Abstract: A plurality of electrically conductive wires is connected between two terminals and cross over each other at crossover points. Wire segments connect adjacent crossover points. All such adjacent connected crossover points have different potentials when a voltage is connected between the terminals. This forms a screen which protects an engine from damage caused by foreign objects carried into the engine intake. When a power source is connected to the terminals, the screen is heated to prevent the accretion of ice.

Abstract: A noise reduction nacelle for a jet engine having an inlet duct, a center body and at least one exit duct and which includes a composite sandwich panel positioned in the inlet duct, the center body and the at least one exit duct. The panel includes an inner face sheet, a honey comb core and an outer face sheet wherein the inner face sheet and the outer face sheet are connected to the inner and outer surfaces, of the core. A plurality of perforations are provided in the inner face sheet of a predetermined density and wherein each of the perforations is of a predetermined diameter. A method of forming the composite sandwich panel is also provided.

Abstract: A boundary layer control device is installed in the acoustically treated inlet duct of a turbofan engine. The device sucks off the turbulent boundary layer of air flowing over the inner or "air wetted" surface of the inlet during aircraft take-off, cruise and approach. The lip of the inlet can thus be made thinner to reduce drag during cruise without degradation of fan performance during take-off. The acoustic liner of the inlet comprises a microporous honeycomb sandwich structure through which air may be sucked at various locations through headers and conduits connected to an onboard pump.

Abstract: Air is blown into an air boundary layer to re-energize the boundary layer prior to its ingestion by an engine inlet (12) of a supersonic aircraft (10).

Abstract: A nacelle structure (14) for a gas turbine engine (4) extends upstream from the engine air inlet (10) and includes an external surface (18) and an internal surface (16). The external surface (18) is concentric about a linear centerline (22) which is disposed parallel to the free airflow stream (6) encountered by the nacelle (14) in flight. The internal surface (16) is concentric about a curved centerline (30), the curved centerline (30) being parallel to the free airflow stream (6) at the nacelle inlet (12) and parallel to the engine centerline (26) at the engine air inlet (10) for smoothly directing the internal airflow stream (32) into the engine air inlet (10).

Abstract: A pair of vortex generators are attached to the exterior surface of an aircraft and located forwardly of a flush inlet so as to effectively remove or reduce the thickness of a slower-moving boundary layer airflow ajdacent to the exterior aircraft surface and increase the mass airflow into the flush inlet. The pair of vortex generators induce higher mean total pressure airflow into the area between the vortex generators and downstream thereof and in front of to the flush inlet, thereby resulting in an increase in mass airflow into the flush inlet for a given inlet area.

Abstract: The invention is an improved inlet particle separator for removing extraneous matter from a stream of air directed into the engine's core section. The improved separator utilizes two stages of separation. The first stage is an axial flow separator for initially separating engine inlet air into a first flow of relatively contaminated air and a second flow of relatively clean air. This first stage of separation is accomplished by sharply turning the air flow radially inwardly so that the relatively dense extraneous matter continues in its original direction into a scavenge system. A second stage of separation is accomplished in the scavenge system and comprises a centrifugal separator that separates the first flow of air into third and fourth flows of relatively contaminated air for the purpose of protecting a blower that powers the flow through the scavenge system and which is in flow communication with only the relatively less contaminated fourth flow of air.

Abstract: An aircraft comprising a discoidal fuselage having a planar upper surface and containing at least one vertical duct extending longitudinally therethrough, an impeller located within the duct for producing an upward flow of gas, and a gas flow director movably mounted with respect to said duct. The vertical duct is central to the fuselage. The impeller is a vertical turbojet engine. The gas director comprises a central conical member, an upper annular flow control member, and a plurality of radially spaced apart vent controls. The vent controls are hydraulic cylinders. A hatch is mounted about the bottom opening of said duct. The hatch is movable such that one position seals the duct from the entry of liquids. An air passageway extends into and communicates with the duct.

Abstract: A ram constriction vane diffuser adapted as an air intake of an air plenum-engine pod wherein vertical multiple vanes are fitted on the vertically inclined air intake opening and include fixed vanes positioned adjacent the centerline portion of the air plenums which define an envelope for the airflow including nozzles locate on both sides of a jet engine, a plurality of deflectable vanes positioned in an equally spaced relationship in the air intake openings on both sides of fixed vanes, and wherein each deflectable vane has a leading edge and a drivable trailing section pivotally mounted on the rigid leading section of the deflectable vane and with the drivable trailing sections of each vane and with an actuator for adjusting the angle of the deflectable vanes relative to the freestream air flow for enabling the drivable trailing section of each vane to be turned away from a parallel position to the centerline of an engine suction diffuser, which is the original position thereof for speed flight, to reduce t

Abstract: Aerodynamic flow conditions at the air intake of gas turbine engines, espally aircraft engines, comprising boundary layer deflectors are improved by movably arranging the boundary layer deflectors so that they may be retracted flush into the aircraft fuselage during take-off and low speed flight, and may be extended to an operating position during high speed flight. A similar retractable boundary layer deflector may be provided for an air intake for an auxiliary engine, which operates intermittently to drive auxiliary devices of an aircraft. When the auxiliary engine operates the air intake is open and the deflector is extended thereby improving the intake air flow conditions. When the auxiliary engine is shut down, the air intake is covered by a control flap and the deflector is retracted flush into the fuselage.

Abstract: A diffuser for an air intake of an aircraft has an inlet and an outlet, both with variable cross-sectional flow areas. At least one wall section of a diffuser defining flow channel is movable by one or separate lever linkage systems for varying the inlet and outlet cross-sectional flow areas. A control circuit, preferably a closed loop control circuit responsive to a control program, makes sure that optimal flow cross-sectional areas are maintained at the inlet and outlet of the diffuser to optimize the operation of the diffuser.

Abstract: A two-dimensional inlet for a high speed ram jet missile includes in combination an educated slot and a single ramp for varying the geometry of the inlet.

Abstract: A valve for selectively changing the direction of flow of working fluid through a variable cycle engine which comprises a first and second compressor 14,16 spaced along a flow duct 26. The duct 26 having air intakes 42 leading to the second compressor 16 and outlets leading to nozzles 44. The valve comprising a sleeve 30 axially movable along the duct. The sleeve 30 having openings 31 in it in which are located doors 32. Links 36 are connected to each of the doors 32 so that as the sleeve 30 is moved axially the doors 32 are pulled open to open the air inlets 42 and the outlets and simultaneously obturate the flow duct 26. In a second position of the sleeve 30 the doors 32 and the sleeve 30 close off the air inlets and outlets and open the duct to allow the first compressor to supercharge the second compressor.

Abstract: An aircraft having a fuselage provided with an internal duct extending longitudinally therethrough to provide an internal wing for the craft, the internal duct having the forward end open for receiving an air stream therethrough and the aft end thereof open for discharge of the air stream therefrom, the internal contour of the duct being alterable in accordance with required operational conditions for the flight of the craft, and a plurality of control flaps and/or vanes provided at the aft end of the duct for proving operational controls for the craft in the manner of a more conventional external wing craft.

Abstract: An air vehicle has a passenger section, a tail section including variable camber air foil wings and horizontal and vertical control surfaces, ducted fan propellers and landing gear wheels driven by an engine. The landing gear wheels accelerate the vehicle until the fans produce sufficient thrust, at which time the ducted fans propel the vehicle into flight. In one embodiment, while the tail section is detached, the passenger section can be used as a land vehicle. Alternatively, the passenger section and tail section are formed as a single unit in which case the vehicle is used solely as an airplane.

Abstract: An inlet particle separator for a gas turbine engine is provided with unique vanes distributed around an entrance to a particle collection chamber. The vanes are uniquely constructed to direct extraneous particles that enter the engine into the collection chamber and prevent the particles from rebounding back into the engine's air flow stream. The vanes are provided with several features to accomplish this function, including upstream faces that are sharply angled towards air flow stream direction to cause particles to bounce towards the collection chamber. In addition, throat regions between the vanes cause a localized air flow acceleration and a focusing of the particles that aid in directing the particles in a proper direction.

Abstract: A variable air inlet includes an air intake duct with upper ramps, an air inlet bottom spaced below the ramp and a movable air scoop lip pivotally secured to the end of the air inlet bottom closer to the opening into the air intake duct. The air scoop lip is pivotally displaceable through two angular operating ranges, a wider one in the subsonic/transonic range and a narrower one in the upper supersonic range. Various control members including computers are used to control the position of the lower air scoop lip. The movement in the subsonic/transonic range is effected in response to the flight machnumber and the aircarft angle of attack based on a given control law. The control in the supersonic range is established in response to a variable demand pressure ratio between the static pressure above the upper ramps and the free stream total pressure, with the variable demand pressure ratio being a function of the actual air scoop lip position.

Abstract: An airflow particle separator for a gas turbine engine provided for removing foreign particles and moisture from the air flow. The separator comprises an inner wall and an outer wall defining a passageway therebetween, with the inner wall including an inlet portion diverging in a downstream direction away from the separator axis while converging towards the outer wall to form a throat to accelerate incoming air to a higher velocity in a substantially axial direction. The inner wall then converges towards the separator axis and diverges from said outer wall with a splitter ring disposed between the inner and outer walls for splitting said passageway into inner and outer passages, with the outer passage adapted to bypass moisture and foreign particles. The leading edge of the splitter ring is located downstream and inward of said throat.

Abstract: A device, particularly for use with guided missiles, of a type having an intake pipe which is not fully rotationally symmetrical and is particularly semi-rotationally symmetrical, having particularly a semi-rotationally symmetrical air intake cross-section. The device prevents hum in the supersonic intakes of air-breathing reaction engines, particularly, ram jet engines, of a type which are operated with solid fuels and without regulation of the amount of air intake, the amount of fuel or the amount of thrust current flow for driving guided missiles. The construction includes a missile body having an intake pipe mounted thereon with a front opening disposed in an opening plane defining an inlet. A displacement body is mounted within the pipe in spaced relationship thereto and has a front pointed end which extends outwardly beyond the intake plane and which projects into the incoming air flow.

Abstract: An air intake for a helicopter mounted gas turbine engine comprises two intake portions which comprises vortex separator panels. One panel is generally forward facing while the other is generally sideways facing. A panel is pivotally mounted between the separator panels so as to pivot between a first position in which it obturates the generally sideways facing panel and a second position in which it obturates neither of the separator panels. The arrangement is such that when the helicopter is in fast forward flight, the pressure of the ram air flow through the generally forward facing inlet panel causes the pivoted panel to pivot to the position in which it obturates the generally sideways facing inlet panel.

Abstract: Hot compressed air is bled from the compressor of an engine and a portion of it is directed through a flow through type indirect heat exchanger of ring form located within an annular chamber in the engine cowl which is partially formed by lip surfaces of the inlet. Such air gives up heat to low pressure air within such chamber which carries the heat to the inlet surfaces. The compressed air is then removed from the heat exchanger and is admixed with additional hot compressed air. A part of the mixture is delivered to a wing TAI subsystem and a second portion is used for cabin conditioning and pressurization.

Abstract: A vented cowl variable geometry inlet for aircraft which provides means to permit starting an overly contracted inlet by dumping sufficient air to obtain the start, as well as to dump air when no thrust is required, but without loss of combustion, and to effect operation of an aircraft of piloted or missile character in a regime where reduction in fuel flow and thrust is advantageous.

Abstract: A propulsion system for vertical take off and landing aircraft includes a forward compressor fan (40) and an aft compressor fan (42) downstream of the forward fan and in series flow communication with the forward fan. The forward and aft fans are positioned in a central duct (26). A gas turbine engine (44) is in series flow with the forward and aft fans for driving the fans. The forward fan, aft fan and turbine engine are interconnected by a common shaft (50). A forward diverter structure (100) is positioned downstream of the forward fan and is movable between a first position for diverting exhaust from the forward fan downwardly relative to the longitudinal axis of the aircraft while simultaneously permitting the introduction of air behind the forward diverter structure but ahead of the aft fan and a second position wherein the exhaust from the forward fan is channeled through the aft fan and turbine.

Abstract: A compression-sealed door assembly for use in controlling air flow pressure levels within a supersonic jet nacelle inlet, wherein substantially U-shaped strips of resiliently compressible material is compressed between a door and the nacelle inlet to seal air flow passageways through the inlet when the door assembly is pivoted to its fully closed position.

Abstract: A flush inlet and inlet air passage for supersonic aircraft including provisions for efficiently decelerating a supersonic airstream entering the inlet and converting such airstream to subsonic airflow within the inlet air passage prior to introduction into the aircraft's jet propulsion engine.

Abstract: A high bypass turbofan engine is coupled to a wing strut by a spaceframe thrust linkage. The linkage transfers the axially oriented thrust-induced loads to the strut along the axial horizontal centerplane of the engine. The inlet to the engine is supported by a combined triangular and tetrahedral linkage system which suspends the inlet and transfers axial, vertical, and side loads directly from the inlet to the strut. The inlet is coupled to the engine fan case via a plurality of fluid-filled piston and cylinder assemblies that transmit only axially oriented loads from the inlet to the fan case. Additionally, the linear actuators for the annular thrust reverser are coupled to the inlet so that the axial thrust reversing loads are first transferred to the inlet, from which the axial loads are effectively transferred to the fan case along the engine centerline and hence to the strut via the spaceframe linkage.

Abstract: An intake system for removing particles from air entering an engine, in which the intake air in an intake duct is divided into a primary airstream which flows upwardly at a sharp angle from the intake stream and into the engine inlet, and a secondary airstream which flows directly rearwardly with the particles to be removed, into a plenum where the particles are collected. A third airstream is formed which flows forwardly from the plenum beneath and at the sides of the intake duct, then upwardly around the sides of the intake duct and into the engine inlet.

Abstract: A deployable inlet for use with a center boost engine on a jet propelled aircraft having the capability of aerodynamically fairing the air inlet located in the leading edge of the vertical stabilizer at such times as the center boost engine is shut down and non-operative, thus minimizing drag. More particularly, an inlet construction for use with aircraft of the type commonly employing multiple main power plants and an auxiliary center boost engine of the type which is commonly used only: (i) during take-off; (ii) during air refueling operations; and/or (iii), under certain emergency operating conditions; and, wherein the air inlet for such center boost engine is located at the root leading edge of the aircraft's vertical stabilizer.

Abstract: One or more channels whose edges generate streamwise vortices from heights coincidental with a local flow-control surface into the channels are used to maintain attached flow of a fluid medium flowing therepast, even in areas of severe regional adverse pressure gradients. The channels are generally triangular in shape with the apex forwardmost in the flow. The channels work very effectively when nested in series and are most effective when the channels extend to the trailing edge of a flow-control surface.

Abstract: A triangular airfoil plate is forward of and below the air intake duct of an aircraft-mounted gas-turbine engine, and a small airfoil member is below the airfoil plate. An inductive action of leading-edge separation vortices generated from the leading edges of the airfoil plate and the small airfoil member is utilized to curve the direction of air flowing into the air intake duct and thereby to prevent turbulence in the intake airflow and resulting defective operation or failure of the engine during flight of the aircraft at large angles of attack.

Abstract: There is described a fluid flow concentrating device suitable, for example, for concentrating the flow of tidal waters or of wind, which comprises a hollow body closed at one end and open at the other. The body has a fixed circumferential wall composed of a plurality of fixed spaced vanes and a nozzle located at the open end of the wall. Fluid moving from outside the device through the vanes to the inside of the body creates a vortex within the body and a fluid flow axially of the body through the nozzle. In certain preferred embodiments a turbine is located for rotation in a direction opposite to the direction of rotation of the vortex about a vertical axis, centrally within the nozzle downstream of the fluid flow. The turbine can be used to drive a generator or a motor to, for example, propel a marine craft, or, the augmentor can be used on a aircraft to assist the lift of a wing, or, in another application, can be used with a jet turbine engine to improve both the intake to and the thrust from the engine.

Abstract: An air inlet and scoop for aircraft auxiliary power units to provide satisfactory performance thereof under all operational conditions, including full capability for in-flight starting at high altitudes, whereby operational difficulties caused by thick boundary layers and adverse pressure gradients between the inlet and the tail cone in the vicinity of the inlet are overcome. The inlet opening is contoured along its outer edges to conform to the aircraft fuselage and has a ramp trailing inwardly into the opening, starting at the fuselage and forming the bottom surface of the inlet. The inlet has generally parallel side walls trailing inwardly, the inlet side walls extending inwardly from the fuselage edges along the inlet opening. A scoop is hinged adjacent the fuselage at one end of the inlet opening, the aircraft having means therein to operate the scoop so as to open and close the inlet opening.

Abstract: A two-dimensional, unidirectional oblique air impact diffuser is used as an air inlet for a gas turbine jet engine for aircraft. The air inlet includes an upper rigid air inlet ramp and an air inlet bottom spaced below the ramp. An air scoop lip is pivotally attached to the air inlet bottom so that it can be pivoted from a standard setting point downwardly away from the air inlet ramp and also from the standard setting point toward the ramp. The pivotal displacement of the air scoop lip is a function of the aircraft angle of attack and the flight Mach number. The angular displacement of the air scoop lip from the standard setting point increases downwardly as the aircraft angle of attack increases and decreases as the Mach number increases.

Abstract: The air scoop opening at the leading edge of a flexible, ram-air inflated airfoil canopy, is framed between curved lip sections extending tangentially from the upper and lower surface members of the canopy to prevent airflow separation adjacent the leading edge and the drag producing effect thereof. A baffling curtain extends across the air scoop opening.

Abstract: An elongated air scoop integrated with the engine housing for a jet prop powered aircraft is provided with a thin tubular metal manifold loop fitted to the open forward end of the air scoop and the hot exhaust gas bled from the engine exhaust system is continuously fed through the tubular loop which forms a hot defrost lip for the air scoop.

Abstract: An actuating linkage is provided for use in an aircraft engine having a double door-type particle separator, anti-icing system installed within its air intake ducts. The actuating linkage interconnects the deflecting vane and the bypass door through a coupler link. The deflecting vane is pivotally connected to a linear link which is connected to an actuator link about a pivot point. Movement of the actuator link varies the relative positions of the deflecting vane and the bypass door between ram mode and anti-icing mode positions. The actuating linkage partially balances the aerodynamic forces on the deflecting vane and bypass door so that the input required to operate the anti-icing system may be manually applied by the pilot. The actuating linkage is fail-safe, in that the linkage is operative such that should the actuator link extending to the pilot station fail, the aerodynamic forces on the bypass door cause the deflecting vane and bypass door to be actuated to the anti-icing mode position.

Abstract: An air intake structure for a gas turbine engine comprising a duct having an air inlet at its upstream end for the engine and a generally mushroom-shaped center body. The duct and the center body have circular cross-sections throughout their lengths and are coaxial. The center body has a first stem portion extending into the duct and a second mushroom-shaped portion upstream of the air inlet of the duct, the mushroom-shaped portion having a maximum diameter greater than the diameter of the air inlet. An apertured wall circumferentially extends around the maximum diameter of the second portion of the center body, the apertures of the wall being so dimensioned as to cause any small liquid droplets flowing over the upstream face thereof to coalesce into larger liquid droplets. A step immediately downstream of the apertured wall causes the formed larger droplets to be launched from the center body in a trajectory which avoids the air inlet of the duct.

Abstract: In an air inlet for a gas turbine jet propulsion plant in which the inlet annel is curved, separation flow is generated near the inner wall surfaces of the inlet at certain angles of attack. A flow guide fence is employed which reaches into the air inlet channel a small extent radially so that separation flow is caused to follow the channel and substantially dissolves itself by the time it reaches the compressor entrance so that flow to the compressor is substantially homogeneous.

Abstract: A smooth surfaced, submerged air inlet for use generally forwardly of an engine in an aircraft (missile or other air vehicle). The inlet has an opening having wall surfaces adapted to be flush with or inwardly of an aircraft body surface. The wall surfaces of the opening have a leading and outer end in a plane and the surfaces extend inwardly to form an uncovered shallow channel-shaped portion to the inlet, the channel portion deepening inwardly in the trailing direction and continuing into a partial ellipse portion of the opening. The ellipse portion deepens inwardly as it extends in a trailing direction and has substantially parallel wall surfaces extending outwardly of the ellipse in the direction toward the level of the plane. There are extensions of said substantially parallel wall surfaces diverging outwardly to said plane.

Abstract: An inlet duct of generally rectangular configuration for supersonic aircraft in which a normal shock is produced in close proximity to the forward lip of the lower duct wall, and in which variable area sideplate openings are provided just upstream of the normal shock to achieve boundary layer control for the normal shock-boundary layer interaction during on-design operation and increasing flow area for spillage as the normal shock is moved forward during off-design operation.

Abstract: Ducted fan propulsion unit for aircraft has a main duct 3 containing a reversible pitch fan 1 rearward of which is provided a flow splitter 13 dividing the main duct into radially outer and inner branch ducts 3A, 3B. A radial passage 15 in the splitter connects the branch ducts and divides the splitter into front and rear parts 13A, 13B. The part of the inner branch duct forward of the radial passage contains an array of stator vanes 12B and has outer and inner wall surfaces 3B1,3B2 both of progressively reducing diameter to urge the flow through that branch duct toward the inlet of a compressor 8 of yet smaller diameter. Stator vanes 12A in the outer branch duct are arranged forward of the radial passage. The arrangement favors a relatively low axial length of the powerplant.

Abstract: A permanently fixed fairing is provided extending across the air duct coinciding with the opening in the air duct to the air intake of a gas turbine engine. The fairing is in the form of an airfoil vane with a high pressure concave surface and a low pressure convex surface extending between the leading edge and trailing edge of the fairing and shaped such that the leading edge portion of the fairing is in the direction of the longitudinal axis of the air duct while the trailing edge portion of the fairing is in the direction of the air intake of the engine such that the fairing will divert air into the intake. A deflecting flap is hinged to the wall of the duct in a first position for a non-icing mode whereby the flap is clear of the air duct and in a second position whereby the trailing edge of the flap is adjacent the leading edge of the fairing during an icing mode.

Abstract: A low-drag truck consisting of a tractor-trailer rig (10) characterized by a rounded forebody and a protective fairing (16) for the gap conventionally found to exist between the tractor and the trailer, particularly suited for establishing an attached flow of ambient air along the surfaces thereof, and a forward facing, ram air inlet and duct (24 and 22) and a plurality of submerged inlets (18) and outflow ports (20) communicating with the trailer (14) for continuously flushing heated gasses from the trailer as the rig is propelled at highway speeds.

Abstract: A hinged inlet cover for an overcontracted mixed compression supersonic inlet which does not eject from the aircraft, which reduces carriage drag of the aircraft and which, at the same time, produces an increase in inlet performance by utilizing a dynamic starting process as the cover opens. The cover is actuable to open the inlet by aerodynamic forces.

Abstract: Air intake openings in an aircraft engine cowling are plugged by closures of resilient plastic material while the aircraft is parked, to exclude birds from nesting in the engine compartment. A rope is connected to the closures and draped around the propeller so that, in the event the aircraft operator fails to manually remove the closures, before the engine is started, the turning of the propeller will pull on the rope and thereby pull the closures from the openings, whereupon the closures and rope are deposited on the ground.

Abstract: A ramjet powered vehicle having a bleed slot in the subsonic diffuser, for the ramjet combustor, which supplies air to a turbine for supplying power to vehicle accessories. A vortex tube is provided between the bleed slot and the turbine to provide a cool air supply. Radar absorbing material is positioned adjacent ramjet inlet with a cooling duct provided to supply cooling air from the vortex tube to the ramjet inlet cowl lip to provide cooling for the radar absorbing material.

Abstract: The nose portion of a missile having a ram air turbine for driving an electric generator for supplying electric power to the electric circuits of the missile, especially of its fuse, is designed in a special manner in order to provide, at high missile speeds, a throttling of the air flow, whereby the speed of rotation of the turbine may be kept within reasonable limits. Thus, the air inlet is divided in a plurality of inlet ducts arranged as a wreath around the foward end of the missile. Further, the outlet openings are forwardly directed and co-operate with the shock waves from the acute forward end of the missile and from an annular edge surrounding the wreath of inlets but lying radially inside the outlet openings.

Abstract: A system of separating or removing foreign particles from the gaseous fluid flowing in the primary flow path of a gas turbine engine is provided wherein the particles are removed from the stream near the engine inlet and flow through a conduit to ejector means operative to effect a flow of a second stream of fluid in the conduit. Mixing means are provided for mixing the second stream of fluid with the gaseous fluid flowing in the primary flow path.

Abstract: For a winged high speed missile that includes a two-dimensional inlet supplying air to the missile power plant, the compression ramp of the inlet is oriented with respect to the outwash angle produced by the missile body and the underneath surface of the wing such that the compression ramp of the inlet is subjected to an effective angle of attack. By proper inlet orientation the captured flow is turned inwardly toward the missile center line further compressing the incoming air.

Abstract: Precompression fins extending perpendicular from the wings of a high speed missile are judiciously located relative to an axisymmetric inlet of an airbreathing power plant such that the outwash angle induced by the body and wing of the missile enhances the performance of the inlet.