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9.0
Jul 8, 2019
07/19
by
Hak5
movies
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The future of electric air travel is upon us - Darren reports on LEAPTech from the NASA Armstrong Research Center. Plus, tracking the International Space Station from a Raspberry Pi! Maker Faire is all Iabout Arduino and Raspberry Pi this year! All that and more, this time on Hak5! http://www.nasa.gov/centers/armstrong/Features/leaptech.html http://issabove.com/ https://www.kickstarter.com/projects/1762626887/cubit-the-make-anything-platform/video_share -~-~~-~~~-~~-~- Please watch: "Bash...
Topics: Youtube, video, Science & Technology, leaptech, nasa, dryden, armstrong, Leading Edge...
A free-to-roll study of the low-speed lateral characteristics of the pre-production F/A-18E was conducted in the NASA Langley 12-Foot Low-Speed Tunnel. In developmental flight tests the F/A-18E unexpectedly experienced uncommanded lateral motions in the power approach configuration. The objective of this study was to determine the feasibility of using the free-to-roll technique for the detection of uncommanded lateral motions for the preproduction F/A-18E in the power approach configuration....
Topics: NASA Technical Reports Server (NTRS), ROLL, STRAKES, AERODYNAMIC CONFIGURATIONS, F-18 AIRCRAFT,...
Wind tunnel tests of arrow-wing body configurations consisting of flat, twisted, and cambered twisted wings, as well as a variety of leading and trailing edge control surface deflections, were conducted at Mach numbers from 0.4 to 1.05 to provide an experimental pressure data base for comparison with theoretical methods. Theory to experiment comparisons of detailed pressure distributions were made using state of the art attached flow methods. Conditions under which these theories are valid for...
Topics: NASA Technical Reports Server (NTRS), AEROELASTICITY, ARROW WINGS, BODY-WING CONFIGURATIONS,...
The High-Speed Research Program sponsored the NASA High-Speed Research Program Aerodynamic Performance Review on February 8-12, 1999 in Anaheim, California. The review was designed to bring together NASA and industry High-Speed Civil Transport (HSCT) Aerodynamic Performance technology development participants in areas of: Configuration Aerodynamics (transonic and supersonic cruise drag prediction and minimization) and High-Lift. The review objectives were to: (1) report the progress and status...
Topics: NASA Technical Reports Server (NTRS), CIVIL AVIATION, SUPERSONIC TRANSPORTS, PERFORMANCE...
A wind tunnel investigation of two separate leading-edge flaps, designed for vortex and attached-flow, respectively, were conducted on a High Speed Civil Transport (HSCT) configuration in the Langley 14- by 22-Foot Subsonic Tunnel. Data were obtained over a Mach number range of 0.12 to 0.27, with corresponding chord Reynolds numbers of 2.50 x 10 (sup 6) to 5.50 x 10 (sup 6). Variations of the leading-edge flap deflection angle were tested with outboard leading-edge flaps deflected 0 deg. and...
Topics: NASA Technical Reports Server (NTRS), SUBSONIC WIND TUNNELS, LEADING EDGE FLAPS, VORTICES,...
The HSR program moved into phase two with the selection of a new airplane configuration, the Technology Concept Airplane (TCA). The TCA was designed based on the experiences gained while investigating both the Reference H and the Arrow Wing configurations in different wind tunnels and CFD studies. Part of that investigation included performing extensive high Reynolds number testing on the Reference H configuration in the NTF to provide data for predicting full-scale flight performance, as well...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CONFIGURATIONS, COMPUTATIONAL FLUID DYNAMICS,...
The low speed longitudinal characteristics of the jet flap STOL model were determined. The 17 percent thick supercritical swept wing had leading edge slats and a full span 0.30 chord plain flap with flaperons divided into six equal spanwise segments. The angle of attack range was -4 deg to 24 deg, and the blowing momentum range was from 0 to 2.3. Flap deflections were from 0 deg to 70 deg. Most flap deflections were full span although there were some tests of partial span deflections and...
Topics: NASA Technical Reports Server (NTRS), AIRCRAFT MODELS, JET FLAPS, SHORT TAKEOFF AIRCRAFT, WIND...
Four advanced fighter configurations, which differed in wing planform and airfoil shape, were investigated in the Langley Unitary Plan Wind Tunnel at Mach numbers of 1.60, 1.80, 2.00, and 2.16. Supersonic data were obtained on the four uncambered wings, which were each attached to a single fighter fuselage. The fuselage geometry varied in cross-sectional shape and had two side-mounted, flow-through, half-axisymmetric inlets. Twin vertical tails were attached to the fuselage. The four planforms...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, AIRCRAFT CONFIGURATIONS, FIGHTER...
The primary objective is to determine how an airplane configuration should be modeled to predict both longitudinal and lateral aerodynamic characteristics at high angles of attack. A generic fighter model, an F-16 and an F-18 configuration with leading edge flap deflection and an F-106B configuration were investigated. Furthermore, the F-16XL and X-29 configurations were examined. Some calculated results are given.
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, F-16 AIRCRAFT, F-18 AIRCRAFT,...
Prediction of the loss of wing leading-edge thrust and the accompanying increase in drag due to lift, when flow is not completely attached, presents a difficult but commonly encountered problem. A method (called the previous method) for the prediction of attainable leading-edge thrust and the resultant effect on airplane aerodynamic performance has been in use for more than a decade. Recently, the method has been revised to enhance its applicability to current airplane design and evaluation...
Topics: NASA Technical Reports Server (NTRS), LEADING EDGE THRUST, AIRCRAFT DESIGN, SHARP LEADING EDGES,...
From the bitsavers.org collection, a scanned-in computer-related document. ncr :: ncr-315 :: F-7405 NCR-315 IO Jun61
Topics: tape, processor, instruction, cram, demand, punch, slabs, unit, unit demand, magnetic tape, paper...
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128
May 29, 2011
05/11
by
Bar-Cohen, Yosep
texts
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Nondestructive Evaluation and Advanced Actuators (NDEAA) are presented. The focus areas are on mechanisms and devices that are driven by acoustic or elastic waves. The topics include: 1) Nondestructive Evaluation; 2) Advanced Actuators; 3) Ultrasonic Medical Diagnostics and Treatment; and 4) Telerobotics.
Topics: HIGH SPEED, NASA PROGRAMS, MISSILES, MACH NUMBER, FLAT PLATES, DELTA WINGS, CAVITIES, AIRCRAFT...
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Jun 12, 2011
06/11
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Wilson, John W.; Nealy, John E; Tripathi, Ram K.; Mertens, Christopher J.; Blattnig, Steve R.; Clowdsley, Martha S.; Cucinotta, Francis A.; Tweed, John; Heinbockel, John H.; Walker, Steven A.
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In the present paper, we give the formalism for further developing a fully three-dimensional HZETRN code using marching procedures but also development of a new Green's function code is discussed. The final Green's function code is capable of not only validation in the space environment but also in ground based laboratories with directed beams of ions of specific energy and characterized with detailed diagnostic particle spectrometer devices. Special emphasis is given to verification of the...
Topics: PARTICLE IMAGE VELOCIMETRY, FLOW REGULATORS, CCD CAMERAS, VORTEX GENERATORS, COMPUTATIONAL FLUID...
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May 6, 2010
05/10
by
Valentine, E. F
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Pressure-drag effects of rounding leading edges of hypersonic inlets
Topics: HYPERSONIC INLETS, LEADING EDGES, PRESSURE DRAG, HYPERSONIC INLET, LEADING EDGE, PRESSURE DRAG
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Jul 12, 2010
07/10
by
Baganoff, D.; Liu, G
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No Abstract Available
Topics: AERODYNAMIC CHARACTERISTICS, ARROW WINGS, LEADING EDGE SWEEP, SWEPT WINGS, AERODYNAMIC STABILITY,...
Nonlinear parabolized stability equations and secondary-instability analyses are used to provide a computational assessment of the potential use of the discrete-roughness-element technology for extending swept-wing natural laminar flow at chord Reynolds numbers relevant to transport aircraft. Computations performed for the boundary layer on a natural-laminar-flow airfoil with a leading-edge sweep angle of 34.6 deg, freestream Mach number of 0.75, and chord Reynolds numbers of 17 × 10(exp 6),...
Topics: NASA Technical Reports Server (NTRS), TRANSPORT AIRCRAFT, SURFACE ROUGHNESS, SKIN FRICTION, LAMINAR...
This paper presents a systems overview of how the Boeing and NASA team designed, analyzed, fabricated, and integrated the Active Flow Control (AFC) technology and Insect Accretion Mitigation (IAM) systems on the Boeing 757 ecoDemonstrator. The NASA Environmentally Responsible Aviation (ERA) project partnered with Boeing to demonstrate these two technology systems on a specially outfitted Boeing 757 ecoDemonstrator during the spring of 2015. The AFC system demonstrated attenuation of flow...
Topics: 1e229fe5b7284965a153b0f761643383, Alexander, Michael G., Boeing Commercial Airplane Co., Boeing...
This paper describes the computational analysis of several concepts to improve the maximum lift of a military high-lift airfoil configuration. The computational results are compared with the wind-tunnel data obtained for a gap and overhang study and a Gurney flap study. In the wind tunnel experiments, optimizing the gap and over-hang and adding a Gurney flap provided the largest increases, on the order of 3-4%. These trends were duplicated in the CFD analyses. Incremental lift improvements were...
Topics: DTIC Archive, Hall, D. R., NAVAL AIR WARFARE CENTER AIRCRAFT DIV PATUXENT RIVER MD, *COMPUTATIONS,...
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Jul 2, 2017
07/17
by
KFON-TV
movies
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In this edition of Fontana's Open for Business, Mayor Acquanetta Warren's guest is Nina Henry, Southern California Regional Manager for Leading Edge Learning Center. Find out how Leading Edge can help students excel in their academics with their qualified staff.
Topics: California, Fontana, KFON-TV, Government Access TV, Community Media, PEG, Youtube, kfontv, city of...
From the bitsavers.org collection, a scanned-in computer-related document. ict icl :: 1900 :: 1110020-1900-Standard-Interface-Specification
Topics: peripheral, data, interface, processor, status, iss, control, character, specification, sheet,...
From the bitsavers.org collection, a scanned-in computer-related document. tektronix :: concepts :: 062-0955-00 Television Waveform Processing Circuits Mar69
Topics: sync, pulse, circuit, phase, waveform, pulses, color, field, amplitude, composite, sync pulse,...
From the bitsavers.org collection, a scanned-in computer-related document. dysan :: 224-2a 5inch DS AlignmentDiscSpec Aug79
Topics: track, diskette, alignment, usee, dysan, inches, burst, rev, centerline, azimuth, leading edge,...
From the bitsavers.org collection, a scanned-in computer-related document. mit :: ai :: aim :: AITR-904
Topics: program, flow, graph, recognizer, figure, input, node, loop, rule, grammar, flow graph, control...
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338
Jan 23, 2009
01/09
by
Victor Wilfred Pagé
texts
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Book digitized by Google from the library of the University of Michigan and uploaded to the Internet Archive by user tpb.
Topics: airplane, wing, fuselage, air, propeller, plane, center, aviation, practical, aerofoil, landing...
Source: http://books.google.com/books?id=PyEFAAAAMAAJ&oe=UTF-8
From the bitsavers.org collection, a scanned-in computer-related document. cdc :: discs :: brochures :: CDC 9730 MMD Brochure May79
Topics: data, unit, datatracks, servo, tracks, module, cable, head, mmd, select, data tracks, data head,...
Since mission profiles for airbreathing hypersonic vehicles such as the National Aero-Space Plane include single-stage-to-orbit requirements, real gas effects may become important with respect to engine performance. The effects of the decrease in the ratio of specific heats have been investigated in generic three-dimensional sidewall compression scramjet inlets with leading-edge sweep angles of 30 and 70 degrees. The effects of a decrease in ratio of specific heats were seen by comparing data...
Topics: NASA Technical Reports Server (NTRS), REYNOLDS NUMBER, SUPERSONIC COMBUSTION RAMJET ENGINES, ENGINE...
The results of a series of 39 flight tests of the X-48B Low Speed Vehicle (LSV) performed at the NASA Dryden Flight Research Center from July 2007 through December 2008 are reported here. The goal of these tests is to evaluate the aerodynamic and controls and dynamics performance of the subscale LSV aircraft, eventually leading to the development of a control system for a full-scale vehicle. The X-48B LSV is an 8.5%-scale aircraft of a potential, full-scale Blended Wing Body (BWB) type aircraft...
Topics: NASA Technical Reports Server (NTRS), BLENDED-WING-BODY CONFIGURATIONS, FLIGHT TESTS, GENERAL...
This paper describes methodology and an associated computer program for the design of wing lifting surfaces with attainable thrust taken into consideration. The approach is based on the determination of an optimum combination of a series of candidate surfaces rather than the more commonly used candidate loadings. Special leading-edge surfaces are selected to provide distributed leading-edge thrust forces which compensate for any failure to achieve the full theoretical leading-edge thrust, and a...
Topics: NASA Technical Reports Server (NTRS), CAMBERED WINGS, COMPUTER PROGRAMS, DESIGN ANALYSIS, LEADING...
An assessment of the influence of airfoil geometry on delta wing leading edge vortex flow and vortex induced aerodynamics at supersonic speeds is discussed. A series of delta wing wind tunnel models were tested over a Mach number range from 1.7 to 2.0. The model geometric variables included leading edge sweep and airfoil shape. Surface pressure data, vapor screen, and oil flow photograph data were taken to evaluate the complex structure of the vortices and shocks on the family of wings tested....
Topics: NASA Technical Reports Server (NTRS), AIRFOIL PROFILES, DELTA WINGS, LEADING EDGES, SUPERSONIC...
Active flow control wind tunnel experiments were conducted in the NASA Langley Low-Turbulence Pressure Tunnel using a two-dimensional supercritical high-lift airfoil with a 15% chord hinged leading-edge flap and a 25% chord hinged trailing-edge flap. This paper focuses on the application of zero-net-mass-flux periodic excitation near the airfoil trailing edge flap shoulder at a Mach number of 0.1 and chord Reynolds numbers of 1.2 x 10(exp 6) to 9 x 10(exp 6) with leading- and trailing-edge flap...
Topics: NASA Technical Reports Server (NTRS), LIFT, WIND TUNNEL TESTS, SUPERCRITICAL AIRFOILS, LOW...
A test program conducted in the LaRC 8-foot Transonic Pressure Tunnel on a blended chine/delta wing model to verify the concept of controlled vortex decoupling via inboard leading-edge flaps for improved high-alpha lateral/directional characteristics is discussed. This test extended the Mach number range of a data base previously generated in a LaRC 7 ft. by 10 ft High Speed Tunnel investigation. Six-component force/moment, forebody surface pressures, and central and twin tall static and...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CONFIGURATIONS, ANGLE OF ATTACK, DECOUPLING,...
A detailed investigation of the flight buffeting response of the F-111A was performed in two phases. In Phase 1 stochastic analysis techniques were applied to wing and fuselage responses for maneuvers flown at subsonic speeds and wing leading edge sweep of 26 degrees. Power spectra and rms values were obtained. This report gives results of Phase 2 where the analyses were extended to include maneuvers flown at wing leading edge sweep values of 50 and 75.5 degrees at subsonic and supersonic...
Topics: NASA Technical Reports Server (NTRS), BUFFETING, F-111 AIRCRAFT, FLIGHT TESTS, SUBSONIC SPEED,...
Aerodynamic analysis using computational fluid dynamics (CFD) is most fruitful when it is combined with a thorough program of wind tunnel testing. The understanding of aerodynamic phenomena is enhanced by the synergistic use of both analysis methods. A technique is described for an integrated approach to determining the forces and moments acting on a wind tunnel model by using a combination of experimentally measured pressures and CFD predictions. The CFD code used was FLO57 (an Euler solver)...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC FORCES, COMPUTATIONAL FLUID DYNAMICS, DELTA...
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generalmanual 000031815
Topics: blade, grizzly, circular, awarning, edge, sander, guide, safety, tools, model, edge guide, serious...
Topics: DTIC Archive, Scala, Sinclaire M, GENERAL ELECTRIC CO PHILADELPHIA PA MISSILE AND SPACE DIV,...
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194
Jun 9, 2011
06/11
by
Nowaczyk, Ronald H.; Zang, Thomas A
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The perceptions of a sample of 49 engineers and scientists from NASA Langley Research Center toward engineering design teams were evaluated. The respondents rated 60 team behaviors in terms of their relative importance for team success. They also completed a profile of their own perceptions of their strengths and weaknesses as team members. Behaviors related to team success are discussed in terms of those involving the organizational culture and commitment to the team and those dealing with...
Topics: FLOW DISTRIBUTION, SHEAR LAYERS, STABILITY, LIFT, STRESS TENSORS, NOISE REDUCTION, NAVIER-STOKES...
The feasibility of integrating heat pipes in high temperature structure to reduce local hot spot temperature was evaluated for a variety of hypersonic aerospace vehicles. From an initial list of twenty-two potential applications, the single stage to orbit wing leading edge showed the greatest promise and was selected for preliminary design of an integrated heat pipe thermostructural system. The design consisted of a Hastelloy X assembly with sodium heat pipe passages aligned normal to the wing...
Topics: NASA Technical Reports Server (NTRS), HEAT PIPES, HYPERSONIC VEHICLES, SPACE TRANSPORTATION,...
An investigation has been conducted at Mach numbers ranging from 0.06 to 0.94 to determine the effects of various combinations of leading-edge slat devices on the static aerodynamic characteristics of a twin-jet swept-wing fighter model. The study also included a determination of the effects of wing leading-edge droop, trailing-edge chord-extensions, wing fences, and wing-planform and camber modifications. The angle-of-attack range generally extended from about minus 2 deg to 24 deg and the...
Topics: NASA Technical Reports Server (NTRS), FIGHTER AIRCRAFT, LEADING EDGE SLATS, STATIC AERODYNAMIC...
A wind tunnel investigation was conducted in the Langley 12-Foot Low-Speed Wind Tunnel to study the low-speed stability and control characteristics of a series of four flying wings over an extended range of angle of attack (-8 deg to 48 deg). Because of the current emphasis on reducing the radar cross section of new military aircraft, the planform of each wing was composed of lines swept at a relatively high angle of 60 deg, and all the trailing-edge lines were aligned with one of the two...
Topics: NASA Technical Reports Server (NTRS), AIRCRAFT DESIGN, DIRECTIONAL STABILITY, FLIGHT...
Reynolds number and cowl position effects on the internal shock structure and the resulting performance of a generic three-dimensional sidewall compression scramjet inlet with a leading edge sweep of 45 degrees at Mach 10 have been examined both computationally and experimentally. Prior to the experiment, a three-dimensional Navier-Stokes code was adapted to perform preliminary parametric studies leading to the design of the present configuration. Following this design phase, the code was then...
Topics: NASA Technical Reports Server (NTRS), REYNOLDS NUMBER, SUPERSONIC COMBUSTION RAMJET ENGINES, WIND...
The effects of fin leading edge sweep on peak heating rates due to shock-shock interaction have been experimentally examined in the Langley 20-Inch Mach 6 Tunnel. The shock interaction was produced by the intersection of a planar incident shock (16.8 deg shock angle relative to the freestream, generated by a 9 deg wedge) with the bow shock formed around a O.5-inch diameter cylindrical leading edge fin. Heating distributions along the leading edge stagnation line have been obtained using densely...
Topics: NASA Technical Reports Server (NTRS), LEADING EDGE SWEEP, SHOCK WAVE INTERACTION, WIND TUNNEL...
High resolution infrared observations made from a mobile ground based optical system captured the laminar-to-turbulent boundary layer transition process as it occurred during Space Shuttle Endeavour's return to earth following its final mission in 2011. The STS-134 imagery was part of a larger effort to demonstrate an emerging and reliable non-intrusive global thermal measurement capability and to complement a series of boundary layer transition flight experiments that were flown on the...
Topics: NASA Technical Reports Server (NTRS), SPACE SHUTTLE ORBITERS, HIGH RESOLUTION, INFRARED ASTRONOMY,...
The subsonic aerodynamic characteristics of a series of irregular planform wings were studied in wind tunnel tests conducted at M = 0.3 over a range of Reynolds numbers from 1.6 million to 26 million/m. The five basic wing planforms varied from a trapezoidal to a delta shape. Leading edge extensions, added to the basic shape, varied in approximately 5 deg increments from the wing leading edge sweep-back angle to a maximum 80 deg. Most of the tests were conducted using an NACA 0008 airfoil...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, REYNOLDS NUMBER, SUBSONIC SPEED,...
Experimental/theoretical correlations are presented which show that significant levels of leading edge thrust are possible at supersonic speeds for certain planforms which match the theoretical thrust distribution potential with the supporting airfoil geometry. The analytical process employed spanwise distribution of both it and/or that component of full theoretical thrust which acts as vortex lift. Significantly improved aerodynamic performance in the moderate supersonic speed regime is...
Topics: NASA Technical Reports Server (NTRS), LEADING EDGE THRUST, PLANFORMS, SUPERSONIC SPEED, THRUST...
A wind tunnel investigation was conducted on a generic, high-wing transport model in the Langley 14- by 22-Foot Subsonic Tunnel. This report contains pressure data that document effects of various model configurations and free-stream conditions on wing pressure distributions. The untwisted wing incorporated a full-span, leading-edge Krueger flap and a part-span, double-slotted trailing-edge flap system. The trailing-edge flap was tested at four different deflection angles (20 deg, 30 deg, 40...
Topics: NASA Technical Reports Server (NTRS), ANGLE OF ATTACK, LEADING EDGE FLAPS, MACH NUMBER, PRESSURE...
A tab deployable from the trailing edge of a main airfoil element forces flow onto a following airfoil element, such as a flap, to keep the flow attached and thus enhance lift. For aircraft wings with high lift systems that include leading edge slats, the slats may also be provided with tabs to turn the flow onto the following main element.
Topics: NASA Technical Reports Server (NTRS), LEADING EDGE SLATS, LIFT, TABS (CONTROL SURFACES), TRAILING...
The method and apparatus includes a neural network for generating a model of an object in a wind tunnel from performance data on the object. The network is trained from test input signals (e.g., leading edge flap position, trailing edge flap position, angle of attack, and other geometric configurations, and power settings) and test output signals (e.g., lift, drag, pitching moment, or other performance features). In one embodiment, the neural network training method employs a modified...
Topics: NASA Technical Reports Server (NTRS), NEURAL NETS, WIND TUNNEL TESTS, REAL TIME OPERATION, MODELS,...
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Hewlett-Packard Journal Vol. 30 No. 5 (1979-05)(Hewlett-Packard)
Topics: pulse, isource, memory, assembly, desktop, source, width, transition, output, delay, assembly...
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519
May 27, 2011
05/11
by
Stewart, Elwood C.; Druding, Frank; Nishiura, Tog
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A study has been made to determine the relative importance of those factors which place an inherent limitation on the minimum obtainable miss distance for a beam-rider navigation system operating in the presence of glint noise and target evasive maneuver. Target and missile motions are assumed to be coplanar. The factors considered are the missile natural frequencies and damping ratios, missile steady-state acceleration capabilities, target evasive maneuver characteristics, and angular...
Topics: LIFT DRAG RATIO, SUPERSONIC SPEED, SUBSONIC SPEED, REYNOLDS NUMBER, MINIMUM DRAG, MACH NUMBER,...
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May 23, 2011
05/11
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Moore, Berrien, III; Anderson, James G.; Costanza, Robert; Gates, W. Lawrence; Grew, Priscilla C.; Leinen, Margaret S.; Mayewski, Paul A.; McCarthy, James J.; Sellers, Piers J., et al
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This report reflects the results of a ten-day workshop convened at the Scripps Institution of Oceanography July 19-28, 1995. The workshop was convened as the first phase of a two part review of the U.S. Global Change Research Program (USGCRP). The workshop was organized to provide a review of the scientific foundations and progress to date in the USGCRP and an assessment of the implications of new scientific insights for future USGCRP and Mission to Planet Earth/Earth Observing System...
Topics: SWEPT WINGS, UPPER SURFACE BLOWING, VISCOUS DRAG, NAVIER-STOKES EQUATION, COMPUTATIONAL FLUID...
