1.18 x 0.001 after 90 hours of vacuum exposure. Testing deficiencies have been identified, and the type and location of instruments required to measure the outgassing, the degree of contamination, and return flow are discussed.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TN-D-7492 , G-7346
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  • 16
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    Testing a satellite automatic nutation control system (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Testing of a particular nutation control system for the synchronous meteorological satellite (SMS) is described. The test method and principles are applicable to nutation angle control for other satellites with similar requirements. During its ascent to synchronous orbit, a spacecraft like the SMS spins about its minimum-moment-of-inertia axis. An uncontrolled spacecraft in this state is unstable because torques due to fuel motion increase the nutation angle. However, the SMS is equipped with an automatic nutation control (ANC) system which will keep the nutation angle close to zero. Because correct operation of this system is critical to mission success, it was tested on an air-bearing table. The ANC system was mounted on the three-axis air-bearing table which was scaled to the SMS and equipped with appropriate sensors and thrusters. The table was spun up in an altitude chamber and nutation induced so that table motion simulated spacecraft motion. The ANC system was used to reduce the nutation angle. This dynamic test of the ANC system met all its objectives and provided confidence that the ANC system will control the SMS nutation angle.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TN-D-7596 , G-7426
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  • 17
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    Operation and performance of a lunar laser ranging station (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The Lunar Laser Ranging Experiment has been in continuous operation for about 4 years using the McDonald Observatory 2.7-m telescope. Occupying only a small percentage of the available telescope time, the system is now measuring 350 lunar ranges per year, each with an accuracy of from 10 to 15 cm. This article tabulates the observed signal strengths, the success ratios, and the major operating restrictions that have characterized the daily performance of the experiment. These empirical data can be used to optimize the design of such installations in the future.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Applied Optics; 13; Mar. 197
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  • 18
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    Recognition of three dimensional obstacles by an edge detection scheme (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The need for an obstacle detection system on the Mars roving vehicle was assumed, and a practical scheme was investigated and simulated. The principal sensing device on this vehicle was taken to be a laser range finder. Both existing and original algorithms, ending with thresholding operations, were used to obtain the outlines of obstacles from the raw data of this laser scan. A theoretical analysis was carried out to show how proper value of threshold may be chosen. Computer simulations considered various mid-range boulders, for which the scheme was quite successful. The extension to other types of obstacles, such as craters, was considered. The special problems of bottom edge detection and scanning procedure are discussed.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-139661 , RPI-TR-MP-45
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  • 19
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    Performance evaluation of a second-generation elastic loop mobility system (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were conducted to evaluate the mobility performance of a second-generation Elastic Loop Mobility System (ELMS II). Performance on level test lanes and slopes of lunar soil simulant (LSS) and obstacle-surmounting and crevasse-crossing capabilities were investigated. In addition, internal losses and contact pressure distributions were evaluated. To evaluate the soft-soil performance, two basic soil conditions were tested: loose (LSS1) and dense (LSS5). These conditions embrace the spectrum of soil strengths tested during recent studies for NASA related to the mobility performance of the LRV. Data indicated that for the tested range of the various performance parameters, performance was independent of unit load (contact pressure) and ELMS II drum angular velocity, but was influenced by soil strength and ELMS pitch mode. Power requirements were smaller at a given system output for dense soil than for loose soil. The total system output in terms of pull developed or slope-climbing capability was larger for the ELMS II operating in restrained-pitch mode than in free-pitch mode.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-139531 , M-74-7
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  • 20
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    MSFC Skylab neutral buoyancy simulator (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The use of a neutral buoyancy simulator for developing extravehicular activity systems and for training astronauts in weightless activities is discussed. The construction of the facility and the operations are described. The types of tests and the training activities conducted in the simulator are reported. Photographs of the components of the simulator and actual training exercises are included.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TM-X-64844
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  • 21
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    CVT/GPL phase 2 integrated testing (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experiments representing earth observations, space physics, and material sciences disciplines were installed in the General Purpose Laboratory (GPL). The experiments and the GPL are described. The experiments interfaces the GPL and GPL support systems are assessed. The experiments were cloud physics, ionospheric disturbances, material sciences, high energy astronomy, and superfluid helium.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TM-X-64861
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  • 22
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    Simulators' validation study: Problem solution logic (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study was conducted to validate the ground based simulators used for aircraft environment in ride-quality research. The logic to the approach for solving this problem is developed. The overall problem solution flow chart is presented. The factors which could influence the human response to the environment on board the aircraft are analyzed. The mathematical models used in the study are explained. The steps which were followed in conducting the validation tests are outlined.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-138305 , MEMO-403213
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  • 23
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    The cryogenic wind tunnel for high Reynolds number testing (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experiments performed at the NASA Langley Research Center in a cryogenic low-speed continuous-flow tunnel and in a cryogenic transonic continuous-flow pressure tunnel have demonstrated the predicted changes in Reynolds number, drive power, and fan speed with temperature, while operating with nitrogen as the test gas. The experiments have also demonstrated that cooling to cryogenic temperatures by spraying liquid nitrogen directly into the tunnel circuit is practical and that tunnel temperature can be controlled within very close limits. Whereas most types of wind tunnel could operate with advantage at cryogenic temperatures, the continuous-flow fan-driven tunnel is particularly well suited to take full advantage of operating at these temperatures. A continuous-flow fan-driven cryogenic tunnel to satisfy current requirements for test Reynolds number can be constructed and operated using existing techniques. Both capital and operating costs appear acceptable.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TM-X-70207
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  • 24
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    System design optimization for a Mars-roving vehicle and perturbed-optimal solutions in nonlinear programming (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Work in two somewhat distinct areas is presented. First, the optimal system design problem for a Mars-roving vehicle is attacked by creating static system models and a system evaluation function and optimizing via nonlinear programming techniques. The second area concerns the problem of perturbed-optimal solutions. Given an initial perturbation in an element of the solution to a nonlinear programming problem, a linear method is determined to approximate the optimal readjustments of the other elements of the solution. Then, the sensitivity of the Mars rover designs is described by application of this method.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-138817 , RPI-TR-MP-43
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  • 25
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    Low-cost, air mass 2 solar simulator (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A low cost air mass 2 solar simulator for testing flat-plate solar collectors was developed and operated at Lewis. Total cost was less than $10,800/sq m ($1000/sq ft). It consists of an array of 143 tungsten-halogen 300-watt lamps, each having integral dichroic coated reflectors. A second array of 143 respective hexagonal-shaped plastic Fresnel lenses are located approximately 1 focal length from the lamps. The simulator will produce a uniform collimated beam covering an area of 1.2 by 1.2m(4 by 4 ft). Design features, construction details, and component costs are given, as well as measured results on a 12-lamp prototype.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TM-X-3059 , E-7885
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  • 26
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    Design features and operational characteristics of the Langley pilot transonic cryogenic tunnel (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A fan-driven transonic cryogenic tunnel was designed, and its purging, cooldown, and warmup times were determined satisfactory. Cooling with liquid nitrogen is at the power levels required for transonic testing. Good temperature distributions are obtained by using a simple nitrogen injection system.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TM-X-72012
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  • 27
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    Calibration of the Langley 16-foot transonic tunnel with test section air removal (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Langley 16-foot transonic tunnel with test section air removal (plenum suction) was calibrated to a Mach number of 1.3. The results of the calibration, including the effects of slot shape modifications, test section wall divergence, and water vapor condensation, are presented. A complete description of the wind tunnel and its auxiliary equipment is included.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TR-R-423 , L-9326
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  • 28
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    KSC maintenance capability (laboratories and shops) (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A summary of laboratory and shop facilities at Kennedy Space Center that are available to provide a baseline to the offline maintenance requirements for the space shuttle program is provided.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TM-X-70380 , KSC-GP-1037
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  • 29
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    Dynamic Docking Test System (DDTS) active table frequency response test results (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results are presented of the frequency response test performed on the dynamic docking test system (DDTS) active table. Sinusoidal displacement commands were applied to the table and the dynamic response determined from measured actuator responses and accelerometers mounted to the table and one actuator.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-140285 , D2-118546-1
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  • 30
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    Mathematical model for the simulation of Dynamic Docking Test System (DDST) active table motion (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The mathematical model developed to describe the three-dimensional motion of the dynamic docking test system active table is described. The active table is modeled as a rigid body supported by six flexible hydraulic actuators which produce the commanded table motions.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-140288 , D2-118544-1
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  • 31
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    Analyses of the dynamic docking test system for advanced mission docking system test programs (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results are given of analytical studies performed in support of the design, implementation, checkout and use of NASA's dynamic docking test system (DDTS). Included are analyses of simulator components, a list of detailed operational test procedures, a summary of simulator performance, and an analysis and comparison of docking dynamics and loads obtained by test and analysis.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-140286 , D2-118470-2
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  • 32
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    A new wideband, fully steerable, decametric array at Clark Lake (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A new, fully steerable, decametric array for radio astronomy is under construction at the Clark Lake Radio Observatory near Borrego Springs, California. This array will be a T of 720 conical spiral antennas (teepee-shaped antennas, hence the array is called the TPT), 3.0 by 1.8 km capable of operating between 15 and 125 MHz. Both its operating frequency and beam position will be adjustable in less than one msec, and the TPT will provide a 49-element picture around the central beam position for extended-source observations. Considerable experience has been gained in the operation of completed portions of the array, and successful operation of the final array is assured. This paper describes the results of the tests which have been conducted with the conical spirals and outlines the planned electronics.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Radio Science; 9; Mar. 197
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    Skylab extravehicular mobility unit thermal simulator (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The analytical methods, thermal model, and user's instructions for the Skylab Extravehicular Mobility Unit (SEMU) routine are presented. This digital computer program was developed for detailed thermal performance predictions of the SEMU on the NASA-JSC Univac 1108 computer system. It accounts for conductive, convective, and radiant heat transfer as well as fluid flow and special component characterization. The program provides thermal performance predictions for a 967 node thermal model in one thirty-sixth (1/36) of mission time when operated at a calculating interval of three minutes (mission time). The program has the operational flexibility to: (1) accept card or magnetic tape data input for the thermal model describing the SEMU structure, fluid systems, crewman and component performance, (2) accept card and/or magnetic tape input of internally generated heat and heat influx from the space environment, and (3) output tabular or plotted histories of temperature, flow rates, and other parameters describing system operating modes.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-134389 , T194-06
    Format: application/pdf
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    A wind model for an elevated STOL-port configuration (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Measurements of mean velocity magnitude and direction as well as three-dimensional turbulence intensity were made in the flow over a model of an elevated STOL-port. A 1:300 scale model was placed in a wind tunnel flow simulating the mean velocity profile and turbulence characteristics of atmospheric winds over a typical city environment excluding detailed wake structures of possible nearby buildings. Hot-wire anemometer measurements of velocity and turbulence were made along approach and departure paths of aircraft operating on the runway centerline and at specified lateral distances from the centerline. Approach flow directions simulated were 0 and 30 degrees to the runway centerline.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-2450
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    The use of an aircraft test stand for VTOL handling qualities studies (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The VTOL flight tests stand for testing control concepts on the X-14B VSS aircraft in hover, is described. This stand permits realistic and safe piloted evaluation and checkout of various control systems and of parameter variations within each system to determine acceptability to the pilot. Pilots can use it as a practical training tool to practice procedures and flying techniques and become familiar with the aircraft characteristics. Some examples of test experience are given. The test stand allows the X14B to maneuver in hover from centered position + or - 9.7 deg in roll and + or - 9.3 deg in pitch, about + or - 6 deg in yaw, and + or - 15 cm in vertical translation. The unique vertical free flight freedom enables study of liftoffs and landings with power conditions duplicated. The response on the stand agrees well with that measured in free hovering flight, and pilot comments confirm this.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TM-X-62218
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    NASA Lewis 8 by 6 foot supersonic wind tunnel (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Performance data are presented for the tunnel, which has a Mach number range from 0.36 to 2.0. The tunnel circuit, test section, model support systems, auxiliary systems, instrumentation, control room equipment, and automatic recording and computing equipment are also described. Information is presented on criteria for designing models and on shop facilities available to prospective users.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TM-X-71542 , E-7949
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    Mission and spacecraft support functions of the Materials Engineering Branch: A space oriented technology resource (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The capabilities of the Materials Engineering Branch (MEB) of the Goddard Space Flight Center, Greenbelt, Maryland, are surveyed. The specific functions of spacecraft materials review, materials processing and information dissemination, and laboratory support, are outlined in the Activity Report. Further detail is provided by case histories of laboratory satellite support and equipment. Project support statistics are shown, and complete listings of MEB publications, patents, and tech briefs are included. MEB staff, and their respective discipline areas and spacecraft liaison associations, are listed.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TM-X-70663 , X-755-74-152
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    Operating characteristics of the Langley Mach 10 high Reynolds number helium tunnel (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Operating characteristics of the Langley Mach 10 high Reynolds number helium tunnel are presented for stagnation pressures from 138 N/sq cm to 1655 N/sq cm. The characteristics include detailed Mach number surveys in the test section from which usable core size and regions of disturbed flow were determined, preliminary blockage test results, and maximum run time to be expected at various stagnation pressures. Important tunnel dimensions including details of the model mounting apparatus are given. Measurements show the variation in average core Mach number in the test section to be between 9.4 and 10 for the present range of test conditions. The core radius is from 23 cm to 31.5 cm, depending on stagnation pressure and axial location in the test section.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TM-X-2955 , L-9259
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  • 39
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    Photolysis of spacecraft contaminants (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A molecular beam facility, which was designed to measure photochemical cross-sections, has been constructed at the Athens College science facility. The integration of this vacuum system into an operational photochemical instrument was performed with signal processing consisting of both dc and ac techniques. Of the experiments performed to date on the vacuum ultraviolet photolysis of water vapor, it is apparent that a larger pumping capacity (preferably with differential pumping) is required to improve upon the background signal. Both phase-sensitive detection and ion-counting techniques are recommended for future studies.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-129026
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  • 40
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    Time-dependent polar distribution of outgassing from a spacecraft (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A technique has been developed to obtain a characterization of the self-generated environment of a spacecraft and its variation with time, angular position, and distance. The density, pressure, outgassing flux, total weight loss, and other important parameters were obtained from data provided by two mass measuring crystal microbalances, mounted back to back, at distance of 1 m from the spacecraft equivalent surface. A major outgassing source existed at an angular position of 300 deg to 340 deg, near the rocket motor, while the weakest source was at the antennas. The strongest source appeared to be caused by a material diffusion process which produced a directional density at 1 m distance of about 1.6 x 10 to the 11th power molecules/cu cm after 1 hr in vacuum and decayed to 1.6 x 10 to the 9th power molecules/cu cm after 200 hr. The total average outgassing flux at the same distance and during the same time span changed from 1.2 x 10 to the minus 7th power to 1.4 x to the minus 10th power g/sq cm/s. These values are three times as large at the spacecraft surface. Total weight loss was 537 g after 10 hr and about 833 g after 200 hr. Self-contamination of the spacecraft was equivalent to that in orbit at about 300-km altitude.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TN-D-7597 , G-7419
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    Viking '79 Rover study. Volume 2: Detailed technical report (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N74-19888.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-132418
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    Viking '79 Rover study. Volume 1: Summary report (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a study to define a roving vehicle suitable for inclusion in a 1979 Viking mission to Mars are presented. The study focused exclusively on the 1979 mission incorporating a rover that would be stowed on and deployed from a modified Viking lander. The overall objective of the study was to define a baseline rover, the lander/rover interfaces, a mission operations concept, and a rover development program compatible with the 1979 launch opportunity. During the study, numerous options at the rover system and subsystem levels were examined and a baseline configuration was selected. Launch vehicle, orbiter, and lander performance capabilities were examined to ensure that the baseline rover could be transported to Mars using minimum-modified Viking '75 hardware and designs.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-132417
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    Linear Test Bed. Volume 2: Test Bed No. 2 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Test bed No. 2 consists of 10 combustors welded in banks of 5 to 2 symmetrical tubular nozzle assemblies, an upper stationary thrust frame, a lower thrust frame which can be hinged, a power package, a triaxial combustion wave ignition system, a pneumatic control system, pneumatically actuated propellant valves, a purge and drain system, and an electrical control system. The power package consists of the Mark 29-F fuel turbopump, the Mark 29-0 oxidizer turbopump, a gas generator assembly, and propellant ducting. The system, designated as a linear aerospike system, was designed to demonstrate the feasibility of the concept and to explore technology related to thrust vector control, thrust vector optimization, improved sequencing and control, and advanced ignition systems. The propellants are liquid oxygen/liquid hydrogen. The system was designed to operate at 1200-psia chamber pressure at an engine mixture ratio of 5.5. With 10 combustors, the sea level thrust is 95,000 pounds.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-120183 , R-9049-VOL-2
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    A practical obstacle detection system for the Mars Rover (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Discussion of an obstacle detection system which uses a laser range finder as the principal sensing device. The laser scans the scene ahead and stores the range data for the terrain in a matrix form. This matrix can be thought of as a 'range image'. This range varies from point to point, but sharp changes are caused by the presence of obstacles. Some existing algorithms and one developed by the authors were used to obtain the outlines of obstacles from the 'range image'. All these algorithms end with a thresholding operation. A theoretical analysis shows how a proper value of the threshold may be chosen, given the type of irregularity of the terrain to be detected. The analysis also shows how large the statistics of measurement noise can be allowed without leading to false alarms.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Milwaukee Symposium on Automatic Control; Mar 28, 1974 - Mar 30, 1974; Milwaukee, WI
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  • 45
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    Measurement of dynamic cross-derivatives due to pitching and yawing (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A novel wind-tunnel apparatus is described with which all the 12 static and dynamic moment derivatives due to pitching and yawing can be obtained at angles of attack up to 40 deg and in the presence of some sideslip. The experimental technique and the data reduction procedure are discussed, and preliminary data on dynamic derivatives for an aircraft-like configuration at M ? 0.70 are presented. It is shown that in the range of angle of attack investigated, some rather large variations occur in both the two direct damping derivatives and some of the dynamic cross-derivatives; the latter, however, remain small as compared to the corresponding direct damping derivatives (in general less than 10%).
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: AIAA PAPER 74-611 , Aerodynamic Testing Conference; Jul 08, 1974 - Jul 10, 1974; Bethesda, MD
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    Optimization of spacecraft high temperature outgassing duration (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Spacecraft systems are baked-out under vacuum to remove occluded and adsorbed gases, solvents, water, plasticizer, and other materials acquired during their manufacture. Two bakeouts of solar panels were carried out. Quartz crystal microbalances installed in the vacuum chamber during the tests and held at 273 K (0 C) provided an ongoing measure of the panels' outgassing. From these data, the panels' material weight losses versus time were obtained. A comparison of the total weight loss expected during a relatively long bakeout with that accomplished during a reasonable period of time was used as a criteria for an acceptable duration of the bakeout in order to optimize cost effectiveness.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Annual Meeting on the Cost effectiveness in the environmental sciences; Apr 28, 1974 - May 01, 1974; Washington, DC
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  • 47
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    Selection of appropriate test method for simulating steady-state spacecraft launch loads (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: In ground testing prior to launch the static loads portion of the launch profile may be simulated by either applying static loads directly to the spacecraft through an appropriate loading facility or by subjecting the spacecraft to acceleration loads on a centrifuge. The factors to be considered in selecting one of the two simulation methods are discussed, giving attention to the relative advantages of the two methods in each case.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Annual Meeting on the Cost effectiveness in the environmental sciences; Apr 28, 1974 - May 01, 1974; Washington, DC
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  • 48
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    The use of large cylindrical enclosures as a cost effective approach to reverberant acoustic testing (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The feasibility of using existing cylindrical enclosures as cost effective substitutes for reverberant acoustic test chambers is investigated. In particular the performance of two large cylindrical environmental chambers, 1400 and 14,000 cu m in volume, is evaluated in detail. Reverberant acoustic chamber characteristics are predicted using classical acoustic theory and are compared to results obtained from actual chamber measurements. A method of scaling low level test results to predict the performance of a particular driver/horn/chamber configuration is also discussed. This prediction technique is confirmed by actual test data using a 200 kilowatt acoustic generator.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Annual Meeting on the Cost effectiveness in the environmental sciences; Apr 28, 1974 - May 01, 1974; Washington, DC
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  • 49
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    Skylab facilities modifications at KSC (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The facilities required at KSC to support Skylab were largely those facilities used by Apollo, modified for Skylab's particular needs. The one exception is the series of modifications to permit launching a Saturn IB from Complex 39. This new capability not only supported Skylab, but also supports the upcoming Apollo Soyuz, and any further S-IB launches that might be undertaken.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: AAS PAPER 74-148 , Annual Meeting; Aug 20, 1974 - Aug 22, 1974; Los Angeles, CA
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    URSIES and the Bartol Coude Observatory (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: European Astronomical Meeting; Sep 04, 1972 - Sep 09, 1972; Athens; Greece
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  • 51
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    Automated microbial metabolism laboratory (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The design and rationale of an advanced labeled release experiment based on single addition of soil and multiple sequential additions of media into each of four test chambers are outlined. The feasibility for multiple addition tests was established and various details of the methodology were studied. The four chamber battery of tests include: (1) determination of the effect of various atmospheric gases and selection of that gas which produces an optimum response; (2) determination of the effect of incubation temperature and selection of the optimum temperature for performing Martian biochemical tests; (3) sterile soil is dosed with a battery of C-14 labeled substrates and subjected to experimental temperature range; and (4) determination of the possible inhibitory effects of water on Martian organisms is performed initially by dosing with 0.01 ml and 0.5 ml of medium, respectively. A series of specifically labeled substrates are then added to obtain patterns in metabolic 14CO2 (C-14)O2 evolution.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-138146
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    Scientific and administrative activities at the Lunar Science Institute (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The scientific and administrative activities of the Lunar Science Institute during the period 15 July through 31 December 1973 are reported. The subjects discussed are: (1) contributions of the organization, (2) organization of the staff, (3) administration functions, and (4) scientific and professional meetings held at the institute.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-137081
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    Carbon rod furnace infrared source (1974)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A carbon rod furnace infrared source has been built and has proven to be a reliable and trouble-free source despite the high rod temperature of 2500 K. The furnace offers several advantages over previous furnaces. These include an increase in usable rod length to 6.35 cm, extended rod life, and a fully automated power supply for the furnace. Construction and operational details are discussed.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Review of Scientific Instruments; 45; Oct. 197
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    GSFC Venus atmosphere simulator (1974)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The design and preliminary testing of a Venus Atmosphere Simulation System are described. The system was designed for testing a quadrupole mass spectrometer proposed for the Pioneer-Venus Experiment. The system is capable of providing programmed temperature cycles up to 550 C, and manually controlled pressure up to 100 atmospheres.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TM-X-70739 , X-753-74-229
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  • 55
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    The effect of wind tunnel wall interference on the performance of a fan-in-wing VTOL model (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A fan-in-wing model with a 1.07-meter span was tested in seven different test sections with cross-sectional areas ranging from 2.2 sq meters to 265 sq meters. The data from the different test sections are compared both with and without correction for wall interference. The results demonstrate that extreme care must be used in interpreting uncorrected VTOL data since the wall interference may be so large as to invalidate even trends in the data. The wall interference is particularly large at the tail, a result which is in agreement with recently published comparisons of flight and large scale wind tunnel data for a propeller-driven deflected-slipstream configuration. The data verify the wall-interference theory even under conditions of extreme interference. A method yields reasonable estimates for the onset of Rae's minimum-speed limit. The rules for choosing model sizes to produce negligible wall effects are considerably in error and permit the use of excessively large models.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TN-D-7518 , L-9202
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    A forward speed effects study on jet noise from several suppressor nozzles in the NASA/Ames 40- by 80-foot wind tunnel (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A test program was conducted in a 40 by 80 foot wind tunnel to evaluate the effect of relative velocity on the jet noise signature of a conical ejector, auxiliary inlet ejector, 32 spokes and 104 tube nozzle with and without an acoustically treated shroud. The freestream velocities in the wind tunnel were varied from 0 to 103.6 m/sec (300 ft/sec) for exhaust jet velocities of 259.1 m/sec (850 ft/sec) to 609.6 m/sec (2000 ft/sec). Reverberation corrections for the wind tunnel were developed and the procedure is explained. In conjunction with wind tunnel testing the nozzles were also evaluated on an outdoor test stand. The wind tunnel microphone arrays were duplicated during the outdoor testing. The data were then extrapolated for comparisons with data measured using a microphone array placed on a 30.5 meter (100 ft) arc. Using these data as a basis, farfield to nearfield arguments are presented with regards to the data measured in the wind tunnel. Finally, comparisons are presented between predictions made using existing methods and the measured data.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-114741
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    Path selection system development and evaluation for a Martian roving vehicle (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A path selection system evaluation test procedure has been developed to enhance the analysis capability of an existing digital computer simulation package. The procedure investigates the obstacle avoidance ability of a path selection system on a sequence of test terrains with and without random effects. Using the standard test procedure a proposed mid-range sensor system has been evaluated and recommendations directed at improving the performance of the system have been made. In addition, the initial development and evaluation of a short range sensor system has been undertaken.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-138588 , RPI-TR-MP-42
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  • 58
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    Tracking system analytic calibration activities for the Mariner Mars 1971 mission (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Data covering various planning aspects of Mariner Mars 1971 mission are summarized. Data cover calibrating procedures for tracking stations, radio signal propagation in the troposphere, effects of charged particles on radio transmission, orbit calculation, and data smoothing.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-136826 , JPL-TR-32-1587
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  • 59
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    First heated jettison test on the Centaur standard shroud (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The first in a planned series of heated jettison tests on the Centaur Standard Shround was conducted at NASA Plum Brook Station's Space Power Facility on November 19, 1973. The first 250-second portion of the test sequence involved heating the shroud with a specially-built fixture designed to provide a simulation of the heating environment encountered by the shroud during its ascent through the earth's atmosphere. The two heater halves, which were mounted on a rail system, were then retracted. This was followed by the jettison of the two shroud halves into catch nets positioned at 90 deg to the heater rails. The condition which made this test unique compared to the planned subsequent tests was the location of the maximum thermal line at 32 deg from the shroud separation plane. Information on the test hardware, configuration, and sequence is presented. Shroud thermal and deflection data encountered during the heating portion of the test sequence is compared with free-skin design temperatures in various graphical formats.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TM-X-71501 , E-7868
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    Generalized dynamic engine simulation techniques for the digital computer (1974)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: Recently advanced simulation techniques have been developed for the digital computer and used as the basis for development of a generalized dynamic engine simulation computer program, called DYNGEN. This computer program can analyze the steady state and dynamic performance of many kinds of aircraft gas turbine engines. Without changes to the basic program, DYNGEN can analyze one- or two-spool turbofan engines. The user must supply appropriate component performance maps and design-point information. Examples are presented to illustrate the capabilities of DYNGEN in the steady state and dynamic modes of operation. The analytical techniques used in DYNGEN are briefly discussed, and its accuracy is compared with a comparable simulation using the hybrid computer. The impact of DYNGEN and similar all-digital programs on future engine simulation philosophy is also discussed.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Propulsion and Energetics Meeting; Sept. 9-13, 1974; Ankara; Turkey
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    Electronic displays and digital automatic control in advanced terminal area operations (1974)
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    Publication Date: 2019-07-13
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: AIAA PAPER 74-27 , Aerospace Sciences Meeting; Jan 30, 1974 - Feb 01, 1974; Washington, DC
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    Solar simulator mirror refurbishment (1974)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: Solar simulator mirrors were refurbished. Two different refurbishment methods were employed. In the first, the electroformed mirror replica was removed from the casting and replaced with a new mirror replica. In the second, only the aluminized surface, with its protective overcoat, was removed from the mirror and replaced after cleaning of the nickel surface.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-140298 , XEOS-2304
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    Mississippi Test Facility research projects (1974)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: Research capabilities of Louisiana State University are reported for sustaining a program which complements the Mississippi Test Facility. Projects reported during this period are discussed and include the development of a spectral analyzer, and investigations of plant physiology. Papers published during this period are also listed.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-139370
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  • 64
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    Facility research capabilities at Louisiana State University (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Efforts of LSU are reported to develop research capabilities for supporting the NASA Mississippi Test Facility. Research activities reported include remote sensing technology and salt water encroachment.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-138884
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  • 65
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    A comparative evaluation of three types of acoustic noise generators (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Assessment of the operation and performance characteristics of three acoustic noise generators (a siren, an electropneumatic modulator, and an electrohydraulic modulator) when used in conjunction with a progressive wave tube. Particularly, the spectrum shaping capabilities and efficiencies of the three generators are compared.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Annual Meeting on the Cost effectiveness in the environmental sciences; Apr 28, 1974 - May 01, 1974; Washington, DC
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  • 66
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    Cost effectiveness as applied to the Viking Lander systems-level thermal development test program (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The economic aspects of thermal testing at the systems-level as applied to the Viking Lander Capsule thermal development program are reviewed. The unique mission profile and pioneering scientific goals of Viking imposed novel requirements on testing, including the development of a simulation technique for the Martian thermal environment. The selected approach included modifications of an existing conventional thermal vacuum facility, and improved test-operational techniques that are applicable to the simulation of the other mission phases as well, thereby contributing significantly to the cost effectiveness of the overall thermal test program.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Annual Meeting on the Cost effectiveness in the environmental sciences; Apr 28, 1974 - May 01, 1974; Washington, DC
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  • 67
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    A study of relationships between performance in system tests and space (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Approaches for measuring the effectiveness of tests and test programs are considered, taking into account system test effectiveness, thermal-vacuum test effectiveness, and vibration test effectiveness. Methods for predicting space performance on the basis of system test effectiveness are discussed along with aspects of defect detection in thermal-vacuum tests. Questions regarding the thermal-vacuum test costs in relation to the probability of early space failures are also explored.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Annual Meeting on the Cost effectiveness in the environmental sciences; Apr 28, 1974 - May 01, 1974; Washington, DC
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  • 68
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    A statistical approach to deriving subsystem specifications (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: In order to produce cost effective environmental test programs, the test specifications must be realistic and to be useful, they must be available early in the life of a program. This paper describes a method for achieving such specifications for subsystems by utilizing the results of a statistical analysis of data acquired at subsystem mounting locations during system level environmental tests. The paper describes the details of this statistical analysis. The resultant recommended levels are a function of the subsystems' mounting location in the spacecraft. Methods of determining this mounting 'zone' are described. Recommendations are then made as to which of the various problem areas encountered should be pursued further.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Annual Meeting on the Cost effectiveness in the environmental sciences; Apr 28, 1974 - May 01, 1974; Washington, DC
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  • 69
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    Workmanship vibration test of the SAS-B spacecraft (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The occurrence of a technical problem made it necessary to remove the transmitter from the SAS-B spacecraft. The transmitter was repaired and reinstalled in the spacecraft. After this operation it was necessary to test the mechanical properties of the reassembled spacecraft in a vibration test to be conducted near the spacecraft launching place on the San Marco Range in the Indian Ocean. A vibration system was, therefore, sent to San Marco. The design of the vibration system is discussed, giving attention also to alternative solutions for conducting the required tests.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Annual Meeting on the Cost effectiveness in the environmental sciences; Apr 28, 1974 - May 01, 1974; Washington, DC
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  • 70
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    A directional microphone array for acoustic studies of wind tunnel models (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An end-fire microphone array that utilizes a digital time delay system has been designed and evaluated for measuring noise in wind tunnels. The directional response of both a four- and eight-element linear array of microphones has enabled substantial rejection of background noise and reverberations in the NASA Ames 40- by 80-foot wind tunnel. In addition, it is estimated that four- and eight-element arrays reject 6 and 9 dB, respectively, of microphone wind noise, as compared with a conventional omnidirectional microphone with nose cone. Array response to two types of jet engine models in the wind tunnel is presented. Comparisons of array response to loudspeakers in the wind tunnel and in free field are made.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: AIAA PAPER 74-640 , Aerodynamic Testing Conference; Jul 08, 1974 - Jul 10, 1974; Bethesda, MD
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  • 71
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    Experimental evaluation of an injector system for powering a high Reynolds number transonic wind tunnel (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The problems of powering a large, high-Reynolds number transonic wind tunnel are briefly reviewed, and the advantages of an injector drive system are presented. This paper is based on the results of an experimental investigation of a series of injector configurations and test variables using a pilot wind tunnel with a 6-in.-diameter test section. The purpose of this investigation is to determine the efficiency and flow quality of an injector driven wind tunnel and develop configurations that will reduce the initial cost of a wind tunnel without seriously reducing efficiency and flow quality. The results indicate that high efficiencies can be obtained and that injector drive does not compromise flow quality in a transonic wind tunnel.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: AIAA PAPER 74-632 , Aerodynamic Testing Conference; Jul 08, 1974 - Jul 10, 1974; Bethesda, MD
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  • 72
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    Experimental feasibility study of the application of magnetic suspension techniques to large-scale aerodynamic test facilities (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Based on the premises that (1) magnetic suspension techniques can play a useful role in large-scale aerodynamic testing and (2) superconductor technology offers the only practical hope for building large-scale magnetic suspensions, an all-superconductor three-component magnetic suspension and balance facility was built as a prototype and was tested successfully. Quantitative extrapolations of design and performance characteristics of this prototype system to larger systems compatible with existing and planned high Reynolds number facilities have been made and show that this experimental technique should be particularly attractive when used in conjunction with large cryogenic wind tunnels.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: AIAA PAPER 74-615 , Aerodynamic Testing Conference; Jul 08, 1974 - Jul 10, 1974; Bethesda, MD
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  • 73
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    Jupiter entry simulation with the ANAA shock tube (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An annular arc accelerator (ANAA) shock tube has been built which produces shock velocities and pressures that simulate entry into the atmosphere of Jupiter. The ANAA driver deposits the energy of an arc discharge into a flowing gas, which then expands and cools without any delay for the opening of a diaphragm. A flow transducer, trigger system, and spark gap switches have been developed to coordinate the flow from a high-pressure helium driver with the discharge from a 300-kJ capacitor bank. Shock velocities up to 47 km/sec have been produced in 1.0 torr of hydrogen with the ANAA shock tube, compared with 35 km/sec velocity produced in a conical arc driver with three times the available energy. Attenuation with the ANAA shock tube is comparable to that of a conical arc driver shock tube, and initial spectroscopic measurements indicate that an impurity-free test slug is formed behind the shock wave.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: AIAA PAPER 74-610 , Aerodynamic Testing Conference; Jul 08, 1974 - Jul 10, 1974; Bethesda, MD
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  • 74
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    Design and control considerations for industrial and space manipulators (1974)
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    Publication Date: 2019-07-13
    Description: This paper is a progress report summarizing theoretical and practical results concerning integration of design and control aspects of manipulator arms for industrial or space applications. The relationships between task specifications, gross motions, fine motions, actuator type and location, size and strength of structural members, control servos and strategies, and overall design evaluation are briefly discussed, with some technical examples.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Joint Automatic Control Conference; Jun 18, 1974 - Jun 21, 1974; Austin, TX
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  • 75
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    New design and operating techniques for improved terminal area compatibility (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Current aircraft operating problems that must be alleviated for future high-density terminal areas are safety, dependence on weather, congestion, energy conservation, noise, and atmospheric pollution. The microwave landing system (MLS) under development by FAA provides increased capabilities over the current ILS. It is, however, necessary and urgent to develop the airborne system's capability to take maximum advantage of the MLS capabilities in order to solve the terminal area problems previously mentioned. A major limiting factor in longitudinal spacing for capacity increase is the trailing vortex hazard. Promising methods for causing early dissipation of the vortices are being explored. Also, flight procedures for avoiding the hazard will be explored.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: SAE PAPER 740454 , Air Transportation Meeting; Apr 30, 1974 - May 02, 1974; Dallas, TX
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  • 76
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    The use of a multi-processor minicomputer for communication system simulation (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An experimental facility is described which allows new computer communications techniques to be tested under conditions closely approximating those of real systems. A three-processor minicomputer configuration is used to achieve real-time operation at channel transmission rates of up to 50 Kbits per second. One processor runs a channel controller-concentrator program, a second is dedicated to simulation of the communication channel characteristics, and the third to the simulation of up to 1000 user terminals. The latter are divided into classes consisting of interactive time-sharing users of differing characteristics and file nodes, mixed in different proportions. Real user nodes are connected to the channel simulator processor, providing experience with actual operating characteristics under different channel loadings.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Asilomar Conference on Circuits, Systems, and Computers; Nov 27, 1973 - Nov 29, 1973; Pacific Grove, CA
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  • 77
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    Serpentuator simulation using MARSYAS (1974)
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    Publication Date: 2019-07-13
    Description: The Serpentuator is a serpentine teleoperator device for intraand extravehicular activities in space. It is simulated using the digital simulation software MARSYAS. Direct Simulation (DS) and Component-Connection Simulation (CCS) models are set up. The simulation execution time for the CCS model is less than that of the DS model by a factor of the order of 100. A visual display of the Serpentuator positions is obtained using AMTRAN.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Asilomar Conference on Circuits, Systems, and Computers; Nov 27, 1973 - Nov 29, 1973; Pacific Grove, CA
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  • 78
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    NASA, Langley Impact Dynamics Facility (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Description of an impact dynamics facility that will be used to crash test full-scale light aircraft. The aircraft are crashed into the ground as free bodies, using a pendulum swing method to obtain desired flightpath angles and velocities. The aircraft are unrestrained during impact to obtain realistic reactions. Accelerations and strains of the aircraft structure are measured during impact. The crash sequence and structural deformations are obtained by external and internal camera coverage.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: SAE PAPER 740374 , Business Aircraft Meeting; Apr 02, 1974 - Apr 05, 1974; Wichita, KS
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  • 79
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    The M.I.T. Blowdown compressor facility (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A blowdown compressor test facility has been developed which allows time-resolved aerodynamic testing of full-scale transonic compressor rotors at low cost. The rotor is brought to speed in vacuum, a diaphragm is opened, and the test gas is allowed to flow for a time of the order of 0.1 sec, during which the rotor is driven by its own inertia. Both 'steady-state' performance evaluation and detailed time resolution of the flow on the blade-passing time scale have been demonstrated for a two-ft-diam transonic rotor with a tangential Mach number of 1.2 and a nominal pressure ratio of 1.6. The steady-state performance as determined in the experiments includes an efficiency of 0.92 and a pressure ratio of 1.55 at design speed. The time-resolved measurements include the combination tone structure in the upstream flow field, resolved both axially and radially, and the wake structure downstream of the rotor, also resolved both radially and axially.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: ASME PAPER 74-GT-47 , Gas Turbine Conference and Products Show; Mar 30, 1974 - Apr 04, 1974; Zurich; Switzerland
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  • 80
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    Acoustic chamber for weightless positioning (1974)
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    Publication Date: 2019-07-13
    Description: The objective of this work is to perfect and extend the acoustic position technique that was developed at JPL for use in the future Space Processing Laboratory in Space. The main effort is centered on design of a position device for processing of molten materials. Namely, a resonator has the capability of positioning in an extreme temperature gradient and a frequency servo loop to maintain it there as the temperature varies.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: AIAA PAPER 74-155 , Aerospace Sciences Meeting; Jan 30, 1974 - Feb 01, 1974; Washington, DC
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  • 81
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    Flight simulation characteristics of the Langley high Reynolds number cryogenic transonic tunnel (1974)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The characteristics of the Langley 34 cm (13.5 in.) pilot cryogenic transonic pressure tunnel are described, and the results of initial tunnel operation are presented. Tests of a two-dimensional airfoil at a Mach number of 0.85 show identical pressure distributions for a chord Reynolds number of 8,600,000 obtained first at a stagnation pressure of 4.91 atmospheres at a stagnation temperature of +120 F and then at a stagnation pressure of 1.19 atmospheres at a stagnation temperature of -250 F.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: AIAA PAPER 74-80 , Aerospace Sciences Meeting; Jan 30, 1974 - Feb 01, 1974; Washington, DC
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  • 82
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    The NASA Langley building solar project and the supporting Lewis solar technology program (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The use of solar energy to heat and cool a new office building that is now under construction is reported. Planned for completion in December 1975, the 53,000 square foot, single story building will utilize 15,000 square feet of various types of solar collectors in a test bed to provide nearly all of the heating demand and over half of the air conditioning demand. Drawing on its space-program-developed skills and resources in heat transfer, materials, and systems studies, NASA-Lewis will provide technology support for the Langley building project. A solar energy technology program underway at Lewis includes solar collector testing in an indoor solar simulator facility and in an outdoor test facility, property measurements of solar panel coatings, and operation of a laboratory-scale solar model system test facility. Based on results obtained in this program, NASA-Lewis will select and procure the solar collectors for the Langley test bed.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TM-X-71600 , E-8075 , Intern. Solar Energy Soc. Meeting; Aug 19, 1974 - Aug 23, 1974; Fort Collins, CO; United States
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  • 83
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    Analysis and design of a capsule landing system and surface vehicle control system for Mars exploration (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A number of problems related to the design, construction and evaluation of an autonomous roving planetary vehicle and its control and operating systems intended for an unmanned exploration of Mars are studied. Vehicle configuration, dynamics, control, systems and propulsion; systems analysis; terrain sensing and modeling and path selection; and chemical analysis of samples are included.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-CR-138818 , RPI-TR-MP-44
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  • 84
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    Electromagnetic position sensor for a magnetically supported model in a wind tunnel (1973)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: An investigation was undertaken to determine the feasibility of using superconducting force-producing coils for positioning a model in a wind tunnel. The cryostat containing the forcing coils surrounded the test section of the tunnel, thus favoring an electromagnetic position sensor. Another reason favoring this choice was the fact that the performance of an electromagnetic sensor is essentially unaffected by the shape of the model.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Develop. of a Superconducting Electromagnetic Suspension and Balance System for Dyn. Stability Studies; 4 p
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  • 85
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    Safety aspects of superconducting magnetic suspension systems (1973)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Safety procedures and devices used to insure superconducting magnetic suspension system reliability are outlined. Power supplies and system failure are included.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Develop. of a Superconducting Electromagnetic Suspension and Balance System for Dyn. Stability Studies; 9 p
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  • 86
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    Induced shock pulse testing by transient waveform control (1973)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: A method of synthesizing an arbitrarily shaped transient time pulse on vibration exciters is described. The transient waveform control technique is based on recent developments in digital time series analysis, the real-time FFT processor. A brief description of the theory, error estimates and hardware/software implementation to the JPL Dynamic Environmental Testing Laboratory is presented.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: JPL Quart. Tech. Rev., Vol. 3, No. 2 (NASA-CR-133863); p 11-22
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  • 87
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    Facilities (1973)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Detailed descriptions are provided for mechanical devices, life support systems, and data handling and communications instrumentation that are connected with the altitude chamber in which the Skylab medical experiments altitude tests were performed.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Its Skylab Med. Expt. Altitude Test (SMEAT); 29 p
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  • 88
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    A study of vertical motion requirements for landing simulation (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Tests were conducted to determine the significance of vertical acceleration cues in the simulation of the visual approach and landing maneuver. Landing performance measures were obtained for four subject pilots operating a visual landing simulation mechanized in the Ames Height Control Test Apparatus, a device that provides up to plus or minus 40 ft of vertical motion. Test results indicate that vertical motion cues are utilized in the landing task, and that they are particularly important in the simulation of aircraft with marginal longitudinal-handling qualities. To assure vertical motion cues of the desired fidelity in the landing task, it appears, that a simulator must have excursion capabilities of at least 20 ft in either direction.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Human Factors; 15; Dec. 197
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  • 89
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    A linear accelerator for simulated micrometeors. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Review of the theory, design parameters, and construction details of a linear accelerator designed to impart meteoric velocities to charged microparticles in the 1- to 10-micron diameter range. The described linac is of the Sloan Lawrence type and, in a significant departure from conventional accelerator practice, is adapted to single particle operation by employing a square wave driving voltage with the frequency automatically adjusted from 12.5 to 125 kHz according to the variable velocity of each injected particle. Any output velocity up to about 30 km/sec can easily be selected, with a repetition rate of approximately two particles per minute.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Review of Scientific Instruments; 44; June 197
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  • 90
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    Lens projection system for a solar simulator providing irradiance of 100 solar constants. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Applied Optics; 12; Feb. 197
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  • 91
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    Wallops and its role in depressed metabolism (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Facilities and organization at the Wallops station are reviewed and some current research work is described that pertains to noise abatement studies as well as some testing phases on V/STOL aircraft. Radiation biology results of various space flights are reviewed and some efforts for the Regulatory Biology Program, involving depressed metabolism aspects of space travel are detailed.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Regulatory Biol.: Depressed Metab.; p 23-26
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  • 92
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    Effects of upstream wall temperatures on hypersonic tunnel wall boundary-layer profile measurements. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: AIAA Journal; 11; Apr. 197
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  • 93
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    Welding at the Kennedy Space Center. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Brief description of the nature of the mechanical equipment at a space launch complex from a welding viewpoint. including an identification of the major welding applications used in the construction of this complex. The role played by welding in the ground support equipment is noted, including the welded structures and systems required in the vehicle assembly building, the mobile launchers, transporters, mobile service structure, launch pad and launch site, the propellants system, the pneumatics system, and the environmental control system. The welding processes used at the Kennedy Space Center are reviewed, and a particularly detailed account is given of the design and fabrication of the liquid hydrogen and liquid oxygen storage spheres and piping. Finally, the various methods of testing and inspecting the storage spheres are cited.
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  • 94
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    Aspects of investigating STOL noise using large-scale wind-tunnel models. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The applicability of the NASA Ames 40- by 80-foot wind tunnel for acoustic research on STOL concepts has been investigated. The acoustic characteristics of the wind-tunnel test section have been studied with calibrated acoustic sources. Acoustic characteristics of several large-scale STOL models have been studied in both the free-field and wind-tunnel acoustic environments. The results of these studies indicate that the acoustic characteristics of large-scale STOL models can be measured in the wind tunnel if the test section acoustic environment and model acoustic similitude are taken into consideration. The reverberant field of the test section must be determined with an acoustically similar noise source. A directional microphone, a phased array of microphones, and extrapolation of near-field data to far-field are some of the techniques being explored as possible solutions to the directivity loss in a reverberant field. The model sound pressure levels must be of sufficient magnitude to be distinguishible from the wind-tunnel background noise.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
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  • 95
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    Meeting the challenge of advanced helicopters. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Wind tunnel tests that are conducted during the course of a typical aircraft development program are considered. The objectives of a test program are to reduce technical and financial risk and to improve product performance. Typical fixed-wing and rotary-wing aircraft development programs are compared. It is concluded that existing wind tunnel practice is not adequate in relation to the consequences from serious problems remaining undetected until flight test. In fact, the ultimate goal of the wind tunnel test program should leave nothing for the flight test program but the demonstration of the final product.-
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Vertiflite; 19; Mar
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  • 96
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    Inexpensive high vacuum feedthroughs. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Description of the use of rigid coaxial cable in the construction of high vacuum coaxial and coaxial push-pull rotary motion feedthroughs. This type of feedthroughs is shown to be extremely cheap and simple to make and modify. It can be used for moderately high voltages and provides a continuous, well shielded, low-noise feedthrough cable in any desired configuration.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Review of Scientific Instruments; 44; Mar. 197
    Format: text
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  • 97
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    The cosmic dust analyzer: Experimental evaluation of an impact ionization model (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A thermal equilibrium plasma model is used to process data from an impact ionization time-of-flight mass spectrometer in order to convert the raw ion data to relative abundances of the elemental constituents of cosmic dust particles.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA, Washington Evolutionary and Phys. Properties of Meteoroids; p 299-310
    Format: application/pdf
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  • 98
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    A unique high intensity solar simulation system (1973)
    In:  CASI
    Details
    Publication Date: 2017-06-24
    Description: This simulator is unique in that it is capable of producing intensities up to 16.0 solar constants (25 solar constants without spectral filters) and closely simulates the solar spectrum over a 12 inch diameter area. The simulator is described and the capabilities, calibration, operational experiences, data collection, and safety considerations associated with this simulator are discussed.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: Space Simulation, 7th; p 775-794
    Format: application/pdf
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  • 99
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    Model support roll balance and roll coupling (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The design concepts of two specialized wind tunnel model support mechanisms are described. The forced oscillation roll balance mechanism was designed to meet the specific requirement to measure aerodynamic forces and moments to permit determination of the damping-in-roll parameters of winged configurations. A variable speed motor is used to oscillate the model by means of an offset crank. The oscillating motion is resisted by a torsion spring to provide a restoring torque and is attached to the section forward of the strain-gage balance. This spring action allows the model to be oscillated at a frequency for velocity resonance, whereby the mechanical spring and any aerodynamic spring balance. This spring action allows the model to be oscillated at a frequency for velocity resonance, whereby the mechanical spring and any aerodynamic spring balance out the model inertia. The only torque then required to oscillate the model at that particular frequency is equal to that due to aerodynamic damping. The second mechanism, a roll coupling for remotely rotating a model, was designed to invert or roll a model about its longitudinal axis when mounted for testing.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: The 8th Aerospace Mech. Symp. te; p 155-163
    Format: application/pdf
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  • 100
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    Wind sensitivity studies of a non-return wind tunnel with a 216- by 432-mm (8.5- by 17.0-inches) test section, phase 2 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The refinement of inlet and exit treatments were studied which would minimize the effect of external wind on the test-section flow quality of a nonreturn wind tunnel. The investigation was conducted in the Ames Research Center 40- by 80-foot Wind Tunnel which served as the wind source. Several inlets and two exits were tested at wind directions ranging from 0 to 180 degrees and at wind-to-test-section velocity ratios from zero to somewhat greater than one. For the best inlet configuration the flow quality was good, with a velocity deviation in each of the three component directions generally less. The loss in total pressure due to the inlet treatment was low: about 0.035 of the test-section dynamic pressure for the no-wind case.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TM-X-62307
    Format: application/pdf
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