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At least 91 records · Page 5
All sourcesNASA NTRSDOE OSTI
DOE OSTI2025

HBET V3.0 Installation Manual

The Hydropower Biological Evaluation Toolset (HBET) V3.0 now requires Python v3.11.0 to be installed, following the addition of the absolute fish injury rate prediction feature. This version introduces two new strike metrics—based on velocity and pressure—to provide a more precise understanding of the biological effects of fish collisions with rigid structures within the fish passage system. Additionally, SQL Server 2019 is the supported database for this release. This installation guide will walk users through the process of installing HBET V3.0 along with all necessary dependencies.

13 HYDRO ENERGY↗
DOE OSTI2026

Fermilab 2025 Summer Internship: Repairing Pre-Amplifiers with Mu2e Electronics Installation Team

The author spent nine weeks over summer 2025 working on the tracker electronics installation team for the Mu2e experiment. One of her main responsibilities was repairing high voltage (HV) and calibration (Cal) pre-amplifiers (pre-amps). During installation, the fragile wires connecting the two sockets to the pre-amp board must be bent, often leading to breakage. During production, the sockets and wires were initially soldered to the board at UC Berkely, then the whole pre-amp was coated in parylene before transport to Fermilab. The interns were able to expedite the repairs, and thus whole installation process, by using an alternative method on-site with epoxy. Another task they were responsible for, not included in the original project specifications, was attaching copper clips to specific vias on the Cals to reduce noise. The talk will give listeners insight into the daily problem-solving required by the novel technologies in the Mu2e project. The author would like to acknowledge her fellow Monmouth College undergraduate interns, Lizzie Durfee and Gianna Maughan, advisor and PI of the DOE RENEW Grant Dr. Christopher G. Fasano, and the Mu2e team lead by co-spokesperson Dr. Bob Bernstein and tracker L2 manager Dr. Brendan Kiburg.

de Zwart, Bronte [Monmouth Coll.]↗
NASA NTRS1971

Flight investigation of airframe installation effects on an auxiliary inlet ejector nozzle on an underwing engine nacelle

The local flow field approaching an installed nozzle may vary from isolated test conditions, thereby affecting exhausting nozzle performance. An installation of general interest is a podded engine mounted near the aft lower surface of the wing. The effect of this installation on the performance of an auxiliary inlet ejector nozzle was investigated over a Mach number range of 0.7 to 1.3 by using a modified F-106B aircraft. Both floating and fixed-open door configurations were examined. The ejector nozzle trailing-edge flaps were simulated in the closed position with rigid structure which provided a boattail angle of 15 deg. Primary nozzle area was varied as exhaust gas temperature was varied between 982.2 and 2003.3 K.

Burley, R. R.↗
NASA NTRS1973

The effects on cruise drag of installing long-duct refan-engine nacelles on the McDonnell Douglas DC-8-50 and -61

A high-speed wind tunnel test was conducted to determine the effect on cruise performance of installing long-duct refan-engine nacelles on the DC-8-50 and -61 models. Drag data and wing/pylon/nacelle channel pressure data are presented. At a typical cruise condition there exists a very small interference drag penalty of less than one-percent of total cruise data for the Refan installation. Pressure data indicate that some supersonic flow is present in the inboard channel of the inboard refan nacelle installation, but it is not sufficient to cause any wave drag on boundary layer separation. One pylon modification, which takes the form of pylon bumps, was tested. It resulted in a drag penalty, because its design goal of eliminating shock-related interference drag was not required and the bump thus became a source of additional parasite drag.

Callaghan, J. T.↗
NASA NTRS1973

The effects on cruise drag of installing refan-engine nacelles on the McDonnell-Douglas DC-9

A high speed wind tunnel test has been conducted to determine the effect on cruise drag for installing larger JT8D Refan engine nacelles on the Douglas DC-9. Drag data and wing- and nacelle/pylon/fuselage-channel pressure data are presented. Reduced pylon spares, required to minimize effects of the nacelle installation on low-speed deep stall, were investigated. The reduce span pylons resulted in no adverse interference effects. At typical cruise Mach numbers the measured penalty for the Refan installation was less than estimated due to a favorable effect of the larger entering engine stream tube suppressing the wing upper-surface velocities with subsequent wing compressibility drag reduction. Channel pressures show no shock waves or boundary layer separations.

Callaghan, J. T.↗
NASA NTRS1976

A simplified analysis of propulsion installation losses for computerized aircraft design

A simplified method is presented for computing the installation losses of aircraft gas turbine propulsion systems. The method has been programmed for use in computer aided conceptual aircraft design studies that cover a broad range of Mach numbers and altitudes. The items computed are: inlet size, pressure recovery, additive drag, subsonic spillage drag, bleed and bypass drags, auxiliary air systems drag, boundary-layer diverter drag, nozzle boattail drag, and the interference drag on the region adjacent to multiple nozzle installations. The methods for computing each of these installation effects are described and computer codes for the calculation of these effects are furnished. The results of these methods are compared with selected data for the F-5A and other aircraft. The computer program can be used with uninstalled engine performance information which is currently supplied by a cycle analysis program. The program, including comments, is about 600 FORTRAN statements long, and uses both theoretical and empirical techniques.

Morris, S. J., Jr.↗
NASA NTRS1978

Flat-plate solar collector - installation package

Package includes installation, operation and maintenance manual for collector, analysis of safety hazards, special handling instructions, materials list, installation drawings, and warranty and certification statement. Manual includes instructions for roof preparation and for preparing collector for installation. Several pages are devoted to major and minor repairs.

Source record↗
NASA NTRS1977

Installation package for air flat plate collector

The Solar 2 dimensions are four feet by eight feet by two and one half inches. The collector weighs 130 pounds and has an effective solar collection area of over 29.5 square feet. This area represents 95 percent of the total surface of the collector. The installation, operation and maintenance manual, safety hazard analysis, special handling instructions, materials list, installation concept drawings, warranty and certification statement are included in the installation package.

Source record↗
NASA NTRS1980

Solar heating system installed at Blakedale Professional Center, Greenwood, South Carolina

Information on the solar heating system installed at the Blakedale Professional Center, in Greenwood, South Carolina is presented. The information consists of site and building description, solar system description, performance evaluation, system problems and installation drawings. The solar system was designed to provide approximately 85 percent of the building's heating requirements. The system was installed concurrently with building construction and heats 4,440 square feet of the building. There are 954 square feet of liquid flat plate collectors that are proof-mounted and have a drain-down system to protect the collectors from freezing. A 5,000 gallon steel, polyurethane insulated tank buried underground provides storage. The system was fully instrumented for performance evaluation and integrated into the National Solar Data Network.

Source record↗
NASA NTRS1980

Installation package for a sunspot cascade solar water heating system

Solar water heating systems installed at Tempe, Arizona and San Diego, California are described. The systems consist of the following: collector, collector-tank water loop, solar tank, conventional tank, and controls. General guidelines which may be utilized in development of detailed installation plans and specifications are provided along with instruction on operation, maintenance, and installation of solar hot water systems.

Source record↗
NASA NTRS1982

Fluid Dynamics Panel Symposium on Aerodynamics of Power Plant Installation

Powerplant installations involve complex flows, strongly influenced by viscous effects and often with important aerodynamic interactions between the airframe and propulsion system. The introduction of vehicle propulsion concepts, and points of emphasis in aircraft and missile design requirements, provide an expanding range of aerodynamic problems which cal for both experimental and theoretical study. Aerodynamic problems in powerplant installation are surveyed and work which has improved basic understanding or has enhanced prediction and design methods in this field is reviewed. Powerplant installation effects for both combat and transport aircraft are emphasized.

Henderson, W. P.↗
NASA NTRS1983

Investigation of jet-installation noise sources under static conditions

The acoustical effects of operating a 6-cm exit-diameter nozzle in the presence of a wing-flap model under static conditions are examined experimentally. The geometric parameters of the wing-flap model are chosen to represent a realistic jet-engine installation on a wide-body midrange transport airplane. The effects of varying the installation parameters and the noise sources associated with the engine-installation effects are discussed. The major noise sources are the flow interaction of the jet and wing undersurface, the flow interaction of the jet with the side edges of the flap cutout and flap trailing edge, and the reflection of the jet noise off the undersurface of the wing and flap.

Shearin, J. G.↗
NASA NTRS1984

Aerodynamic test results for a wing-mounted turboprop propulsion installation

The paper provides an overview of the renewed interest in turboprop propulsion systems for future commercial transport designs. The potential operating cost advantage of advanced turbofan designs. Critical technology items for the aerodynamic installation of turboprop propulsion systems are presented, along with experimental results addressing the main technology issue for wing-mounted turboprop installations. Nacelle installation effects are presented for overwing and underwing nacelles. The drag reduction for nacelle contouring is also shown. Wing/nacelle/power data are presented for the baseline wing geometry and for a wing modified to reduce the propeller power effects.

Page, G. S.↗
NASA NTRS1985

Comparison of advanced turboprop installation on swept and unswept supercritical wings at transonic speeds

A series of wind-tunnel investigations were conducted to determine the aerodynamic interference associated with the over wing and under wing installation of a turboprop nacelle on 20 deg swept and unswept supercritical wings. The purpose of the investigations was to increase the understanding of the flow interactions involved with the nacelle turboprop integration and to obtain experimental data for the verification of computational prediction techniques. The models were tested in the Langley 16-Foot Transonic Tunnel at Mach numbers from 0.50 to 0.80 and at angles-of-attack from 0 to 5 deg. In addition, data at several propeller pitch angles and advance ratio settings were obtained. This paper which presents only the results of the over-the-wing nacelle installations shows that wing sweep had considerable influence on the installation interference. Large scale flow separation was observed on the swept wing at M = 0.8. Less severe effects were observed at M = 0.7 on the swept wing and for both M = 0.7 and 0.8 on the unswept wing.

Carlson, J. R.↗
NASA NTRS1987

Summary of studies to reduce wing-mounted propfan installation drag on an M = 0.8 transport

Powerplant installation losses for an advanced, high-speed, turboprop transport have been investigated in the Ames Research Center Transonic Wind Tunnels as a part of the NASA Advanced Turboprop Program (ATP). Force and pressure tests have been completed at Mach numbers from 0.6 to 0.82 on baseline and modified powered-model configurations to determine the magnitude of the losses and to what extent current design tools could be used to optimize the installed performance of turboprop propulsion systems designed to cruise at M = 0.8. Results of the tests indicate a large reduction in installed drag for the modified configuration. The wing-mounted power plant caused destabilizing pitching moments and a negative shift in the zero-lift pitching moment.

Smith, Ronald C.↗
NASA NTRS1987

A feasibility assessment of installation, operation and disposal options for nuclear reactor power system concepts for a NASA growth space station

A preliminary feasibility assessment of the integration of reactor power system concepts with a projected growth space station architecture was conducted to address a variety of installation, operational disposition, and safety issues. A previous NASA sponsored study, which showed the advantages of space station - attached concepts, served as the basis for this study. A study methodology was defined and implemented to assess compatible combinations of reactor power installation concepts, disposal destinations, and propulsion methods. Three installation concepts that met a set of integration criteria were characterized from a configuration and operational viewpoint, with end-of-life disposal mass identified. Disposal destinations that met current aerospace nuclear safety criteria were identified and characterized from an operational and energy requirements viewpoint, with delta-V energy requirement as a key parameter. Chemical propulsion methods that met current and near-term application criteria were identified and payload mass and delta-V capabilities were characterized. These capabilities were matched against concept disposal mass and destination delta-V requirements to provide the feasibility of each combination.

Bloomfield, Harvey S.↗
NASA NTRS1990

In-flight investigation of shuttle tile pressure orifice installations

To determine shuttle orbiter wing loads during ascent, wing load instrumentation was added to Columbia (OV-102). This instrumentation included strain gages and pressure orifices on the wing. The loads derived from wing pressure measurements taken during STS 61-C did not agree with those derived from strain gage measurements or with the loads predicted from the aerodynamic database. Anomalies in the surface immediately surrounding the pressure orifices in the thermal protection system (TPS) tiles were one possible cause of errors in the loads derived from wing pressure measurements. These surface anomalies were caused by a ceramic filler material which was installed around the pressure tubing. The filler material allowed slight movement of the TPS tile and pressure tube as the airframe flexed and bent under aerodynamic loads during ascent and descent. Postflight inspection revealed that this filler material had protruded from or receeded beneath the surface, causing the orifice to lose its flushness. Flight tests were conducted at NASA Ames Research Center Dryden Flight Research Facility to determine the effects of any anomaly in surface flushness of the orifice installation on the measured pressures at Mach numbers between 0.6 and 1.4. An F-104 aircraft with a flight test fixture mounted beneath the fuselage was used for these flights. Surface flushness anomalies typical of those on the orbiter after flight (STA 61-C) were tested. Also, cases with excessive protrusion and recession of the filler material were tested. This report shows that the anomalies in STS 61-C orifice installations adversely affected the pressure measurements. But the magnitude of the affect was not great enough to account for the discrepancies with the strain gage measurements and the aerodynamic predictions.

Moes, Timothy R.↗