Tests were conducted in wind tunnels during April and May 1973, on a 0.030-scale replica of the Space Shuttle Vehicle Configuration 2A. Aerodynamic loads data were obtained at Mach numbers from 0.6 to 3.5. The investigation included tests on the integrated (launch) configuration and on the isolated orbiter (entry configuration). The integrated vehicle was tested at angles of attack and sideslip from -8 deg to +8 deg. The isolated orbiter was tested at angles of attack from -15 deg to +40 deg...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC LOADS, SPACE SHUTTLE ASCENT STAGE, SPACE SHUTTLE...
Tests on a 0.015 scale model of a supersonic transport were conducted at Mach numbers from 0.60 to 1.20. Tests of the complete model with three wing planforms, two different leading-edge radii, and various combinations of component parts, including both leading- and trailing-edge flaps, were made over an angle-of-attack range from about -6 deg to 13 deg and at sideslip angles of 0 deg and 2 deg.
Topics: NASA Technical Reports Server (NTRS), ARROW WINGS, MACH NUMBER, SCALE MODELS, SUPERSONIC...
Methods developed at the NASA Lewis Research Center for predicting the noise contributions from various aircraft noise sources were programmed to predict aircraft noise levels either in flight or in ground tests. The noise sources include fan inlet and exhaust, jet, flap (for powered lift), core (combustor), turbine, and airframe. Noise propagation corrections are available for atmospheric attenuation, ground reflections, extra ground attenuation, and shielding. Outputs can include spectra,...
Topics: NASA Technical Reports Server (NTRS), COMPUTER PROGRAMS, JET AIRCRAFT NOISE, NOISE PREDICTION...
Tabulated pressure data are presented for the orbiter fuselage, the orbiter bodyflap upper surface, and the orbiter bodyflap lower surface. For abstract, see N76-33263.
Topics: NASA Technical Reports Server (NTRS), JET EXHAUST, PLUMES, SPACE SHUTTLE ASCENT STAGE, SPACE...
The results of flight tests to determine the characteristics of spoiler roll control systems on three different light aircraft are summarized. Comparisons are made with wind tunnel data where available. Flight tests indicate that excellent roll characteristics can be achieved with spoilers. Yaw coupling with roll control inputs is virtually eliminated. Roll rates remain high when flaps are deployed at low speed. Very mild nonlinearities in control effectiveness exist, and there was no deadband...
Topics: NASA Technical Reports Server (NTRS), FLIGHT TESTS, LATERAL CONTROL, LIGHT AIRCRAFT, SPOILERS,...
Refinements in the lateral and longitudinal guidance for an automatic landing system capable of curved trajectories were studied. Wing flaps or drag flaps (speed brakes) were found to provide faster and more precise speed control than autothrottles. In the case of the lateral control it is shown that the use of the integral of the roll error in the roll command over the first 30 to 40 seconds of flight reduces the sensitivity of the lateral guidance to the gain on the azimuth guidance angle...
Topics: NASA Technical Reports Server (NTRS), AUTOMATIC LANDING CONTROL, BRAKES (FOR ARRESTING MOTION),...
This book was, written to supply the designer and the advanced aeronautical student with concise, practical information on the dynamics of airplane design. Partial Contents: Elements of theoretical fluid dynamics; Applied wing theory; Wind-tunnel tests; Airfoil data; Flaps and high-lift devices; Static stability and control; Dynamic stability; Parasite drag data; Engine and propeller considerations; Performance calculation--power curves; Performance estimation; Range and endurance; Special...
Topics: DTIC Archive, Diehl, Walter S, DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA...
Some type of servomechanism to control the blade pitch of a helicopter rotor may be desirable in certain cases, for example, in large rotors where excessive control forces and pitching moments may be encountered. Accordingly, tests were made on the Langley helicopter tower to determine the performance and control characteristics of an aerodynamic-servocontrolled helicopter rotor system. It was intended that an investigation of this configuration would give fundamental information of a general...
Topics: DTIC Archive, Carpenter, Paul J, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC,...
An experimental and computational investigation of the effect of lift-enhancing tabs on a two-element airfoil has been conducted. The objective of the study was to develop an understanding of the flow physics associated with lift-enhancing tabs on a multi-element airfoil. An NACA 63(2)-215 ModB airfoil with a 30% chord fowler flap was tested in the NASA Ames 7- by 10-Foot Wind Tunnel. Lift-enhancing tabs of various heights were tested on both the main element and the flap for a variety of flap...
Topics: NASA Technical Reports Server (NTRS), LIFT, AIRFOILS, TABS (CONTROL SURFACES), WIND TUNNEL TESTS,...
Using NASA's CV-990 aircraft, a delayed flap approach procedure was demonstrated to nine guest pilots from the air transport industry. Four demonstration flights and 37 approaches were conducted under VFR weather conditions. A limited pilot evaluation of the delayed flap procedure was obtained from pilot comments and from questionaires they completed. Pilot acceptability, pilot workload, and ATC compatibility were quantitatively rated. The delayed flap procedure was shown to be feasible, and...
Topics: NASA Technical Reports Server (NTRS), AIRCRAFT PILOTS, APPROACH CONTROL, FLAPS (CONTROL SURFACES),...
The results of an engineering and piloted simulator study to adapt a NASA developed-approach energy management system (AEMS) concept to the B727 are presented. The AEMS concept was developed and flight tested on a CV-990. The purpose of the AEMS is to reduce approach time, fuel, and noise by providing computer-driven cockpit displays to assist the pilot in flying optimized delayed flap approach (DFA) procedures. Development of the DFA flight profiles, the AEMS airborne digital computer...
Topics: NASA Technical Reports Server (NTRS), APPROACH CONTROL, BOEING 727 AIRCRAFT, FLAPS (CONTROL...
A flight test investigation was conducted to evaluate the effects of a flap configuration change on the vortex wake characteristics of a Boeing 747 (B-747) aircraft as measured by differences in upset response resulting from deliberate vortex encounters by a following Learjet aircraft and by direct measurement of the velocities in the wake. The flaps of the B-747 have a predominant effect on the wake. The normal landing flap configuration produces a strong vortex that is attenuated when the...
Topics: NASA Technical Reports Server (NTRS), E-4A AIRCRAFT, FLAPS (CONTROL SURFACES), FLIGHT TESTS,...
Longitudinal and lateral-directional stability characteristics of the 139-B orbiter (model 32-0) were obtained in a continuous flow hypersonic tunnel at Mach 10.3. Tests were made at Reynolds numbers of 1.04 million and 2.17 million (based on body length) over an angle of attack range of 12 deg to 36 deg at sideslip angles of 0 deg and minus 5 deg. Data were obtained at three elevon/body flap settings.
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, HYPERSONIC VEHICLES, REYNOLDS...
A limited re-evaluation of the production UH-60A Black Hawk anti-ice and deice systems was conducted to verify correction of deficiencies and shortcomings which were revealed during 1979-1980 icing tests. Testing consisted of 22.3 productive flight hours. The previous droop stop deficiency (failure of the droop stops to return to the shutdown position with ice accumulation on the rotor head) was corrected by the installation of a different droop stop with anti-ice protection. The previous...
Topics: DTIC Archive, Hanks,Marvin L, ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA,...
A full-scale BO-105 hingeless rotor system was tested in the NASA Ames 40- by 80-Foot Wind Tunnel on the rotor test apparatus. Rotor performance, rotor loads, and aeroelastic stability as functions of both collective and cyclic pitch, tunnel velocity, and shaft angle were investigated. This test was performed in support of the Rotor Data Correlation Task under the U.S. Army/German Memorandum of Understanding on Cooperative Research in the Field of Helicopter Aeromechanics. The primary objective...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC LOADS, AERODYNAMIC STABILITY, AEROELASTICITY,...
Acoustic spectral data obtained from a model-scale study of several over the wing (OTW) configurations with a 5:1 slot nozzle using various external deflectors are correlated in terms of deflector geometry and flow parameters. Variations in the deflector geometry include deflector size and deflector angle. In addition, geometry variations in flap setting and nozzle chordwise location are included. Three dominant noise sources are correlated: fluctuating lift noise, flap trailing edge noise, and...
Topics: NASA Technical Reports Server (NTRS), EXHAUST NOZZLES, NOZZLE GEOMETRY, SHORT TAKEOFF AIRCRAFT,...
During this test program, ten flights were conducted for a total of 22.8 hours, of which 14.6 hours were productive. Tests were performed in the Guardrail/Common Sensor System mission configuration ballasted to an average gross weight of 16,000 lb and centers of gravity at fuselage station 188.1 (forward) and 195.1 (aft). Test results were evaluated against military specification MIL-F-8785C for handling qualities. Performance data presented in the operator's manual were confirmed, as was the...
Topics: DTIC Archive, Miess, Joseph C, ARMY AVIATION ENGINEERING FLIGHT ACTIVITY EDWARDS AFB CA,...
A previously developed transient aeroelastic rotor response analysis for shipboard engage/disengage sequences is utilized in the present research. The blade has elastic flap and torsion degrees of freedom and the equations of motion are discretized using the finite element method. The discretized equations of motion are integrated for a specified rotor speed run-up or run-down profile. Blade element theory is used to calculate quasi-steady or unsteady aerodynamic loads in linear and nonlinear...
Topics: DTIC Archive, Geyer, William P., Jr., NAVAL AIR WARFARE CENTER AIRCRAFT DIV PATUXENT RIVER MD,...
The stalling characteristics of a 4.23-percent-thick,faired, double-wedge airfoil section with and without a plain nose flap were investigated. Flap chords equal to 12, 16, 20, and 25 percent of the airfoil chord were tested. Results of force and pressure-distribution measurements as well as studies of the boundary layer are presented for a Reynolds number of 5,800,000 and a Mach number of 0.17. The basic airfoil section stalled as a result of separation of flow from the entire upper surface....
Topics: DTIC Archive, Rose, Leonard M, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES...
The TAC (Tab-Assisted Control) and FlexTAC (Flexible Tab-Assisted Control) airfoils based on NACA 0018 sections are conceptual multi-element airfoil designs for future marine vehicle control surfaces. In addition to a relative motion between the stabilizer and the flap, either a rigid (for TAC) or a flexible (for FlexTAC) tab is used to augment the functionality of the control surfaces. The TAC airfoil has a front and a rear gap while FlexTAC airfoil has only the front gap. This report...
Topics: DTIC Archive, Lee, Yu-Tai, NAVAL SURFACE WARFARE CENTER CARDEROCK DIV BETHESDA MD, *COMPUTATIONAL...
This report describes the development of a method for numerically computing the inviscid transonic flow field over an airfoil with a leading-edge slat or a trailing-edge flap. The approach is to solve the full inviscid irrotational flow equations about two-element airfoil systems. The methodology consists of the development of a suitable computational plane and grid system through the application of a series of conformal mappings. The appropriate set of equations and boundary conditions are...
Topics: DTIC Archive, Grossman,B, GRUMMAN AEROSPACE CORP BETHPAGE N Y RESEARCH DEPT, *FLAPS(CONTROL...
Topics: DTIC Archive, Malmuth,N D, ROCKWELL INTERNATIONAL THOUSAND OAKS CALIF SCIENCE CENTER, *TRANSONIC...
Surgical production of the isolated, perfused porcine skin flap (IPPSF) model involved resection and suturing of an area of inguinal skin to form a tubular flap. Two days after production, the flap was cannulated and perfused in an environmentally controlled chamber. The objective of this work was to establish the IPPSF technology at Battelle for examining the dermatotoxicity of topically applied sulfur mustard (HD) and for assessing candidate countermeasures. Data obtained from an initial set...
Topics: DTIC Archive, Olson, Carl, BATTELLE MEMORIAL INST COLUMBUS OH, *TUBULAR STRUCTURES, *MUSTARD...
A test and preliminary analysis program was conducted to develop a data base and initial understanding of the interior noise of a Upper Surface Blowing STOL airplane using the YC-14 as a test vehicle. A data base has been secured consisting of concurrent cabin noise; exterior fuselage fluctuating pressures; fuselage wall vibrations; and associated aerodynamic, propulsive, and mechanical performance values covering the normal operating envelope of the airplane. Results from preliminary analysis...
Topics: DTIC Archive, Butzel, L. M., BOEING COMMERCIAL AIRPLANE CO SEATTLE WA, *JET TRANSPORT AIRCRAFT,...
Topics: DTIC Archive, NAVAL AIR SYSTEMS COMMAND PATUXENT RIVER MD, *COATINGS, *WEAR RESISTANCE, ACTUATORS,...
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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)
Two dimensional wind tunnel tests were conducted for the GA(W)-2 airfoil section with: 20% aileron, 25% slotted flap; 30% Fowler flap, and 10% slot-lip spoiler. All tests were conducted at a Reynolds number of 2,200,000 and a Mach Number of 0.13. In addition to force measurements, tuft studies were conducted for the slotted and Fowler flap configurations. Aileron and spoiler hinge moments were obtained by integration of surface pressure measurements. Tests results show that a value of 3.82 was...
Topics: NASA Technical Reports Server (NTRS), AIRFOILS, FLAPS (CONTROL SURFACES), SPOILER SLOT AILERONS,...
The NASA goal of reducing external aircraft noise by 10 dB in the near-term presents the acoustics community with an enormous challenge. This report identifies technologies with the greatest potential to reduce airframe noise. Acoustic and aerodynamic effects will be discussed, along with the likelihood of industry accepting and implementing the different technologies. We investigate the lower bound, defined as noise generated by an aircraft modified with a virtual retrofit capable of...
Topics: NASA Technical Reports Server (NTRS), AEROACOUSTICS, AIRFRAMES, AIRCRAFT NOISE, NOISE REDUCTION,...
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Direct lift control flap system for Boeing 367-80 aircraft
Topics: ACTUATORS, WING FLAPS, BOEING 707 AIRCRAFT, FLAP CONTROL, HYDRAULIC ACTUATOR, WING FLAP, AIRCRAFT...
A wind-tunnel investigation was made at low speed to determine the aerodynamic characteristics of a 45 deg sweptback untapered semispan wing of NACA 64A010 airfoil section normal to the leading edge and aspect ratio of 1.59 equipped with 25-percent-chord plain unsealed flaps having various spans and spanwise locations. Lift, drag, pitching-moment, and flap hinge-moment data were obtained for the wing with the various flaps deflected up to 60 deg. A comparison is made,with data obtained on the...
Topics: DTIC Archive, Johnson, Harold S, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC, *WIND...
The design and development of an A-4 landing flap is described. The flap was initially selected as a suitable component for obtaining flight experience with boron filaments. The existing production aluminum flap was redesigned utilizing boron skins supported by a full depth honeycomb core, while retaining some of the basic component aluminum parts for interchangeability reasons. A second flap design, utilizing graphite as the composite reinforcement and developed in accordance with advanced...
Topics: DTIC Archive, Hawley, A. V., MCDONNELL DOUGLAS CORP LONG BEACH CA DOUGLAS AIRCRAFT DIV,...
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Liquid-gaseous centrifugal separator for weightlessness environment
Topics: JETTISON SYSTEMS, RECOVERABLE SPACECRAFT, SPACE CAPSULES, FLAPS (CONTROL SURFACES)
On February 8, 1997, about 1935 Atlantic standard time, a Cessna 402, N318AB, operating under the provisions of Title 14 Code of Federal Regulations (CFR) Part 135 as Air Sunshine flight 319, crashed into the Caribbean Sea southwest of St. Thomas, U.S. Virgin Islands. The flight had been a regularly scheduled flight operating under visual flight rules (VFR) between St Thomas and St. Croix. The airplane was destroyed; two passengers were killed, and the pilot and two of the remaining four...
Topics: DTIC Archive, NATIONAL TRANSPORTATION SAFETY BOARD WASHINGTON DC, *AVIATION ACCIDENTS, *ACCIDENT...
Topics: DTIC Archive, Whittle, Jr., Edward F., Lipson, Stanley, NATIONAL AERONAUTICS AND SPACE...
It is proposed to design and build a wind tunnel model comprising a Douglas Aircraft Company three-element high-lift airfoil with internal actuators to move the flap vertically and horizontally under computer control. The model will be used to find the optimum flap location for a fixed angle of attack, slat position and flap deflection angle. The model will span the full tunnel width and lift will be measured by integration of pressure readings taken from midspan taps. It is proposed to conduct...
Topics: NASA Technical Reports Server (NTRS), ACTUATORS, AIRCRAFT MODELS, AIRFOILS, DOUGLAS AIRCRAFT, FLAPS...
The current study expands the application of computational fluid dynamics to three-dimensional multi-element high-lift systems by investigating the flow dynamics created by a slat edge. Flow is computed over a three-element high-lift configuration using an incompressible Navier-Stokes solver with structured, overset grids processed assuming full turbulence with the one-equation Baldwin-Barth turbulence model. The geometry consists of an unswept wing, which spans the wind tunnel test section, a...
Topics: NASA Technical Reports Server (NTRS), COMPUTATIONAL FLUID DYNAMICS, TURBULENCE MODELS,...
Exploratory wind tunnel tests are reported on a 74 deg. delta wing model. The potential of a vortex flap concept in reducing the subsonic lift dependent drag of highly swept, slender wings is examined. The suction effect of coiled vortices generated through controlled separation over leading edge flap surfaces to produce a thrust component is discussed. A series of vortex-flap configurations were investigated to explore the effect of some primary geometric variables.
Topics: NASA Technical Reports Server (NTRS), DELTA WINGS, FLAPS (CONTROL SURFACES), LEADING EDGES,...
Holographic interferometry data were acquired on an NACA 64A010 airfoil with an oscillating flap. The airfoil was installed in the Ames 11-Foot Transonic Wind Tunnel between splitter plates. Recordings were made at discrete phase angles of the oscillation. The interferometry results provided detailed flow visualization of the shock boundary-layer interaction and the separated flow. Quantitative results were extracted from the interferograms to produce pressure data. These results were compared...
Topics: NASA Technical Reports Server (NTRS), FLAPS (CONTROL SURFACES), FLOW DISTRIBUTION, HOLOGRAPHIC...
Boeing and a team from NASA, Army, DARPA, Air Force, MIT, UCLA, and U. of Maryland have successfully completed a wind tunnel test of the smart material actuated rotor technology (SMART) active flap rotor in the 40- by 80-foot wind-tunnel of the National Full-Scale Aerodynamic Complex at NASA Ames Research Center. The Boeing SMART active flap rotor is a full-scale, five-bladed bearingless MD 900 helicopter rotor modified with a piezoelectric-actuated trailing edge flap on each blade. The...
Topics: DTIC Archive, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCH CENTER,...
This report presents the development of an improved aerodynamic model of a flapping wing unmanned aerial vehicle (FWUAV). Flapping wing flight is a complex phenomenon encompassing unsteady effects, controls using multiple degrees of freedom, creation of leading edge vortices, significant wing deformation, and extreme angles of attack during flight. These phenomena are not well modeled using the traditional conceptual aerodynamic models originally developed for fixed wing and rotary wing...
Topics: DTIC Archive, ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD VEHICLE TECHNOLOGY DIRECTORATE,...
Research covers computational studies to explicate the fundamental physical mechanisms of unsteady viscous propulsor hydrodynamics: development of methods for obtaining time-accurate Navier- Stokes and Reynolds-averaged Navier-Stokes solutions for flows involving fixed and moving boundaries and separation; determination of appropriate time and length scales for such flows; and investigations of the interaction between natural and forced unsteady flows.
Topics: DTIC Archive, Stern, Fred, IOWA UNIV IOWA CITY, *UNSTEADY FLOW, *VISCOUS FLOW, *HYDRODYNAMICS,...
This rept. includes: THE TOPOLOGY OF THE AERODYNAMIC PARAMETERS OF AN AIRPLANE WITH A JET-AUGMENTED FLAP, by William H. Wentz, Jr. Thesis. June 1961, 58p. incl. illus.A preliminary analysis has been made of an STOL transport of 35,000 pounds gross weight equipped with features that produce a total performance not heretofore achieved in a single airplane. The prime goal of the analysis was to secure an airplane in which a pilot could consistently achieve landings such that the landing field...
Topics: DTIC Archive, RAZAK, KENNETH, WICHITA STATE UNIV KS SCHOOL OF ENGINEERING, *SHORT TAKEOFF AIRCRAFT,...
The purpose of the study was to develop a unified analytical procedure to evaluate the effects of passive high-lift devices on deflected- slipstream or tilt-wing V/STOL configurations. Methods were developed to predict the two-dimensional flapped airfoil characteristics to be used in a span load program. The span load results are used in procedures for estimating the coefficients of lift, longitudinal force, and moment for a wing partially immersed in a propeller slipstream. These...
Topics: DTIC Archive, Hebert, J, GENERAL DYNAMICS SAN DIEGO CA CONVAIR DIV, *LIFT, *VERTICAL TAKEOFF...
Wind tunnel investigations were conducted to probe the wake of a C-141 aircraft in an airdrop configuration. A rake with twelve 5-hole yaw head probes measured velocities at various positions in the wake, and these measurements were used to compute the vorticity of the wake. In addition, motion pictures and force measurements were taken with three differently sized extraction parachute models attached to the model aircraft by three extraction lines of different lengths. Correlation of parachute...
Topics: DTIC Archive, Huson,Gregory G, DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA...
An experimental investigation of the flap-lag stability of a hingeless rotor in hovering flight is presented and discussed. The rotor blade and hub configuration were selected such that the hub and blade had comparable levels of bending stiffness. Experimental measurements of the lag damping were made for various values of rotor rotational speed and blade pitch angle. Specifically at a blade pitch angle of 8 deg at three-quarters radius, the lag damping was determined over a range of rotational...
Topics: NASA Technical Reports Server (NTRS), AIRCRAFT CONTROL, FLAPS (CONTROL SURFACES), HOVERING...
The effects that deflection of conventional ailerons have on the lateral/directional characteristics of an oblique wing mounted on top of a body of revolution were measured. The wing had an aspect ratio of 6 (based on the unswept wing span) and was tested at various sweep angles ranging from 0 deg to 60 deg. Krueger nose flaps mounted on drooped-nose flaps were investigated on the downstream wing panel (for sweep angles of 45 deg and 60 deg) in an attempt to create more symmetrical spanwise...
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, AILERONS, BODIES OF REVOLUTION,...
Aerodynamic characteristics of a general aviation wing equipped with NACA 65 sub 2-415, NASA GA(W)-1, and NASA GA(PC)-1 airfoil sections were examined. The NASA GA(W)-1 wing was equipped with plain, split, and slotted partial- and full-span flaps and ailerons. The NASA GA(PC)-1 wing was equipped with plain, partial- and full-span flaps. Experimental chordwise static-pressure distribution and wake drag measurements were obtained for the NASA GA(PC)-1 wing at the 22.5-percent spanwise station....
Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, BODY-WING CONFIGURATIONS,...
The jet-diffuser ejector was integrated into the General Dynamics Corp. E205 fighter/attack aircraft to provide a VTOL capability for the aircraft. Some modifications of the ejector design were required to achieve the integration and stowage required for avoidance of deleterious effects on the aircraft performance during conventional flight. The ejector is designed to operate at a nozzle pressure ratio of 3 with an expected thrust augmentation of 1.95. The necessary thrust force for transition...
Topics: DTIC Archive, Alperin, Morton, FLIGHT DYNAMICS RESEARCH CORP VAN NUYS CA, *DIFFUSERS, *THRUST...
The flow features developing over a two-element NACA 0012 airfoil, with the rear portion serving as a trailing edge flap, were investigated using dye flow visualization in the NPS water tunnel. The original motivation for the work arose from a need to identify any potential to enhance maneuverability of aircraft to enable smoother landing under adverse flight situations. The flap portion was maneuvered in two different unsteady motion histories by a drive mechanism: a constant pitch rate motion...
Topics: DTIC Archive, Gonzalez,Edgar E, Naval Postgraduate School Monterey United States, unsteady...
All types of high-lift devices are covered. Both experimental and theoretical topics are reviewed, and the selected reports are listed by a subject and an author index.
Topics: DTIC Archive, Hebert, Jr , Joseph, GENERAL DYNAMICS SAN DIEGO CA CONVAIR DIV, *LIFT, *VERTICAL...
