2,495
2.5K
May 6, 2010
05/10
by
Heath, A. R., Jr.; Igoe, A. W
texts
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Effects of deflected inboard ailerons on wing loads of 45-deg swept-back wing at transonic speeds
Topics: AILERONS, WING LOADING, DEFLECTION, SWEPTBACK WINGS, TRANSONIC SPEED, WIND TUNNELS, WING LOADING,...
332
332
Jun 19, 2010
06/10
by
Kuhl, A. E.; Little, M. V.; Rogers, J. T
texts
eye 332
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Flight-determined and predicted effects of flexibility on steady-state wing loads of B-52 airplane
Topics: AEROELASTICITY, B-52 AIRCRAFT, FLEXIBILITY, MACH NUMBER, STEADY STATE, WING LOADING, B-52 AIRCRAFT,...
517
517
Jun 18, 2010
06/10
by
Hill, W. A., Jr.; Kaattari, G. E
texts
eye 517
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Force and pressure distribution studies to high angles of attack on all-movable triangular and rectangular wings in combination with body at supersonic speeds
Topics: ANGLE OF ATTACK, ANGLE OF ATTACK, PRESSURE DISTRIBUTION, RECTANGULAR WING, SUPERSONIC SPEED,...
321
321
Jul 11, 2010
07/10
by
Calcote, H. F
texts
eye 321
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The original objective of this program was to determine the feasibility of high volume, low-cost production of high purity silane or solar cell grade silicon using a non equilibrium plasma jet. The emphasis was changed near the end of the program to determine the feasibility of preparing photovoltaic amorphous silicon films directly using this method. The non equilibrium plasma jet should be further evaluated as a technique for producing high efficiency photovoltaic amorphous silicon films.
Topics: AGRICULTURE, AIRCRAFT DESIGN, FIXED WINGS, AIRCRAFT CONFIGURATIONS, ASPECT RATIO, ECONOMIC FACTORS,...
260
260
Jun 2, 2011
06/11
by
Goebel, J
texts
eye 260
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Ames Research Center is supporting the development and manufacture of the guide-star telescope detectors of the Gravity Probe B (GPB) Project. GPB is a Stanford University/Lockheed-Martin/Marshall Space Flight Center Physical Science Mission that has called upon Ames Research Center's expertise in cryogenic electronics to help meet the program's launch schedule. The Ames technical contribution has been made over a period of 2 years and is expected to conclude shortly after launch, currently...
Topics: AEROELASTICITY, TORQUE, BENDING MOMENTS, LOAD TESTS, WING LOADING, CALIBRATING, CONTROL SURFACES,...
247
247
Jun 9, 2011
06/11
by
Allred, Ronald E.; Wesson, Sheldon P.; Shin, E. Eugene; Inghram, Linda; McCorkle, Linda; Papadopoulos, Demetrios; Wheeler, Donald; Sutter, James K
texts
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To increase performance and durability of high-temperature composites for potential rocket engine components, it is necessary to optimize wetting and interfacial bonding between high modulus carbon fibers and high-temperature polyimide resins. Sizings commercially supplied on most carbon fibers are not compatible with polyimides. In this study, the chemistry of sizings on two high-modulus carbon fibers (M40J and M60J, Toray) was characterized as was the chemistry of PMR-II-50 fluorinated...
Topics: WING LOADING, AEROELASTICITY, TEST FACILITIES, CCD CAMERAS, PHOTOGRAMMETRY, WIND TUNNEL MODELS,...
253
253
Jun 27, 2010
06/10
by
Rossow, V. J.; Clements, H. G.; Denardo, B. P
texts
eye 253
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Development and characteristics of device for deployment of long wires as method of reducing hazards due to lightning during spacecraft launches
Topics: AERODYNAMIC LOADS, SPACE SHUTTLES, SPACECRAFT CONTROL, LOAD DISTRIBUTION (FORCES), POTENTIAL...
1,174
1.2K
Jul 12, 2010
07/10
by
Dietert, L. E.; Briggs, C. A
texts
eye 1,174
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No Abstract Available
Topics: AERODYNAMIC CHARACTERISTICS, WING PLANFORMS, WING PROFILES, ASPECT RATIO, PREDICTION ANALYSIS...
365
365
Jul 23, 2010
07/10
by
Batina, John T
texts
eye 365
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Modifications to unsteady transonic small disturbance theory to include entropy and vorticity effects are presented. The modifications were implemented in the CAP-TSD (Computational Aeroelasticity Program - Transonic Small Disturbance) code. The code permits the aeroelastic analysis of complete aircraft configurations in the flutter critical transonic speed range. Entropy and vorticity effects were incorporated within the solution procedure to more accurately analyze flows with strong shock...
Topics: SIDESLIP, SUBSONIC SPEED, WIND TUNNEL MODELS, WINGLETS, ANGLE OF ATTACK, MACH NUMBER, PRESSURE...
271
271
Jul 11, 2010
07/10
by
Pratt, K. G
texts
eye 271
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Results are drawn from studies of the impact of advanced technologies on the design of an arrow-wing configuration. Information presented includes estimated benefits, effects of combinations of active control concepts, and constraints. Emphasis is placed on characteristics that are uniquely related to a large airframe featuring a slender body with a fixed wing of low aspect ratio, high sweep, and small thickness ratio.
Topics: AUTOMATIC FLIGHT CONTROL, C-5 AIRCRAFT, LIFT, WING LOADING, FORCE DISTRIBUTION, GUST LOADS,...
The application is considered of vortex lattice techniques to the problem of describing the aerodynamics and performance of statically thrusting propellers. A numerical lifting surface theory to predict the aerodynamic forces and power is performed. The chordwise and spanwise loading is modelled by bound vortices fixed to a twisted flat plate surface. In order to eliminate any apriori assumptions regarding the wake shape, it is assumed the propeller starts from rest. The wake is generated in...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMICS, HELICOPTER WAKES, VORTICES, AERODYNAMIC FORCES,...
217
217
Jun 1, 2011
06/11
by
deBoer, Gary; Scott, Car
texts
eye 217
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Carbon nanotubes, elongated molecular tubes with diameters of nanometers and lengths in microns, hold great promise for material science. Hopes for super strong light-weight material to be used in spacecraft design is the driving force behind nanotube work at JSC. The molecular nature of these materials requires the appropriate tools for investigation of their structure, properties, and formation. The mechanism of nanotube formation is of particular interest because it may hold keys to...
Topics: LOAD DISTRIBUTION (FORCES), WING LOADING, SCALE MODELS, DEFLECTION, FLAPPING, WINGS, BOMBER...
There is currently little data available for trend analysis of tile-rotor performance. This study analyzed the sensitivity of predicted tile-rotor performance to variations in six design parameters: disk loading, tip speed, solidity, download, wing loading, and wing thickness ratio. Two mission profiles were analyzed: a combat search-and-rescue (CSAR) mission and an antisubmarine warfare (ASW) mission. A tilt-rotor preliminary design code (TR-87) was used to perform computer simulations; and...
Topics: Tilt-rotor, Design parameters, Design trade-offs, Disk loading, Tip speed, Rotor solidity,...
162
162
May 23, 2011
05/11
by
Rajpal, Sandeep; Rhee, Do Jun; Lin, Sh
texts
eye 162
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The first part of this paper presents a simple and systematic technique for constructing multidimensional M-ary phase shift keying (MMK) trellis coded modulation (TCM) codes. The construction is based on a multilevel concatenation approach in which binary convolutional codes with good free branch distances are used as the outer codes and block MPSK modulation codes are used as the inner codes (or the signal spaces). Conditions on phase invariance of these codes are derived and a multistage...
Topics: JOINED WINGS, AIRCRAFT CONFIGURATIONS, WING LOADING, STRESS DISTRIBUTION, LEADING EDGES,...
259
259
Jul 11, 2010
07/10
by
Jansson, R. M
texts
eye 259
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comment 0
No Abstract Available
Topics: BENDING MOMENTS, WING LOADING, LIFT, LOAD DISTRIBUTION (FORCES), ROLLING MOMENTS, TURBULENCE, WING...
Crack propagation was studied in a full-scale wing structure under different simulated flight conditions. Omission of low-amplitude gust cycles had a small effect on the crack rate. Truncation of the infrequently occurring high-amplitude gust cycles to a lower level had a noticeably accelerating effect on crack growth. The application of fail-safe load (100 percent limit load) effectively stopped subsequent crack growth under resumed flight-simulation loading. In another flight-simulation test...
Topics: NASA Technical Reports Server (NTRS), CRACK PROPAGATION, FLIGHT SIMULATION, SCALE MODELS, AIRCRAFT...
Nonplanar load line, slender wing, elliptic wing, and infinite aspect ratio limit loading theories are developed. These are quasi two dimensional theories but satisfy wing boundary conditions at all points along the nonplanar spanwise extent of the wing. These methods are applicable for generalized configurations such as the laterally nonplanar wing, multiple nonplanar wings, or wing with multiple winglets of arbitrary shape. Two dimensional theory infers simplicity which is practical when...
Topics: NASA Technical Reports Server (NTRS), SLENDER WINGS, WING LOADING, WINGLETS, AERODYNAMIC...
385
385
May 23, 2011
05/11
by
McMaster, Matthew S
texts
eye 385
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Interest in thin sheet flows has recently been renewed due to their potential application in space radiators. Theoretical and experimental studies of the fluid dynamics and stability of thin liquid sheet flows have been carried out in this thesis. A computer program was developed to determine the cross-sectional shape of the edge cylinder given the cross-sectional area of the edge cylinder. A stability analysis was performed on a non-planer liquid sheet. A study was conducted to determine the...
Topics: AIRCRAFT DESIGN, CONTROLLABILITY, COMPUTERIZED SIMULATION, FIGHTER AIRCRAFT, AIRCRAFT MANEUVERS,...
An algorithm is reported for resizing structures subjected to combined thermal and mechanical loading. The algorithm is applicable to uniaxial stress elements (rods) and membrane biaxial stress members. Thermal Fully Stressed Design (TFSD) is based on the basic difference between mechanical and thermal stresses in their response to resizing. The TFSD technique is found to converge in fewer iterations than ordinary fully stressed design for problems where thermal stresses are comparable to the...
Topics: NASA Technical Reports Server (NTRS), STRUCTURAL DESIGN, THERMAL STRESSES, WINGS, ALGORITHMS,...
398
398
May 27, 2011
05/11
by
Wardle, Brian L
texts
eye 398
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Experimental and numerical work was conducted to better understand composite shell response to transverse loadings which simulate damage-causing impact events. The quasi-static, centered, transverse loading response of laminated graphite/epoxy shells in a [/-45(sub n)/O(sub n)](sub s) layup having geometric characteristics of a commercial fuselage are studied. The singly-curved composite shell structures are hinged along the straight circumferential edges and are either free or simply supported...
Topics: ANGLE OF ATTACK, SLENDER BODIES, PRESSURE DISTRIBUTION, REYNOLDS NUMBER, ESTIMATING, WING LOADING,...
An equivalent plate procedure is developed to provide a computationally efficient means of matching the stiffness and frequencies of flight vehicle wing structures for prescribed loading conditions. First, the equivalent plate is used to match the stiffness of a stiffened panel without damage and the stiffness of a stiffened panel with damage. For both stiffened panels, the equivalent plate models reproduce the deformation of a corresponding detailed model exactly for the given loading...
Topics: NASA Technical Reports Server (NTRS), WING LOADING, DAMAGE, MASS DISTRIBUTION, WINGS, FLEXIBILITY,...
The question of the effect of distribution and magnitude of spanwise circulation and shed vorticity from an airplane wing on the distribution pattern of agricultural products distributed from an airplane was studied. The first step in an analysis of this question is the determination of the actual distribution of lift along an airplane wing, from which the pattern of shed vorticity can be determined. A procedure is developed to calculate the span loading for flapped and unflapped wings of...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC COEFFICIENTS, AGRICULTURAL AIRCRAFT, CROP...
A part of the lower side of the main wing at the joint of the main spar with the fuselage frame was investigated. This wing beam area was simulated by a test specimen consisting of a spar boom of AZ 74 forging (7075 aluminum alloy modified with 0.3 percent Ag) and a portion of a honeycomb sandwich panel attached to the boom flange with steel bolts. The cross section was reduced to half scale. However, the flange thickness, the panel height, and the bolt size were full scale. Further, left and...
Topics: NASA Technical Reports Server (NTRS), AIRCRAFT STRUCTURES, FATIGUE TESTS, SAAB AIRCRAFT, ALUMINUM...
261
261
Jun 11, 2011
06/11
by
White, Michael J
texts
eye 261
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This paper presents the design and implementation of the Discrete Fourier Transform (DFT) algorithm on a reconfigurable processor system. While highly applicable to many engineering problems, the DFT is an extremely computationally intensive algorithm. Consequently, the eventual goal of this work is to enhance the execution of a floating-point precision DFT algorithm by off loading the algorithm from the computing system. This computing system, within the context of this research, is a typical...
Topics: AEROACOUSTICS, THIN AIRFOILS, UNSTEADY AERODYNAMICS, AERODYNAMIC LOADS, COMPUTATIONAL FLUID...
333
333
Jun 13, 2011
06/11
by
Masciarelli, James P.; Westhelle, Carlos H.; Graves, Claude A
texts
eye 333
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A performance evaluation of the Hybrid Predictor-corrector Aerocapture Scheme (HYPAS) guidance algorithm for aerocapture at Neptune is presented in this paper for a Mission to Neptune and the Neptune moon Triton. This mission has several challenges not experienced in previous aerocapture guidance assessments. These challengers are a very high Neptune arrival speed, atmospheric exit into a high energy orbit about Neptune, and a very high ballistic coefficient that results in a low altitude...
Topics: AERODYNAMIC FORCES, TIME DOMAIN ANALYSIS, AIRCRAFT CONTROL, SIMULATORS, DYNAMIC TESTS, WING...
247
247
Jun 21, 2010
06/10
by
Rogallo, V. L
texts
eye 247
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Null-type vacuum microbalance for measuring minute mechanical displacements
Topics: AERODYNAMIC CONFIGURATIONS, WIND TUNNEL MODELS, JET STREAMS (METEOROLOGY), LIFT FANS, VERTICAL...
209
209
Jun 1, 2011
06/11
by
Shin, Sung Y
texts
eye 209
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The initial focus of the project by the JSC laboratories will be to develop, test and implement a standardized complement of integrated physiological test (Integrated Testing Regimen, ITR) that will examine both system and intersystem function, and will be used to validate and certify candidate countermeasures. The ITR will consist of medical requirements (MRs) and non-MR core ITR tests, and countermeasure-specific testing. Non-MR and countermeasure-specific test data will be archived in a...
Topics: LOAD DISTRIBUTION (FORCES), BENDING MOMENTS, TORSIONAL STRESS, WING LOADING, SCALE MODELS, AIRCRAFT...
A method is described for using lifting-surface theory to obtain the pressure distribution on a wing with a trailing-edge flap or control surface. The loading has a logarithmic singularity at the flap edges, which may be determined directly by the method of matched asymptotic expansions. Expressions are given for the singular flap loading for various flap hinge line and side edge geometries, both for steady and unsteady flap deflection. The regular part of the flap loading must be obtained by...
Topics: NASA Technical Reports Server (NTRS), CONTROL SURFACES, PRESSURE DISTRIBUTION, WING LOADING,...
The benefits are assessed of span distributed loading concepts as applied to future commercial air cargo operations. A two phased program is used to perform this assessment. The first phase consists of selected parametric studies to define significant configuration, performance, and economic trends. The second phase consists of more detailed engineering design, analysis, and economic evaluations to define the technical and economic feasibility of a selected spanloader design. A conventional...
Topics: NASA Technical Reports Server (NTRS), CARGO AIRCRAFT, ECONOMIC FACTORS, TECHNOLOGY ASSESSMENT, WING...
A reduction in wing area, thickness, and span increases wing loading and lowers parasitic drag for a typical light airplane by 10.5%.
Topics: NASA Technical Reports Server (NTRS), DRAG REDUCTION, LIGHT AIRCRAFT, WING LOADING, AERODYNAMIC...
358
358
Jul 23, 2010
07/10
by
Meszaros, Stephen Pau
texts
eye 358
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This atlas shows the locations of and gives information about optical telescopes used for astronomical research in the United States as of late 1986. Those instruments with mirror or lens diameters of 3/4 m (approx. 30 inches) and larger are included. These telescopes are concentrated in the Southwest, on the West Coast and on the island of Hawaii.
Topics: AIRCRAFT CONFIGURATIONS, VELOCITY DISTRIBUTION, WING LOADING, MATHEMATICAL MODELS, NOISE REDUCTION,...
As part of an ongoing study of the spreading rate of lift-generated vortex wakes, the present investigation considers possible reasons as to why segments of lift-generated wakes sometimes depart from the main part of the wake to move rapidly in either an upward or downward direction. It is assumed that deficiencies or enhancements of the lift carry over across the fuselage-shrouded wing are the driving mechanism for departures of wake-segments. The computations presented first indicate that...
Topics: NASA Technical Reports Server (NTRS), FLIGHT SAFETY, WING LOADING, WAKES, VORTICES, FUSELAGES,...
A flow visualization technique was developed which allows the nature of lift-generated wakes behind aircraft models to be investigated. The technique was applied to models being towed underwater in a ship model basin. Seven different configurations of a small-scale model of a 747 transport aircraft were used to allow observation of typical vortex interactions and merging in multiple vortex wakes. It was established that the motion of the wake vortices is often sensitive to small changes in...
Topics: NASA Technical Reports Server (NTRS), AIRCRAFT WAKES, FLOW VISUALIZATION, VORTICES, AIRCRAFT...
The performance and economic benefits of a constrained application of Active Controls Technology (ACT) are identified, and the approach to airplane design is established for subsequent steps leading to the development of a less constrained final ACT configuration. The active controls configurations are measured against a conventional baseline configuration, a state-of-the-art transport, to determine whether the performance and economic changes resulting from ACT merit proceeding with the...
Topics: NASA Technical Reports Server (NTRS), ACTIVE CONTROL, AERODYNAMIC CONFIGURATIONS, AIRCRAFT DESIGN,...
Longitudinal control of a hang glider by weight shift is not always adequate for recovery from a vertical dive. According to Lanchester's phugoid theory, recovery from rest to horizontal flight ought to be possible within a distance equal to three times the height of fall needed to acquire level flight velocity. A hang glider, having a wing loading of 5 kg sq m and capable of developing a lift coefficient of 1.0, should recover to horizontal flight within a vertical distance of about 12 m. The...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC STABILITY, CLIMBING FLIGHT, GLIDERS, LIFT, LIGHT...
An assessment is made of the capabilities of the BQM-34E supersonic drone aircraft as a test bed research vehicle. This assessment is made based on a flight conducted for the purpose of obtaining flight test measurements of wing loads at various maneuver flight conditions. Flight plan preparation, flight simulation, and conduct of the flight test are discussed along with a presentation of the test data obtained and an evaluation of how closely the flight test followed the test plan.
Topics: NASA Technical Reports Server (NTRS), FLIGHT TESTS, RESEARCH AIRCRAFT, TARGET DRONE AIRCRAFT,...
712
712
Jul 12, 2010
07/10
by
NON
texts
eye 712
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Achievements in the aeronautics and space program by function are summarized. Activities in communications, Earth's resources and environment, space science, space transportation, international activities, and aeronautics are included.
Topics: ACTIVE CONTROL, STRUCTURAL WEIGHT, WIND TUNNEL TESTS, WINGLETS, AERODYNAMIC CONFIGURATIONS, BOEING...
An analytical study was made of an optimal gust alleviation system that employs a vertical gust sensor mounted forward of an aircraft's center of gravity. Frequency domain optimization techniques were employed to synthesize the optimal filters that process the corrective signals to the flaps and elevator actuators. Special attention was given to evaluating the effectiveness of lead time, that is, the time by which relative wind sensor information should lead the actual encounter of the gust....
Topics: NASA Technical Reports Server (NTRS), GUST ALLEVIATORS, OPTIMIZATION, SHORT TAKEOFF AIRCRAFT, WING...
Gust load calculations are extended to the range of conditions encountered by ultralight aircraft such as hang gliders. Having wing loadings of the order of 5 kg/sq m, these gliders acquire a substantial fraction of the motion of a gust within a distance of 1 or 2 m. Comparative loads and displacements for a small powered airplane having a wing loading of 50 kg sq m and for a commercial jet with 500 kg sq m are shown.
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, GLIDERS, GUST LOADS, LIGHT...
The development of a nonplanar lifting surface method having a continuous distribution of singularities and satisfying the tangent flow boundary condition on the mean camber surface is given. The method predicts some incompressible longitudinal aerodynamic coefficients of rectangular wings which have circular-arc camber. The solution method is of the integral-equation type and the resulting surface integrals are evaluated by either using numerical or analytical techniques, as are appropriate....
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC COEFFICIENTS, CAMBER, RECTANGULAR WINGS, ANGLE OF...
A modification of the simplified lifting-surface theory for wings with deflected flaps is presented and evaluated. The modification is simple and straightforward in application, and is shown to overcome the deficiency in the theory that results in an underestimation of flap lift effectiveness for wings that have low or moderate aspect ratios.
Topics: NASA Technical Reports Server (NTRS), JET FLAPS, LIFT DEVICES, LOW ASPECT RATIO, WING FLAPS,...
The use of delta wing aerodynamic design for modern fighter aircraft is discussed. Various current French fighter airplanes are utilized for comparisons.
Topics: NASA Technical Reports Server (NTRS), AERODYNAMICS, AIRCRAFT DESIGN, AIRCRAFT PERFORMANCE, DELTA...
Experimental data and correlative analytical results on the flutter and gust response characteristics of a torsion-free-wing (TFW) fighter airplane model are presented. TFW consists of a combined wing/boom/canard surface and was tested with the TFW free to pivot in pitch and with the TFW locked to the fuselage. Flutter and gust response characteristics were measured in the Langley Transonic Dynamics Tunnel with the complete airplane model mounted on a cable mount system that provided a near...
Topics: NASA Technical Reports Server (NTRS), GUST LOADS, TORSIONAL VIBRATION, TRANSONIC FLUTTER, WIND...
A high-performance glider is defined as a glider which has been designed to carry the pilot in a minimum of time a given distance, taking into account conditions which are as conveniently as possible. The present investigation has the objective to show approaches for enhancing the cross-country flight cruising speed, giving attention to the difficulties which the design engineer will have to overcome. The characteristics of the cross-country flight and their relation to the cruising speed are...
Topics: NASA Technical Reports Server (NTRS), AIRCRAFT DESIGN, AIRCRAFT PERFORMANCE, FLIGHT...
553
553
Mar 4, 2009
03/09
by
NASA LaRC Office of Education
movies
eye 553
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NASA Connect segment explaining how the Fibonacci sequence and the Golden Ratio help NASA engineers research, design and develop airplanes.
Topics: NASA Connect, Ratios, Proportions, Fibonacci Sequence, Golden Ratio, Airplanes, Design, Model,...
Source: http://nasa.ibiblio.org/details.php?videoid=6302&start=40&subject=Mathematics
This paper documents a parametric study of various aircraft wing-load test features that affect the quality of the resultant derived shear, bending-moment, and torque strain-gage load equations. The effect of the following on derived strain-gage equation accuracy are compared: single-point loading compared with distributed loading, variation in applied test load magnitude, number of applied load cases, and wing-box-only compared with control-surface loading. The subject of this study is an...
Topics: NASA Technical Reports Server (NTRS), AEROELASTICITY, BENDING MOMENTS, LOAD TESTS, WING LOADING,...
An assessment is presented of three separate programs that have incorporated advanced technology into the design of long-range passenger and cargo aircraft. The first technology centers around the use of a span-loaded cargo aircraft with the payload distributed along the wing. The second technology is the application of laminar flow control to the aircraft to reduce the aerodynamic drag. The last program evaluates the production of alternate aircraft fuels from coal and the use of liquid...
Topics: NASA Technical Reports Server (NTRS), AIRCRAFT DESIGN, CARGO AIRCRAFT, COMMERCIAL AIRCRAFT,...
This report summarizes the Integrated Application of Active Controls (IAAC) Technology to an Advanced Subsonic Transport Project, established as one element of the NASA/Boeing Energy Efficient Transport Technology Program. The performance assessment showed that incorporating ACT into an airplane designed to fly approximately 200 passengers approximately 2,000 nmi could yield block fuel savings from 6 to 10 percent at the design range. The principal risks associated with incorporating these...
Topics: NASA Technical Reports Server (NTRS), ACTIVE CONTROL, AVIONICS, FLY BY WIRE CONTROL, SUBSONIC...
The implementation of the changes to the program for Wing Aeroelastic Design and the development of a program to estimate aircraft fuselage weights are described. The equations to implement the modified planform description, the stiffened panel skin representation, the trim loads calculation, and the flutter constraint approximation are presented. A comparison of the wing model with the actual F-5A weight material distributions and loads is given. The equations and program techniques used for...
Topics: NASA Technical Reports Server (NTRS), APPROXIMATION, COMPUTER PROGRAMS, FUSELAGES, MATHEMATICAL...
An automated system to measure the change in wing twist and bending under aerodynamic load in a wind tunnel is described. The basic instrumentation consists of a single CCD video camera and a frame grabber interfaced to a computer. The technique is based upon a single view photogrammetric determination of two dimensional coordinates of wing targets with a fixed (and known) third dimensional coordinate, namely the spanwise location. The measurement technique has been used successfully at the...
Topics: NASA Technical Reports Server (NTRS), WING LOADING, AEROELASTICITY, TEST FACILITIES, CCD CAMERAS,...
