What is submerged inlet

The purpose of indirect drainage is to prevent sewage from backing up into the unit being drained, which could expose food products to sewage. Using an air gap to prevent backflow In most situations, an air gap is the most cost-effective and reliable form of backflow prevention. An air gap should be used to prevent backflow from rainwater tanks and other water supply tanks into the mains-supplied water system.

Submerged inlet means a public water supply pipe extending into a tank, vessel fixture or appliance where the liquid level or overflow rim is higher than the inlet. The best way to prevent backflow is to avoid creating a cross-connection. Do not attach a hose to a faucet unless a backflow prevention device, such as a vacuum breaker, is attached. In Ga, hand sinks can drain directly OR indirectly into a floor sink or hub drain. The only drains that need trap primers are area floor drains on the sanitary system.

The methods presented are useful for determining the inlet weight flows, total pressure recovery, and aerodynamic drag coefficients for given inlet geometric designs. Limited geometric input data is required to use this inlet performance prediction methodology. The analyses presented here may also be used to perform inlet preliminary design studies. The calculated inlet performance parameters may be used in subsequent engine cycle analyses or installed engine performance calculations for existing uninstalled engine data.

Development of Wing Inlets. Lift, drag, internal flow, and pressure distribution measurements were made on a low-drag airfoil incorporating various air inlet designs.

Two leading-edge air inlets are developed which feature higher lift coefficients and critical Mach than the basic airfoil. Higher lift coefficients and critical speeds are obtained for leading half of these inlet sections but because of high suction pressures near exist, slightly lower critical speeds are obtained for the entire inlet section than the basic airfoil.

Drought and submergence tolerance in plants. The Origin of Inlet Buzz in a Mach 1. Supersonic inlets with external compression, having a good level performance at the critical operating point, exhibit a marked instability of the flow in some subcritical operation below a critical value of the capture mass flow ratio.

This takes the form of severe oscillations of the shock system, commonly known as "buzz". The underlying purpose of this study is to indicate how Detached Eddy Simulation DES analysis of supersonic inlets will alter how we envision unsteady inlet aerodynamics, particularly inlet buzz.

Presented in this paper is a discussion regarding the physical explanation underlying inlet buzz as indicated by DES analysis. It is the normal shock wave boundary layer separation along the spike surface which reduces the capture mass flow that is the controlling mechanism which determines the onset of inlet buzz, and it is the aerodynamic characteristics of a choked nozzle that provide the feedback mechanism that sustains the buzz cycle by imposing a fixed mean corrected inlet weight flow.

Supersonic Wind Tunnel SWT show a strong similarity both in turbulent flow field structure and shock wave formation during the buzz cycle. This demonstrates the value of DES analysis for the design and understanding of supersonic inlets. Within a short time of the first flight of the Wright brothers in , the United States government recognized the importance of fostering development in the new and critical field of aeronautics.

NASA's predecessor, the National Advisory Committee for Aeronautics NACA , was chartered by Congress in specifically "to supervise and direct the scientific study of the problems of flight, with a view to their practical solution.

The results of the NACA 's research appeared in more than 16, research reports of one type or another, distributed widely for the benefit of all.

Small inlet optical panel and a method of making a small inlet optical panel. An optical panel having a small inlet , and a method of making a small inlet optical panel, are disclosed, which optical panel includes a individually coating, stacking, and cutting a first plurality of stacked optical waveguides to form an outlet face body with an outlet face, individually coating, stacking, and cutting a second plurality of stacked optical waveguides to form an inlet face body with an inlet face, and connecting an optical coupling element to the first plurality and to the second plurality, wherein the optical coupling element redirects light along a parallel axis of the inlet face to a parallel axis of the outlet face.

In the preferred embodiment of the present invention, the inlet face is disposed obliquely with and askew from the outlet face. The paths of cloud droplets into two engine inlets have been calculated for a wide range of meteorological and flight conditions. The amount of water in droplet form ingested by the inlets and the amount and distribution of water impinging on the inlet walls are obtained from these droplet-trajectory calculations.

In both types of inlet , a prolate ellipsoid of revolution represents either part or all of the forebody at the center of an annular inlet to an engine. The configurations can also represent a fuselage of an airplane with side ram-scoop inlets.

The studies were made at an angle of attack of 0 degree. The principal difference between the two inlets studied is that the inlet -air velocity of one is 0. The studies of the two velocity ratios lead to some important general concepts of water ingestion in inlets. Orders of Magnitude. The effects of NACA airfoil modification on aerodynamic performance improvement and obtaining high lift coefficient and post-stall airfoil. In this study, aerodynamic performances of NACA airfoils with distinct modification are numerically investigated to obtain high lift coefficient and post-stall airfoils.

NACA airfoil is divided into two part thought chord line then suction sides kept fixed and by changing the thickness of the pressure side new types of airfoil are created. Numerical experiments are then conducted by varying thickness of NACA from lower surface and different relative thicknesses asymmetrical airfoils are modified and NACA , , , , , , , are created and simulated by using COMSOL software.

Design and Analysis Tools for Supersonic Inlets. Computational tools are being developed for the design and analysis of supersonic inlets. The objective is to update existing tools and provide design and low-order aerodynamic analysis capability for advanced inlet concepts. The Inlet Tools effort includes aspects of creating an electronic database of inlet design information, a document describing inlet design and analysis methods, a geometry model for describing the shape of inlets , and computer tools that implement the geometry model and methods.

The geometry model has a set of basic inlet shapes that include pitot, two-dimensional, axisymmetric, and stream-traced inlet shapes. The inlet model divides the inlet flow field into parts that facilitate the design and analysis methods. The inlet geometry model constructs the inlet surfaces through the generation and transformation of planar entities based on key inlet design factors.

Future efforts will focus on developing the inlet geometry model, the inlet design and analysis methods, a Fortran 95 code to implement the model and methods. Other computational platforms, such as Java, will also be explored. Information is given on the number of NACA holdings in paper copy, bound volumes, and microfiche.

Additional information is given on the bibliographic records and availability. Wind-tunnel investigation of an NACA airfoil with 30 percent-chord venetian-blind flaps.

Report presents the results of an investigation made in the NACA 7 by foot wind tunnel of a NACA airfoil with percent-chord venetian-blind flaps having one, two, three, and four slats of Clark y section. The three-slat arrangements was aerodynamically the best of those tested but showed practically no improvement over the comparable arrangement used in the preliminary tests published in NACA Technical Report No.

The multiple-slat flaps gave slightly higher lift coefficients than the one-slat Fowler flap but gave considerably greater pitching-moment coefficients. An analysis of test data indicates that substitution of a thicker and more cambered section for the Clark y slats should improve the aerodynamic and the structural characteristics of the venetian-blind flap.

The facility was built in the mids to simulate the atmospheric conditions that caused ice to build up on aircraft. The foot diameter drive fan, seen in this photograph, created air flow velocities up to miles per hour. The s were prime years for the Icing Research Tunnel. NACA engineers had spent the s trying to resolve the complexities of the spray bar system. The final system put into operation in included six horizontal spray bars with 80 nozzles that produced a 4- by 4-foot cloud in the test section.

The icing tunnel was used for extensive testing of civilian and military aircraft components in the s. The NACA also launched a major investigation of the various methods of heating leading edge surfaces.

Lewis researchers also made significant breakthroughs with icing on radomes and jet engines. Although the Icing Research Tunnel yielded major breakthroughs in the s, the Lewis icing research program began tapering off as interest in the space program grew.

The icing staff was transferred to other research projects and the icing tunnel was temporarily mothballed. Scramjet Inlets. This paper will describe the two prototypes it has developed and the present production system configuration. DigiDoc configuration integrates the on-line catalog database World Wide Web interface and PDF technology to provide a powerful and flexible search and retrieval system. It describes in detail significant achievements and lessons learned in terms of data conversion, storage technologies, full-text searching and retrieval, and image databases.

The conclusions from the experiences of digitization and full- text access and future plans for DigiDoc system implementation are discussed. Typical models and the testing technique used in the NACA free-spinning wind tunnel are described in detail.

The results of tests on two models afford a comparison between the spinning characteristics of scale models in the tunnel and of the airplanes that they represent. Inlet -engine matching for SCAR including application of a bicone variable geometry inlet. Airflow characteristics of variable cycle engines VCE designed for Mach 2. This is a formidable requirement for conventional, high performance, axisymmetric, translating centerbody mixed compression inlets.

An alternate inlet is defined, where the second cone of a two cone center body collapses to the initial cone angle to provide a large off-design airflow capability, and incorporates modest centerbody translation to minimize spillage drag. Estimates of transonic spillage drag are competitive with those of conventional translating centerbody inlets. The inlet 's cruise performance exhibits very low bleed requirements with good recovery and high angle of attack capability.

Spiral inlets for steam turbines. This paper deals with the design process of special nozzle blades for spiral inlets. Spiral inlets are used for the first stages of high pressure and intermediate pressure steam turbines with both reaction and impulse blades when throttling or sliding pressure control is applied. They improve the steam flow uniformity from the inlet pipe and thus decrease the aerodynamic losses.

The proposed evaluation of the inlet angle is based on the free vortex law. Axisymmetric inlet minimum weight design method. An analytical method for determining the minimum weight design of an axisymmetric supersonic inlet has been developed.

The goal of this method development project was to improve the ability to predict the weight of high-speed inlets in conceptual and preliminary design. The initial model was developed using information that was available from inlet conceptual design tools e.

Stiffened shell construction was assumed. Mass properties were computed by analyzing a parametric cubic curve representation of the inlet geometry. Design loads and stresses were developed at analysis stations along the length of the inlet. The equivalent minimum structural thicknesses for both shell and frame structures required to support the maximum loads produced by various load conditions were then determined. Preliminary results indicated that inlet hammershock pressures produced the critical design load condition for a significant portion of the inlet.

By improving the accuracy of inlet weight predictions, the method will improve the fidelity of propulsion and vehicle design studies and increase the accuracy of weight versus cost studies.

Submergible torch for treating waste solutions and method thereof. The submergible torch is ignited to form a flame within the combustion chamber of the submergible torch.

On the tsunami wave- submerged breakwater interaction. The tsunami wave loads on a submerged rigid breakwater are inertial.

It is the result arising from the simple calculation method here proposed, and it is confirmed by the comparison with results obtained by other researchers. The method is based on the estimate of the speed drop of the tsunami wave passing over the breakwater. The calculation is rigorous for a sinusoidal wave interacting with a rigid submerged obstacle, in the framework of the linear wave theory.

This new approach gives a useful and simple tool for estimating tsunami loads on submerged breakwaters. An unexpected novelty come out from a workedmore » example: assuming the same wave height, storm waves are more dangerous than tsunami waves, for the safety against sliding of submerged breakwaters. Airline manufacturers would soon be introducing jet engines on their passenger aircraft, and there was concern regarding the noise levels for both the passengers and public on the ground.

This problem was particularly pronounced at high subsonic speeds. The researchers found the majority of the noise occurred in the low and middle octaves.

These investigations were enhanced with a series of flights using the FB Starfire. The missions measured wall-pressure, turbulence fluctuations, and mean velocity profiles. Mach 0. The results substantiated the wind tunnel findings. Inlet design for high-speed propfans. A two-part study was performed to design inlets for high-speed propfan installation.

The first part was a parametric study to select promising inlet concepts. A wide range of inlet geometries was examined and evaluated - primarily on the basis of cruise thrust and fuel burn performance. In the second part of this study, inlet design points were chosen to optimize the net installed thrust, and detailed design of the two inlet configurations was performed.

An analytical methodology was developed to account for propfan slipstream effects, transonic flow efects, and three-dimensional geometry effects. Using this methodology, low drag cowls were designed for the two inlets.

The noise produced by the large jet engines, however, would pose a considerable problem for communities near airports. This problem was demonstrated at the Inspection by an NACA Lewis researcher who played longplay LP audio records of military jet engines for an audience.

The pressures resulting from this turbulence produced sound waves. Afterwards, they determined that the addition of an NACA -developed ejector reduced the noise levels without diminishing thrust. Harvesting microalgal biomass using submerged microfiltration membranes. This study was performed to investigate the applicability of submerged microfiltration as a first step of up-concentration for harvesting both a freshwater green algae species Chlorella vulgaris and a marine diatom Phaeodactylum tricornutum using three lab-made membranes with different porosity.

The filtration performance was assessed by conducting the improved flux step method IFM and batch up-concentration filtrations. The cost analysis was estimated based on the data of a related full-scale submerged membrane bioreactor MBR. Overall results suggest that submerged microfiltration for algal harvesting is economically feasible. All rights reserved. The test articles were lifted by a two-rail Shaw box crane through the high-bay and the second-story test chamber before being lowered into the test section.

Technicians then spent days or weeks hooking up the supply lines and data recording telemetry. The engines were mounted on wingspans that stretched across the test section. The balance frame included six devices that recorded data and controlled the engine. The measurements were visible in banks of manometer boards next to the control room.

Photographs recorded the pressure levels in the manometer tubes, and the computing staff manually converted the data into useful measurements. The lid was sealed into place using hand-turned locks accessible from the viewing platform. The lid had viewing windows above and below the test article, which permitted the filming and visual inspection of the tests. A rash of passenger aircraft crashes in and spurred a White House call for an investigatory board staffed by members of the Civil Aeronautics Board, military, and the NACA.

The group addressed fire segregation, extinguishment, and prevention. The Lewis team simulated situations in which an aircraft failed to become airborne during takeoff resulting in crashes into embankments and other objects.

The Lewis researchers initially used surplus C and C military transport planes. In these situations, the aircraft generally suffered damage to its fuel system and other components, but was structurally survivable. The aircraft were mounted to a rail that ran down a foot long test runway.

The aircraft was secured at the starting point with an anchor pier so it could get its engines up to takeoff speed before launching down the track. Barriers at the end of the runway were designed to simulate a variety of different types of crashes.

Telemetry and high-speed cameras were crucial elements in these studies. The preliminary testing phase identified potential ignition sources and analyzed the spread of flammable materials. Accretion of a New England U.

Sediment accumulation rates were determined at several sites throughout Nauset Marsh Massachusetts, U. The barrier spit fronting the Spartina-dominated study site has a complex geomorphic history of inlet migration and over-wash events. This study evaluates sediment accumulation rates in relation to inlet migration, storm events, and sea-level rise.

The marker horizon technique displayed strong temporal and spatial variability in response to storm events and proximity to the inlet. Sediment accumulation rates of up to 24 mm year -1 were recorded in the immediate vicinity of the inlet during a period that included several major coastal storms, while feldspar sites remote from the inlet had substantially lower rates trace accumulation to 2.

During storm-free periods, accumulation rates did not exceed 6. Based on Cs 3. At one site, the Pb-based sedimentation rate and rate of relative sea-level rise were nearly similar and peat rhizome analysis revealed that Distichlis spicata recently replaced this once S. Horizon markers are useful in evaluating the role of short-term events, such as storms or inlet migration, influencing marsh sedimentation processes.

However, sampling methods that integrate marsh sedimentation over decadal time scales are preferable when evaluating a systems response to sea. The barrier spit fronting the Spartima-dominated study site has a complex geomorphic history of inlet migration and overwash events. This study evaluates sediment accumulation rates in relation to inlet migration, storm events and sea-level rise.

Sediment accumulation rates of up to 24 mm year-1 were recorded in the immediate vicinity of the inlet during a period that included several major coastal storms, while feldspar sites remote from the inlet had substantially lower rates trace accumulation to 2.

However, sampling methods that integrate marsh sedimentation over decadal time scales are preferable when evaluating a systems response to sea-level rise.

The conference on Turbojet-Engine Thrust-Augmentation Research was organized by the NACA to present in summarized form the results of the latest experimental and analytical investigations conducted at the Lewis Flight Propulsion Laboratory on methods of augmenting the thrust of turbojet engines. The technical discussions are reproduced herewith in the same form in which they were presented.

The original presentation in this record are considered as complementary to, rather than substitutes for, the committee's system of complete and formal reports. The laboratory had undertaken a multi-year investigation into the causes and preventative measures for fires resulting from low altitude aircraft crashes. The program was expanded in the mids to include the study of crash impact on passengers, new types of types of seat restraints, and better seat designs.

The impact program began by purposely wrecking surplus transport Fairchild C Packet and Piper Cub aircraft into barricades at the end of a test runway. After determining the different loads experienced during a crash and the effects on the passengers, the NACA researchers began designing new types of seats and restraints.

Rectangular-to-elliptical shape-transition REST inlets are of interest for use on scramjet engines because they are efficient and integrate well with the forebody of a planar vehicle.

The classic design technique by Smart for these inlets produces an efficient inlet but the complex three-dimensional viscous effects are only approximately included. Certain undesirable viscous features often occur in these inlets. In the present work, a design toolset has been developed which allows for rapid design of REST-class inlet geometries and the subsequent Navier-Stokes analysis of the inlet performance.

This gives the designer feedback on the complex viscous effects at each design iteration. This new tool is applied to design an inlet for on-design operation at Mach 8. The tool allows for rapid investigation of design features that was previously not possible. The outcome is that the inlet shape can be modified to affect aspects of the flow field in a positive way. Supersonic Elliptical Ramp Inlet. A supersonic inlet includes a supersonic section including a cowl which is at least partially elliptical, a ramp disposed within the cowl, and a flow inlet disposed between the cowl and the ramp.

The ramp may also be at least partially elliptical. Stepped inlet optical panel. An optical panel includes stacked optical waveguides having stepped inlet facets collectively defining an inlet face for receiving image light, and having beveled outlet faces collectively defining a display screen for displaying the image light channeled through the waveguides by internal reflection. Investigations of the pressure distribution, the profile drag, and the location of transition for a inch-chord percent-thick N.

A 8-foot high-speed wind tunnel for the purpose of aiding in the development of a thick wing for high-speed airplanes. The tests were made at a lift coefficient of 0. The effect on the profile drag of fixing the transition point was also investigated. The effect of compressibility on the rate of increase of pressure coefficients was found to be greater than that predicted by a simplified theoretical expression for thin wings. The results indicated that, for a lift coefficient of 0.

The value of the profile-drag coefficient at a Reynolds Number of 4,, was 0. The increase in the profile-drag coefficient for a given movement of the transition point was about three times as large as the corresponding increase for the N. Transition determinations indicated that, for Reynolds Numbers up to? Computer investigations of the turbulent flow around a NACA airfoil wind turbine. In this work, computer investigations are carried out to study the flow field developing around a NACA airfoil wind turbine.

These equations are solved numerically to determine the local characteristics of the flow. The models tested are implemented in the software "SolidWorks Flow Simulation" which uses a finite volume scheme.

The numerical results are compared with experiments conducted on an open wind tunnel to validate the numerical results. This will help improving the aerodynamic efficiency in the design of packaged installations of the NACA airfoil type wind turbine. A computer code named SUPIN has been developed to perform aerodynamic design and analysis of external-compression, supersonic inlets.

The baseline set of inlets include axisymmetric pitot, two-dimensional single-duct, axisymmetric outward-turning, and two-dimensional bifurcated-duct inlets. The aerodynamic methods are based on low-fidelity analytical and numerical procedures.

The geometric methods are based on planar geometry elements. SUPIN has three modes of operation: 1 generate the inlet geometry from a explicit set of geometry information, 2 size and design the inlet geometry and analyze the aerodynamic performance, and 3 compute the aerodynamic performance of a specified inlet geometry. The aerodynamic performance quantities includes inlet flow rates, total pressure recovery, and drag. The geometry output from SUPIN includes inlet dimensions, cross-sectional areas, coordinates of planar profiles, and surface grids suitable for input to grid generators for analysis by computational fluid dynamics CFD methods.

A comprehensive investigation has been carried on with full-scale models in the NACA foot wind tunnel, the general purpose of which is to furnish information in regard to the physical functioning of the composite propeller-nacelle unit under all conditions of take-off, taxiing, and normal flight.

This report deals exclusively with the cowling characteristics under condition of normal flight and includes the results of tests of numerous combinations of more than a dozen nose cowlings, about a dozen skirts, two propellers, two sizes of nacelle, as well as various types of spinners and other devices.

A method for determining the optimum inlet geometry of a liquid rocket engine swirl injector includes obtaining a throttleable level phase value, volume flow rate, chamber pressure, liquid propellant density, inlet injector pressure, desired target spray angle and desired target optimum delta pressure value between an inlet and a chamber for a plurality of engine stages.

The method calculates the tangential inlet area for each throttleable stage. The method also uses correlation between the tangential inlet areas and delta pressure values to calculate the spring displacement and variable inlet geometry of a liquid rocket engine swirl injector.

Attic Inlet Technology Update. Attic inlets are a popular addition for new construction and energy saving retrofits. Proper management of attic inlets is necessary to get maximum benefits from the system and reduce the likelihood of moisture-related problems in the structure. Solar energy levels were determined for the continen Tests were made in the NACA two-dimensional low-turbulence tunnel of three gun ports with a height of approximately 4 percent of the chord faired into an NACA 66, low-drag-airfoil section by bulging the section at the gun port.

Gun ports faired in this manner had practically no effect on the maximum lift and the critical compressibility speed of the section and showed only small increase in the drag in the range of lift coefficients for high-speed and cruising-flight conditions.

Patterns of peroxidative ethane emission from submerged rice seedlings indicate that damage from reactive oxygen species takes place during submergence and is not necessarily a post-anoxic phenomenon.

Using ethane as a marker for peroxidative damage to membranes by reactive oxygen species ROS we examined the injury of rice seedlings during submergence in the dark. It is often expressed that membrane injury from ROS is a post- submergence phenomenon occurring when oxygen is re-introduced after submergence -induced anoxia. We found that ethane production, from rice seedlings submerged for h, was stimulated to nl gFW -1 , indicating underwater membrane peroxidation. When examined a week later the seedlings were damaged or had died.

On de- submergence in air, ethane production rates rose sharply, but fell back to less than 0. We compared submergence -susceptible and submergence -tolerant cultivars, submergence starting in the morning more damage and in the afternoon less damage and investigated different submergence durations.

The seedlings showed extensive fatality whenever total ethane emission exceeded about 15 nl gFW Smaller amounts of ethane emission were linked to less extensive injury to leaves. Partial oxygen shortage O 2 levels submergence is not associated with extensive anoxia. Instead, injury is linked to membrane peroxidation in seedlings that are partially oxygen deficient while submerged. On return to air, further peroxidation is suppressed within about 2 h indicating effective control of ROS production not evident during submergence itself.

The tidal currents and hydrography at two adjacent inlets of the Indian River Lagoon estuary Florida were recently measured using a personal watercraft-based coastal profiling system.

Although the two inlets—Sebastian Inlet and Port Canaveral Inlet—are separated by only 60 km, their characteristics and dynamics are quite unique.

Underway measurements of tidal currents were obtained using a bottom tracking acoustic Doppler current profiler; vertical casts of hydrography were obtained with a conductivity-temperature-depth profiling instrument; and continuous underway measurements of surface water hydrography were made using a Portable SeaKeeper system.

Survey transects were performed to elucidate the along-channel variability of tidal flows, which appears to be significant in the presence of channel curvature. Ebb and flood tidal currents in Sebastian Inlet routinely exceeded 2. Preliminary analysis of a submerged wave energy harvesting device is presented. The device is composed of a thin, horizontally submerged plate that is restricted to heave oscillations under the influence of surface waves.

The submerged plate is oscillating, and it can be attached to a fixed rotor, or a piston, to harvest the wave energy. A fully submerged wave energy converter is preferred over a surface energy convertor due to its durability and less visual and physical distractions it presents.

In this study, the device is subject to nonlinear shallow-water waves. Wave loads on the submerged oscillating plate are obtained via the Level I Green-Naghdi equations. The unsteady motion of the plate is obtained by solving the nonlinear equations of motion. The results are obtained for a range of waves with varying heights and periods. The amplitude and period of plate oscillations are analyzed as functions of the wave parameters and plate width.

Particular attention is given to the selection of the site of desired wave field. Initial estimation on the amount of energy extraction from the device, located near shore at a given site, is provided. A perspective on underwater photosynthesis in submerged terrestrial wetland plants. Background and aims Wetland plants inhabit flood-prone areas and therefore can experience episodes of complete submergence.

Submergence impedes exchange of O2 and CO2 between leaves and the environment, and light availability is also reduced. The present review examines limitations to underwater net photosynthesis PN by terrestrial i.

Scope Floodwaters are variable in dissolved O2, CO2, light and temperature, and these parameters influence underwater PN and the growth and survival of submerged plants. Aquatic species possess morphological and anatomical leaf traits that reduce diffusion limitations to CO2 uptake and thus aid PN under water.

Many aquatic plants also have carbon-concentrating mechanisms to increase CO2 at Rubisco. Terrestrial wetland plants generally lack the numerous beneficial leaf traits possessed by aquatic plants, so submergence markedly reduces PN.

Some terrestrial species, however, produce new leaves with a thinner cuticle and higher specific leaf area, whereas others have leaves with hydrophobic surfaces so that gas films are retained when submerged ; both improve CO2 entry.

Conclusions Submergence inhibits PN by terrestrial wetland plants, but less so in species that produce new leaves under water or in those with leaf gas films. Leaves with a thinner cuticle, or those with gas films, have improved gas diffusion with floodwaters, so that underwater PN is enhanced. Underwater PN provides sugars and O2 to submerged plants. Floodwaters often contain dissolved CO2 above levels in equilibrium with air, enabling at least some PN by terrestrial species when submerged , although rates remain well below those in air.

The inhibitory effect of allelochemicals released by submerged macrophytes on phytoplankton is considered as one of the mechanisms that contribute to the stabilization of clear-water status in shallow lakes. This paper reviewed the research progress in the allelopathy of submerged macrophytes on algae from the aspects of the occurrence frequency and coverage of allelopathically active submerged macrophytes in lakes, and the kinds and allelopathical effects of the allelochemicals released from the macrophytes.

The previous researches indicated that allelopathically active submerged macrophyte species such as Myriophyllum, Ceratophyllum, and Elodea were efficient to control phytoplankton, especially when their biomass was high enough, and the dominant algae were sensitive species. The allelochemicals such as hydroxybenzene released by the submerged macrophytes could inhibit the growth of algae.

Different phytoplankton species exhibited different sensitivity against allelochemicals, e. Examples of Submerged inlet in a sentence Submerged inlet ports shall be located so as to avoid creating a disturbance of the settled floc. Submerged lands means those lands which are inundated by water on a seasonal or more frequent basis.

Submerged fill pipe means any fill pipe with the discharge opening entirely submerged when the liquid level is six inches above the bottom of the tank; or when applied to a tank which is loaded from the side, shall mean any fill pipe with the discharge opening entirely submerged when the liquid level is eighteen inches above the bottom of the tank. Drip irrigation means any non-spray low volume irrigation system utilizing emission devices with a flow rate measured in gallons per hour.

Low volume irrigation systems are specifically designed to apply small volumes of water slowly at or near the root zone of plants. Pump spray means a packaging system in which the product ingredients within the container are not under pressure and in which the product is expelled only while a pumping action is applied to a button, trigger or other actuator.

Tanks has the meaning set forth in Section 4. Tank means a stationary device, designed to contain an accumulation of hazardous waste which is constructed primarily of non-earthen materials e. Pump means a device used to raise pressure, drive, or increase flow of liquid streams in closed or open conduits.

Bulk gasoline plant means a gasoline storage and distribution facility with an average daily throughput equal to or less than 76, liters 20, gallons which receives gasoline from bulk terminals by trailer transport, stores it in tanks, and subsequently dispenses it via account trucks to local farms, businesses, and service stations.

Power Plant means a facility for the generation of electricity that is permitted as a single plant by a jurisdiction inside or outside the state.

Propeller means for a device for propelling an aircraft that has blades on a powerplant driven shaft and that, when rotated, produces by its action on the air, a thrust approximately perpendicular to its plane of rotation and it includes control components normally supplied by its manufacturer, but does not include main and auxiliary rotors or rotating airfoils of powerplants;.