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  • Other Sources  (830)
  • Aircraft Design, Testing and Performance  (472)
  • AERODYNAMICS
  • Aircraft Propulsion and Power
  • 2005-2009  (708)
  • 1950-1954  (122)
  • 1
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    X-48B System Flight Test (2007)
    In:  CASI
    Details
    Publication Date: 2013-04-10
    Description: Provides an overview of the X-48B prototype system flight test including vehicle characteristics and configuration. There are two X-48B Vehicles: the first, Vehicle 1, is the wind tunnel and flight test model. The second, Vehicle 2, provides the primary flight test. In mid-May 2006 the research team successfully completed 250 hours of wind tunnel tests on the X-48B Vehicle 1 at NASA's Langley Air Force Base. The prototype was then shipped to NASA's Dryden Flight Research Center at Edwards Air Force Base to serve as a backup to Vehicle 2, which is used for planned remotely piloted flight tests at Dryden.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    High Temperature Investigations into an Active Turbine Blade Tip Clearance Control Concept (2008)
    In:  Other Sources
    Details
    Publication Date: 2018-06-06
    Description: System studies have shown the benefits of reducing blade tip clearances in modern turbine engines. Minimizing blade tip clearances throughout the engine will contribute materially to meeting NASA s Ultra-Efficient Engine Technology (UEET) turbine engine project goals. NASA GRC is examining two candidate approaches including rub-avoidance and regeneration which are explained in subsequent slides.
    Keywords: Aircraft Propulsion and Power
    Type: 2007 NASA Seal/Secondary Air System Workshop; 101-123; NASA/CP-2008-215263/VOL1
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    High-Frequency, High-Temperature Fretting Experiments (2005)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Fretting is a structural damage mechanism observed when two nominally clamped surfaces are subjected to an oscillatory loading. A critical location for fretting induced damage has been identified at the blade/disk and blade/damper interfaces of gas turbine engine turbomachinery and space propulsion components. The high-temperature, high-frequency loading environment seen by these components lead to severe stress gradients at the edge-of-contact. These contact stresses drive crack nucleation and propagation in fretting and are very sensitive to the geometry of the contacting bodies, the contact loads, materials, temperature, and contact surface tribology (friction). To diagnose the threat that small and relatively undetectable fretting cracks pose to damage tolerance and structural integrity of in-service components, the objective of this work is to develop a well-characterized experimental fretting rig capable of investigating fretting behavior of advanced aerospace alloys subjected to load and temperature conditions representative of such turbomachinery components.
    Keywords: Aircraft Propulsion and Power
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    General Matrix Inversion for the Calibration of Electric Field Sensor Arrays on Aircraft Platforms (2006)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: We have developed a matrix calibration procedure that uniquely relates the electric fields measured at the aircraft with the external vector electric field and net aircraft charge. Our calibration method is being used with all of our aircraft/electric field sensing combinations and can be generalized to any reasonable combination of electric field measurements and aircraft. We determine a calibration matrix that represents the individual instrument responses to the external electric field. The aircraft geometry and configuration of field mills (FMs) uniquely define the matrix. The matrix can then be inverted to determine the external electric field and net aircraft charge from the FM outputs. A distinct advantage of the method is that if one or more FMs need to be eliminated or de-emphasized (for example, due to a malfunction), it is a simple matter to reinvert the matrix without the malfunctioning FMs. To demonstrate our calibration technique, we present data from several of our aircraft programs (ER-2, DC-8, Altus, Citation).
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Small UAS Test Area at NASA's Dryden Flight Research Center (2008)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: This viewgraph presentation reviews the areas that Dryden Flight Research Center has set up for testing small Unmanned Aerial Systems (UAS). It also reviews the requirements and process to use an area for UAS test.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    IRAC Full-scale Flight Test (2008)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: This viewgraph presentation reviews Integrated Resilient Aircraft Control (IRAC) full scale flight tests.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    NASA High Temperature Turbine Seal Rig Development (2006)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: This viewgraph presentation describes a turbine seal rig concept to meet next generation engine speed and temperatures requirements. The contents include: 1) Turbomachinery Seal Development Objectives; 2) High Temperature Turbomachinery Seal Test Rig; 3) Test Parameters; 4) Highlights of Engineering Calculations; 5) Seal Rig Global Thermal Analysis; 6) Test Rig Status; 7) Seal Rig Schematic; 8) Test Chamber Enlarged View; and 9) Rig Features Unique Measurement Systems.
    Keywords: Aircraft Propulsion and Power
    Type: Seals/Secondary Fluid Flows Workshop 1997; Volume I; 69-82; NASA/CP-2006-214329/VOL1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Liquid Annular Seal CFD Analysis for Rotordynamic Force Prediction (2006)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: A commercially available code is utilized to analyze a plain and grooved liquid annular seal. These type seals are commonly used in modern turbopumps and have a pronounced effect on the rotordynamic behavior of these systems. Accurate prediction of both leakage and dynamic reaction forces is vital to ensure good performance and sound mechanical operation. The code SCISEAL developed by CFDRC is a generic 3-D, finite volume based CFD code solving the 3-D Reynolds averaged Navier Stokes equations. The code allows body-fitted, multi-blocked structured grids, turbulence modeling, rotating coordinate frames, as well as integration of dynamic pressure and shear forces on the rotating journal. The code may be used with the commercially available pre-and post-processing codes from CFDRC as well.
    Keywords: Aircraft Propulsion and Power
    Type: Seals/Secondary Fluid Flows Workshop 1997; Volume I; 295-337; NASA/CP-2006-214329/VOL1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Baseline HSR Inlet and Engine Bay Cowl Seal Requirements (2006)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: The two dimensinal bifurcated inlet, down selected for the HSR program, and the engine bay cowling consist of many sealing interfaces. The variable geometry characteristics of this inlet and the size of the propulsion system impose new sealing requirements for commercial transport aircraft. Major inlet systems requiring seal development and testing include the ramp system, the bypass/take-off system, and the inlet/engine interface. Engine bay cowling seal interfaces include the inlet/cowling interface, the keel split line, the hinge beam/engine bay cowling, and the nozzle/cowling interface. These seals have to withstand supersonic flight operating temperatures and pressures with typical commercial aircraft reliability and lives. The operating conditions and expected seal lives will be identified for the various interfaces. Boeing's SST seal development program will also be discussed.
    Keywords: Aircraft Propulsion and Power
    Type: Seals/Secondary Fluid Flows Workshop 1997; Volume II: HSR Engine Special Session; 17-58; NASA/CP-2006-214329/VOL2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    HSCT Anticipated Seal Needs Turbomachinery Seals Combustor Seals (2006)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: The High Speed Civil Transport (HSCT) engine concept is a large mixed flow turbofan similar in construction to current military fighter engines. The mission, however, is quite different. The engine will operate for long periods of time at very high Mach numbers and high altitudes. The engine is required to have very low emissions and noise levels to be acceptable in commercial service. Current thrust levels are in the 55000 lb range. At the current supercruise speed requirement of Mach 2.4, the engine inlet temperature will be at least 380 F. This is the lowest cycle temperature expected anywhere in the propulsion system.Seals will be exposed to operate at this temperature and higher for thousands of hours without failure. Durability, cost, and weight will all be very important in determining the type of seals selected for a successful HSCT engine.
    Keywords: Aircraft Propulsion and Power
    Type: Seals/Secondary Fluid Flows Workshop 1997; Volume II: HSR Engine Special Session; 59-86; NASA/CP-2006-214329/VOL2
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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