195
195
Jun 21, 2010
06/10
by
Booth, F. W
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Liquid-gaseous centrifugal separator for weightlessness environment
Topics: JETTISON SYSTEMS, RECOVERABLE SPACECRAFT, SPACE CAPSULES, FLAPS (CONTROL SURFACES)
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2.0K
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On September 22-24, 1993, investigators from the First United States Microgravity Laboratory (USML-1) and the First United States Microgravity Payload (USMP-1) Missions met with the Microgravity Measurement Group (MGMG) in Huntsville, Alabama, to discuss science results and the microgravity environments from the respective missions. USML-1 was launched June 1992, and USMP-1 was launched October 1992. This document summarizes from the various investigations, the comprehensive results and...
Topics: WIND TUNNEL TESTS, AIRCRAFT BRAKES, DRAG DEVICES, LIFT, FLAPS (CONTROL SURFACES)
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231
Jul 11, 2010
07/10
by
Davis, J. C.; Mcnaughton, J. L
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The author has identified the following significant results. Spatial frequency analysis of ERTS-1 images appears to be useful in discriminating between large scale ground patterns in Kansas. Using parameters derived from the optical data processing of ERTS-1 images, sample areas from large physiographic categories have been accurately identified.
Topics: AERODYNAMIC CHARACTERISTICS, FLAPS (CONTROL SURFACES), GROUND EFFECT (AERODYNAMICS), AIRCRAFT...
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1.2K
Jul 11, 2010
07/10
by
NON
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No Abstract Available
Topics: EXTERNALLY BLOWN FLAPS, SCALE MODELS, SHORT TAKEOFF AIRCRAFT, WIND TUNNEL TESTS, AERODYNAMIC...
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292
Jun 20, 2010
06/10
by
Aoyagi, K.; Hickey, D. H.; Kirk, J. V
texts
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Simulated wind-tunnel investigation with jet-augmented flap
Topics: AIRCRAFT CONTROL, TURBOJET ENGINES, WIND TUNNEL MODELS, AERODYNAMIC STABILITY, FLAPS (CONTROL...
Topics: DTIC Archive, HAZEN, D. C., PRINCETON UNIV NJ JAMES FORRESTAL RESEARCH CENTER, *FLAPS(CONTROL...
307
307
Jul 26, 2010
07/10
by
Turner, G. B
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No Abstract Available
Topics: AIR FLOW, FLAPS (CONTROL SURFACES), FLOW DEFLECTION, JET FLAPS, WING FLAPS, AERODYNAMIC...
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425
Jul 23, 2010
07/10
by
Rennie, Michael W
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eye 425
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No Abstract Available
Topics: FLAPS (CONTROL SURFACES), LIFT, NACELLES, SPANWISE BLOWING, WIND TUNNEL TESTS, WINGS, ANGLE OF...
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185
Jul 9, 2010
07/10
by
ISAMUKHAMEDOVA, M. S.; KARAGEORGIY-ALKALAYEV, P. M.; LEYDERMAN, A. Y
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THE INJECTION OF CHARGE CARRIERS IN A SEMICONDUCTOR AFFORDS THE POSSIBILITY OF MODULATING EPSILON WITH CURRENT I BY CHANGING THE SATURATION OF LOCAL CENTERS. THE FUNCTION EPSILON (I) MAY INFLUENCE THE PASSAGE OF SPACE-CHARGE LIMITED CURRENTS. THE DISTRIBUTION OF THE FIELD AND POTENTIAL IN A SEMICONDUCTOR IS DETERMINED AND THE VOLT-AMPERE CHARACTERISTIC OF THE SPECIMEN IS DESCRIBED ANALYTICALLY.
Topics: AERODYNAMIC CONFIGURATIONS, FLAPS (CONTROL SURFACES), FLOW THEORY, LIFT AUGMENTATION, WING...
Flapping-wing offers unique force enhancement mechanisms over conventional flight methods for design of micro air vehicles (MAVs), especially in the low Reynolds number (Re) regime. The inherently unsteady nature of flapping kinematics is responsible for the primary force production, and also differentiates flapping-wing motion from conventional fixed and rotary wing configurations. From previous observation, the unsteady aerodynamic phenomena of flapping mechanism are not only sensitive to...
Topics: DTIC Archive, PURDUE UNIV LAFAYETTE IN, *WINGS, AERODYNAMICS, DRONES, FLAPS(CONTROL SURFACES),...
269
269
Jul 11, 2010
07/10
by
Herrera, B. J
texts
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No Abstract Available
Topics: CONTROL STABILITY, HELICOPTER DESIGN, ROTARY WINGS, STRUCTURAL VIBRATION, AEROELASTICITY, COMPUTER...
Topics: DTIC Archive, ANDERSON, A, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *AERODYNAMIC...
Fixed-base simulator tests of direct lift control were conducted during carrier landing approaches as a means of increasing flight path control pre cision. The direct lift control system that was tested consists of controlling the trailing-edge flaps of a Model A-3 = 10 degrees from the normal 35-degree deflection at normal flight control rates. Control of the flaps was achieved through a three-position switch on the control stick, operating in the same sense as the basic longitu dinal control...
Topics: DTIC Archive, DOUGLAS AIRCRAFT CO LONG BEACH CA, *CARRIER LANDINGS, *AERODYNAMIC LIFT,...
Topics: DTIC Archive, Platt, Robert C., NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC,...
Potential-flow and boundary-layer development calculations were continued. From the standpoint of high lift, it is advantageous to deflect a leading and trailing edge flap about 60 deg and to apply boundary layer suction in the region of the hinge line. Suction through a larger number of fine slots or through a porous surface will require smaller suction quantities and slightly less power than with a single slot. A Kruger flap together with suction at the leading edge may give slightly higher C...
Topics: DTIC Archive, NORTHROP AIRCRAFT INC HAWTHORNE CA, *WINGS, *BOUNDARY LAYER CONTROL, SUCTION SLOTS,...
Many lifting and propulsive surfaces in Nature are structurally flexible. How important is this flexibility on the lift and thrust forces generated and on the efficiency is an important and open question. The objective of the present work is to study some aspects of the unsteady flow associated with flapping flexible foils. The present research aims to experimentally study the effect of chordwise flexibility on the flow past a flexible flapping foil.
Topics: DTIC Archive, INDIAN INST OF SCIENCE BANGALORE (INDIA), *FLEXIBLE STRUCTURES, *UNSTEADY FLOW, WAKE,...
An invention to be used for controlling aircraft flaps is described. It is applicable to control systems with two coaxial output units which pivot simultaneously with respect to two fixed units and which are activated by two opposed, straight coaxial jacks.
Topics: NASA Technical Reports Server (NTRS), AIRCRAFT PARTS, CONTROL THEORY, FLAPS (CONTROL SURFACES),...
An analysis is presented of some aspects of the full scale wind tunnel tests of the Avrocar vehicle. Methods used to analyze force and pressure data are formulated and results are compared with theory and small scale model tests. Aerodynamically, the performance demonstrated by the first Avrocar vehicle in its initial configuration was disappointing in that a low lift curve slop, a large nose-up pitching moment and insufficient jet vectoring capability precluded flight in free air and in the...
Topics: DTIC Archive, WHITTLEY, D C, AVRO AIRCRAFT LTD (CANADA), *FLYING PLATFORMS, *VERTICAL TAKEOFF...
To provide flap with large upper surface radius as required for airplanes with over-the-wing blowing, distort upper surface of flap by actuator. Flap can be used as control surface at leading as well as trailing edges and, with minor modification, as variant of Jacobs-Hurkamp air flap.
Topics: NASA Technical Reports Server (NTRS), ACTUATORS, AIRCRAFT STRUCTURES, AIRFOILS, FLAPS (CONTROL...
This AFOSR YIP project provides a comprehensive understanding of the unique dynamics and control characteristics of tailless micro aerial vehicle equipped with flexible, articulated wings. This project has successfully demonstrated the ability to stabilize and control the robotic flapping testbed by using the phase synchronized nonlinear oscillators inspired by the central pattern generators in spinal cord. Furthermore, it is shown that the dihedral angle of the wing can be varied symmetrically...
Topics: DTIC Archive, ILLINOIS UNIV AT URBANA-CHAMPAIGN, *DRONES, *FLAPS(CONTROL SURFACES), AERODYNAMIC...
Objective of the research was to measure forces generated by flapping test-ring for rigid and wings having controlled flexibility to identify an efficient wing-kinematics. The results also helps in quantifying lift and thrust for potential wing-kinematics, so that one could select a suitable wing kinematics depending on the requirement.
Topics: DTIC Archive, JAWAHARLAL NEHRU CENTRE FOR ADVANCED SCIENTIFIC RESEARCH BANGALORE (INDIA), *WINGS,...
Topics: DTIC Archive, ROBINSON, ROSS B, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC,...
A flapped natural laminar flow airfoil for general aviation applications, the NLF(1)-0215F, has been designed and analyzed theoretically and verified experimentally in the Langley Low Turbulence Pressure Tunnel. The basic objective of combining the high maximum lift of the NASA low speed airfoils with the low cruise drag of the NACA 6 series airfoils has been achieved. The safety requirement that the maximum lift coefficient not be significantly affected with transition fixed near the leading...
Topics: NASA Technical Reports Server (NTRS), AIRFOILS, FLAPS (CONTROL SURFACES), LAMINAR FLOW, AERODYNAMIC...
The effects of propeller operation on the static longitudinal stability of single-engine tractor monoplanes are analyzed, and a simple method is presented for computing power-on pitching-moment curves for flap-retracted flight conditions. The methods evolved are based on the results of powered model wind-tunnel investigations of 28 model configurations. Correlation curves are presented from which the effects of power on the downwash over the tail and the stabilizer effectiveness can be rapidly...
Topics: DTIC Archive, Weil, Joseph, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC,...
An investigation was made to determine experimentally the effects of a linked differential flap system upon the effective dihedral characteristics of a powered aircraft. The differential flap system consisted of two flaps so connected as to cause rolling moments automatically opposing those of slipstream effects. Results indicate that the negative dihedral changes caused by power may be reduced or eliminated by use of the differential flap system. Differential flaps also increased the static...
Topics: DTIC Archive, Pitkin, Marvin, NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON...
A first-of-its-kind demonstration of the use of localized, non-harmonic active flap motions, for suppressing low frequency, in-plane rotor noise, is reported in this paper. Operational feasibility is verified via testing of the full-scale AATD/Sikorsky/UTRC active flap demonstration rotor in the NFAC's 40- by 80-Foot anechoic wind tunnel. Effectiveness of using localized, non-harmonic active flap motions are compared to conventional four-per-rev harmonic flap motions, and also active flap...
Topics: DTIC Archive, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCH CENTER,...
The main objective of the work was to understand the effect of flexibility on flapping foils. Flexibility is inevitably present, though, to different degrees, in the wings of many natural fliers and in the fins and tails of fish. The loads on such foils are related to the circulations developed around the foils and indirectly to the circulations in the vortices that are shed in the wake. The foils and fins in nature are three dimensional and the interactions between the fluid and the flexible...
Topics: DTIC Archive, INDIAN INST OF SCIENCE BANGALORE (INDIA), *AIRFOILS, *FLAPS(CONTROL SURFACES),...
An investigation of the longitudinal aerodynamic characteristics of an aspect ratio 4.735 airfoil having a 9.8 percent chord blowing flap has been made in an out of ground influence over the endless moving belt ground plane in the 5.18 meter test section of the former Langley 300 MPH 7 by 10 foot wind tunnel. For flap deflections of 30 deg or less, at a height of 0.25 span, ground effect was negligible; but at this ground height, at a flap deflection of 60 deg and a lift coefficient of 8.0, the...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, AIRFOILS, FLAPS (CONTROL...
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...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
209
209
Jun 1, 2011
06/11
by
Shin, Sung Y
texts
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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...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
The state of the art of STOL aerodynamic technology for selected lift/propulsion concepts was surveyed to identify the available test data and prediction methods in the literature. The report consists of two volumes. In Volume I important areas of technology and information necessary for the evaluation of STOL aircraft aerodynamics are listed; the aerodynamic test data and prediction methodology relevant to the deflected slipstream and externally blown flap concepts are assessed, with emphasis...
Topics: DTIC Archive, May, Fred, BOEING VERTOL CO PHILADELPHIA PA, *AERODYNAMICS, *SHORT TAKEOFF AIRCRAFT,...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
An adjustable airfoil is described for varying the geometry of a jet inlet and an ejector inlet in a jet engine for providing thrust augmentation and noise reduction. The airfoil comprises essentially a plurality of segments which are extended radially outward and retracted relative to the longitudinal axis of the engine as a function of a change in the pressure differential between the upstream and downstream surfaces of the airfoil. A servo mechanism responsive to the change in the pressure...
Topics: NASA Technical Reports Server (NTRS), AIR INTAKES, FLAPS (CONTROL SURFACES), THRUST AUGMENTATION,...
Measurements of the fluctuating pressures on the wing surface of an upper-surface-blown powered-lift model and a JT15 engine were obtained using two types of pressure transducers. The pressures were measured using overall-fluctuating pressures and power spectral density analyses for various thrust settings and two jet impingement angles. Comparison of the data from the two transducers indicate that similar results are obtained in the lower frequency ranges for both transducers. The data also...
Topics: NASA Technical Reports Server (NTRS), PRESSURE OSCILLATIONS, PRESSURE SENSORS, TRANSDUCERS,...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
Development of the Body Flap Actuation Subsystem for Space Shuttles included alterations from the original design to mechanical stops, planet gears, control valves, and solenoid valves. The mechanical stops were redesigned to absorb stall load and rotating inertia of the hydraulic motors instead of only stall load. The institution of a quill shaft (torsion spring) was a successful solution. The planet gears in the geared rotary actuators developed cracks during testing. This failure was...
Topics: NASA Technical Reports Server (NTRS), ACTUATION, ACTUATORS, FLAPS (CONTROL SURFACES), SPACE...
The objective of this program was to evaluate two types of ventilator kits for maximum cost effectiveness. The kits shown on the following page are: (1) Pedal Ventilator Kit, and (2) the Kearny Pump Kit. The two units were previously developed by GARD in 1969 for DCPA under Contract No. DAHC20-68-C-0123. An engineering study was conducted on the ventilator kits to determine the potential manufacturing economies. Based on the conclusions of the study, the fabrication drawings, military...
Topics: DTIC Archive, Buday,John M, GARD INC NILES ILL, *VENTILATORS, *FALLOUT SHELTERS, FLAPS(CONTROL...
A wind tunnel investigation was carried out on a semi-span wing model to assess the feasibility of controlling vortices emanating from outboard flaps and tip-flaps by actively varying the degree of boundary layer separation. Separation was varied by means of perturbations produced from segmented zero-efflux oscillatory blowing slots, while estimates of span loadings and vortex sheet strengths were obtained by integrating wing surface pressures. These estimates were used as input to inviscid...
Topics: NASA Technical Reports Server (NTRS), VORTICES, FLAPS (CONTROL SURFACES), BOUNDARY LAYER...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
Wind tunnel tests have been made to determine the aerodynamic section characteristics of an NACA 0009 airfoil with plain flaps 25 and 50 percent of the airfoil chord. The flaps were tested independently and in combination. Results of the investigation indicated that the larger flap would provide greater lift increments but would lose lift effectiveness at the higher deflect ions and at a lower angle of attack than would the smaller flap. The hinge-moment and lift-effectiveness parameters for...
Topics: DTIC Archive, Spearman, M L, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC,...
An Improved Semi empirical Method has been developed to estimate the static aerodynamics of configurations that use a trailing edge flap for control. The method is based on deflecting the full aft-located lifting surface an amount that allows the normal force coefficient to be equal to that generated by the deflected flap. A transfer in pitching moments and a modified axial force coefficient is derived to complete the set of static aerodynamics. The method is derived using theoretical methods...
Topics: DTIC Archive, Moore, Frank G, NAVAL SURFACE WARFARE CENTER DAHLGREN DIV VA, *AERODYNAMIC...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
Topics: DTIC Archive, Fei,Xu, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *FLAPS(CONTROL SURFACES),...
471
471
Jun 2, 2011
06/11
by
Liu, Tianshu; Kuykendoll, K.; Rhew, R.; Jones, S
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This paper describes the avian wing geometry (Seagull, Merganser, Teal and Owl) extracted from non-contact surface measurements using a three-dimensional laser scanner. The geometric quantities, including the camber line and thickness distribution of airfoil, wing planform, chord distribution, and twist distribution, are given in convenient analytical expressions. Thus, the avian wing surfaces can be generated and the wing kinematics can be simulated. The aerodynamic characteristics of avian...
Topics: LATERAL CONTROL, DEFLECTION, FLAPS (CONTROL SURFACES), LIFT, SIKORSKY AIRCRAFT, WIND TUNNEL TESTS,...
Tests carried out in November 1981 on the stationary flap of STOL test planes at Kakuda Labs are described. Acoustic pressure, outer plate temperature of the fore flap, and acceleration, strain, and temperature of the outer plate of the main flap were measured. High load turbine inlet distortion experiments were also performed. Results of these experiments are discussed.
Topics: NASA Technical Reports Server (NTRS), FLAPS (CONTROL SURFACES), SHORT TAKEOFF AIRCRAFT, SOUND...
