Anti drag penetrator

Abstract

An anti-drag penetrator is a device that captures ram air or fluid flow generated by the forward motion of a vehicle, projectile or object, or by the impingement of a moving fluid stream upon a stationary object, routes said flow through a flow-reversing duct, and emits it as a forward-directed counterflow jet that modifies the stagnation region ahead of the vehicle or object before the oncoming fluid medium contacts any surface thereof. The emitted jet pre-emptively displaces and deflects the oncoming atmosphere, reducing pressure drag and aerodynamic or hydrodynamic resistance. Captured and compressed ram air may additionally be circulated through cooling channels within the vehicle surface to provide active thermal management. The device requires no external energy source, compressor or pressurised storage. Applications include road vehicles, motorcycles, high-speed rail, metro systems, racing vehicles, aircraft, watercraft, spacecraft during atmospheric and potential future space flight phases, stationary structures in moving fluid streams, and all hypersonic vehicles.

Description

[0001] ANTI-DRAG PENETRATOR

[0002] Field of the Invention

[0003] This invention relates to an Anti-Drag Penetrator, a device for reducing aerodynamic and hydrodynamic drag and improving the energy efficiency of any vehicle, projectile, object or stationary structure operating within or subject to a moving fluid medium. The invention has application across all forms of transport including road vehicles, motorcycles, bicycles, trains, high¬ speed rail, metro and underground rail systems, racing vehicles including Formula 1, Formula E and Le Mans vehicles, aircraft, drone, watercraft, submarines, spacecraft during atmospheric flight phases, and any other moving object subject to fluid resistance. The invention additionally provides active thermal management through ram-air-powered cooling channels applicable to spacecraft re-entry and all high-speed hypersonic vehicles. The invention further applies to stationary objects within moving fluid streams including wind turbine blades, bridge pylons, offshore structures and buildings.

[0004]

[0005] Background

[0006] The efficiency of any moving vehicle or object operating within a fluid medium is substantially determined by the aerodynamic or hydrodynamic forces acting upon it. Drag comprises principally pressure drag arising from the high-pressure stagnation region at the leading surface and low- pressure wake at the trailing surface, and skin friction drag arising from the viscous boundary layer in contact with the vehicle surface.

[0007] Conventional approaches to drag reduction focus on streamlining the external shape of the vehicle to minimise the magnitude of these forces after the fluid medium has already made contact with the vehicle surface. Such approaches are inherently reactive — they manage the consequences of fluid-vehicle contact rather than preventing or reducing that contact.

[0008] Active flow control systems exist in aviation where engine bleed air energises the boundary layer or applies suction through porous surface panels. However these systems impose a significant parasitic energy penalty by diverting compressed air from the main engines. No self-powered, compressor-free passive-active system exists that pre-emptively acts upon the fluid medium ahead of the vehicle before contact occurs.

[0009] For spacecraft during atmospheric re-entry, aerodynamic heating of the vehicle surface by the superheated plasma layer is managed entirely by passive means — ablative heat shields that bum away or ceramic files. Both are heavy, expensive and in the case of ablatives single-use. No active thermal management system powered solely by ram air captured during descent exists. The present invention addresses this through two complementary mechanisms: a forward counterflow jet displacin the plasma layer to reduce incident heat flux, and a ram-air-powered cooling channel network absorbing and venting conducted heat from the vehicle skin.in rail applications, aerodynamic drag constitutes a dominant proportion of total running resistance at speed, in metro and underground systems operating in tightly confined tube bores, the piston effect — the sustained pressure differential between the leading and trailing faces of the train throughout its entire tunnel journey — represents the primary aerodynamic drag source and additionally drives tunnel heat build-up and pressure pulses at stations. No existing passive device addresses the piston effect directly or coordinates with tunnel ventilation infrastructure to recover the energy it represents.

[0010] For two-wheeled vehicles including motorcycles and bicycles, aerodynamic drag constitutes the dominant resistance force at speed, with the rider's body accounting for the majority of total frontai area. No existing passive self-powered system a dresses stagnation region drag on two¬ wheeled vehicles or provides ram-air-powered lateral stabilisation against crosswind.

[0011] The present invention addresses all of these limitations through a single unified device and principle: the Anti-Drag Penetrator.

[0012] Summary of the Invention

[0013] The invention provides an Anti-Drag Penetrator device comprising one or more inlets configured to capture ram air or fluid flow generated by the forward motion of a vehicle, projectile or object through a fluid medium, or by the impingement of a moving fluid stream upon a stationary object; a flow-reversing duct routing said captured flow and reversing its direction by at least 90 degrees; and one or more outlets emitting the captured flow as a forward-directed counterflow jet directed into the oncoming fluid stream.

[0014] The emited counterflow jet penetrates, deflects and displaces the oncoming fluid medium ahead of the vehicle or object, modifyin the stagnation region and forming a displacement zone through which the vehicle continuously travels. This action is pre-emptive — it acts upon the fluid medium before contact with any vehicle surface which distinguishes the Anti-Drag Penetrator from ail conventional aerodynamic measures. An anti drag penetrator is a device for reducing aerodynamic and hydrodynamic drag and improving the energy efficiency and / or speed of any vehicle, projectile, object.

[0015] in a further embodiment, ram air captured by the inlet is compressed by a ram-air-po ered turbine and compressor system and circulated as a coolant flowthrough a network of cooling channels within or immediately beneath the outer surface of the vehicle. This active thermal management function absorbs and removes heat conducted through the vehicle skin during highspeed flight, supplementing the plasma displacement function of the forward counterflow jet to provide a complete integrated thermal protection system powered entirely by ram air.

[0016] Because the device is powered entirely by ram air or fluid flow it requires no external energy source, compressor, pressurised storage tank or engine bleed air at operating speed. A supplementary power source may be employed before the vehicle reaches operating speed, with automatic transition to fully self-powered operation at speed.Detailed Description

[0017] 1. General Principle and Operating Mechanism

[0018] The Anti-Drag Penetrator operates on the principle that aerodynamic and hydrodynamic drag can be reduced most effectively by pre-emptively acting upon the fluid medium ahead of the vehicle before contact occurs. One or more inlets are positioned on the leading surface at or near the stagnation point where ram pressure is greatest. During forward motion the vehicle’s kinetic energy drives fluid into the inlet at a pressure above ambient. This captured fluid is routed through a duct that reverses the flow direction by at least 90 degrees — • the flow-reversing duct — such that fluid captured at the leading surface is redirected and emited forwardiy from that same surface as a counterflow jet directed into the oncoming fluid stream. Additional ram air and counterflow jet management can incorporate diffusers, plenum chambers and manifolds. In the ground reference frame the absolute velocity of the emitted jet is the sum of the jet emission velocity relative to the vehicle and the vehicle's forward velocity. Where the duct converges to accelerate the flow the absolute jet velocity exceeds the vehicle's own speed, making the device progressively more effective at higher velocities.

[0019] 2. Inlet Configurations

[0020] The inlet may be of any geometry suited to the operating speed regime of the vehicle. At subsonic speeds, NACA submerged duct inlets offer minimal parasitic drag while providing effective ram pressure recovery. Pitot-style forward-facing inlets provide maximum stagnation pressure capture and are suited to applications where inlet drag is less critical than pressure recovery. At transonic and supersonic speeds, oblique shock inlets, isentropic spike inlets, variable geometry intake ramps and bifurcated supersonic diffusers decelerate the captured ram air through a series of controlled oblique shocks before entry into the flow-reversing duct, maximising pressure recovery across the full transonic and supersonic operating envelope. The inlet geometry may be of fixed or variable cross-sectional area, adjustable in real time in response to changes in speed, angle of attack, yaw, sideslip and atmospheric conditions.

[0021] 3. Duct Geometry and Outlet Configuration

[0022] The flow-reversing duct may be U-shaped, S-shaped or of any geometry that reverses the captured flow direction by at least 90 degrees. The duct may converge continuously from inlet to outlet, accelerating the captured flow by the Venturi principle. The degree of convergence may be fixed or variable and adjustable in real time. The outlet aperture may be shaped to correspond to and project a counterflow jet profile matching or exceeding the cross-sectional profile of the vehicle, forming an aerodynamic pre-tunnel or enlarged displacement void ahead of the vehicle with a defined clearance margin on all sides, reducing edge turbulence at the vehicle's leading surfaces. The device may comprise a distributed network of ducts and outlets across the vehicle surface, each independently controllable or alternatively

[0023] 4. Jet Characteristics.

[0024] The jet may be emitted as a continuous flow or in rapid pulses or oscillating bursts, with pulse frequency actively tuned to cancel specific frequencies of oncoming pressure waves. The jet maybe heated by a heating element powered by a ram-air turbine, reducing atmospheric density ahead of the vehicle. The device additionally comprises rearward-facing outlets at the trailing surface emitting a pressurising jet into the low-pressure wake, reducing base drag, powered by the same ram-air system. The device may also emit jets in any form including cyclonic, angled, intersecting and annular and from any position on the vehicle or object.

[0025] 5. Active Thermal Management — - Ram-Air Cooling

[0026] In a significant further embodiment applicable to spacecraft re-entry and ail high-speed hypersonic vehicles, ram air captured by the inlet is compressed by a ram-air-powered turbine and compressor system and circulated as a coolant flow through a network of cooling channels within or immediately beneath the outer surface of the vehicle. This is directly analogous to the internal cooling channels used in jet engine turbine blades, applied here to the spacecraft or vehicle hull using captured ram air as the sole coolant medium.

[0027] During atmospheric re-entry the device operates simultaneously as a plasma displacement system and an active skin cooling system. The forward counterflow jet reduces the heat flux incident upon the spacecraft surface by displacing and deflecting the superheated plasma layer ahead of the spacecraft. The ram-air cooling channel network manages the residual heat conducted through the spacecraft skin. Together these two functions constitute an integrated active thermal protection system powered entirely by ram air during atmospheric descent, reducing or eliminating the need for passive ablative or ceramic heat shield materials.

[0028] The active cooling function applies to all high-speed vehicles, projectiles and objects subject to aerodynamic heating, including hypersonic aircraft, ballistic missiles, re-entry vehicles and highspeed projectiles. Jet emission parameters and coolant flow rates are automatically adjusted in response to real-time measurements of surface temperature, atmospheric density and flight velocity.

[0029] 6. Power and Control Systems

[0030] The device is inherently self-powered through ram air utilisation at operating speed and requires no external energy source. A supplementary power source may be employed to operate the device before the vehicle reaches the speed threshold at which ram air pressure is sufficient for self- sustaining operation. A transition mechanism automatically detects when ram air pressure reaches the self-sustaining threshold and progressively transfers operational power from the supplementary source to ram air alone. The device may be integrated with the vehicle's onboard computer or management system to enable automated real-time optimisation of jet and boundary layer control parameters. Sensors, pressure taps and angle-of-attack, yaw, sideslip, atmospheric pressure, temperature, humidity and icing risk detectors may be employed to continuously co¬ optimise ram air capture and counterflow jet emission as a single integrated function.

[0031] 7. Application to Road Vehicles

[0032] When applied to a road vehicle the device is positioned at one or more of the front face, grilie, bonnet, roofline, sides, underside, rear and wheel arch areas. For large blunt-ended vehiclesincluding coaches, buses and lorries, the combination of the forward counterflow jet reducing frontal pressure drag with the rearward outlets reducing base drag simultaneously addresses both primary drag sources from a single integrated ram-air system. For electric vehicles, drag reduction extends operational range without additional primary energy consumption. For a standard 13.6 metre curtainsider trailer at 56 miles per hour a conservative drag reduction of 10 to 15 percent represents a fuel saving of the order of 5 to 7 percent at motorway cruise with commensurate reductions in carbon dioxide emissions.

[0033] 8. Application to Motorcycles and Bicycles

[0034] When applied to a motorcycle, the ADP, Anti Drag Penetrator, inlet, is positioned at the front fairing, headlight cowl or nose of the vehicle at the stagnation point, routing ram air through a compact U-shaped duct behind the fairing and emitting a forward counterflow jet through an outlet at the front of the fairing or headlight cluster. The geometry is compact and suited to the available space within a motorcycle fairing. For naked bikes without fairings a self-contained ADP unit may be integrated into the headlight nacelle or handlebar stem assembly. Additionally, the device can be applied to or positioned on a rider helmet or garment.

[0035] A motorcycle at motorway speed has a drag coefficient of approximately 0.6 to 0.7, with the rider's body accounting for approximately 70 percent of total frontal area. The ADP addresses the stagnation region directly ahead of the rider and fairing, which is the dominant source of pressure drag. One or more directional outlets positioned on the lateral surfaces of the fairing emit stabilising jets in response to real-time sensor detection of crosswind, lateral ya w or aerodynamic imbalance, counteracting lateral aerodynamic forces and improving vehicle stability a safety benefit not available from any existing motorcycle aerodynamic system.

[0036] When applied to a bicycle, the device may be integrated into a time trial helmet, the nose of a time trial frame, or a handlebar-mounted unit. At track cycling speeds and elite road racing speeds sufficient ram pressure is available for a meaningful counterflow jet. The aerodynamic margins in professional cycling are extremely fine and the ADP’s pre-emptive stagnation region modification represents a novel performance advantage at elite level.

[0037] 9. Application to High-Speed Rail

[0038] When applied to a high-speed train operating predominantly in open air the forward counterflow jet reduces aerodynamic resistance along the full length of the consist. On tunnel entry the jet pre¬ compresses and deflects the air column ahead of the train, reducing tunnel sonic boom and micro¬ pressure waves at tunnel portals. Directed jets seal the gaps between coupled vehicles. Directional jets compensate for crosswind effects.

[0039] 10. Application to Metro and Underground Rail Systems

[0040] When applied to a train in a tightly confined tube bore the device manages the compression wave ahead of the train within the confined air column, reducing the sustained piston effect pressure differential throughout tunnel transit. The device automatically detects tunnel confinement via pressure sensors and switches between open displacement mode and compression wavemanagement mode without manual adjustment. Where the tunnel is equipped with ventilation shafts or cross-passages, the counterflow Jet drives displaced air towards the nearest shaft, performing forced ventilation and removing accumulated heat. Air displaced through ventilation shafts drives turbines positioned within the shafts, generating electrical energy from the kinetic energy of the displaced airflow and recovering aerodynamic energy that would otherwise constitute drag on the train as useful electrical power within the tunnel infrastructure.

[0041] 11. Application to Racing Vehicles

[0042] When applied to a high-downforce racing vehicle including Formula 1, Formula E and Le Mans prototype vehicles, the counterflow jet modifies the pressure distribution ahead of the vehicle simultaneously to reduce frontal pressure drag and to influence the aerodynamic flow conditions acting on downforce-generating surfaces including front wings, diffusers, bargeboards and underbody surfaces, providing combined drag reduction and aerodynamic balance management from a single ram-air-powered system consistent with applicable FIA and ACO sustainability regulations.

[0043] 12. Application to Aircraft

[0044] Ram air inlets are located at low-drag positions such as the aircraft underbelly or wing leading edges, avoiding the nose stagnation point to minimise inlet drag. The entire active aerodynamic management of the aircraft including boundary layer suction, boundary layer blowing, counterflow jet emission and surface anti-icing is powered solely by ram air without any use of engine bleed air, reducing engine load and improving propulsive efficiency. Ram air that can be heated or of any temperature, is automatically allocated between the forward counterflow jet and surface anti-icing functions based on ambient temperature, humidity and icing risk sensor data. For any aircraft including sub, super and hyper -sonic, the device provides a counterflow jet virtual spike instead of the physical aerodynamic spike used on current aircraft such as the F59.

[0045] 13. Application to Watercraft

[0046] Above the waterline the device emits a forward counterflow jet from the leading face of the superstructure to reduce aerodynamic pressure drag. Below the waterline, ram water-flow captured by inlets on the submerged hull and / or by inlets above the waterline, is routed through a duct and emited through a distribution network of micro-perforations, slots or porous panels across the submerged hull surface, forming a continuous air lubrication layer reducing skin friction drag without any external power source. In a further embodiment the device operates simultaneously above and below the waterline, both systems powered entirely by the forward motion of the vessel through their respective fluid media. For high-speed watercraft a ram water- flow-powered compressor generates a continuous gaseous cavitation envelope around the hull. 14. Application to Spacecraft

[0047] The device is active during atmospheric flight phases only — specifically during launch ascent and atmospheric re-entry —• and is inactive during orbital or deep space flight where no fluid medium is present. During re-entry the counterflow jet displaces and deflects the superheated plasma layerahead of the spacecraft while the ram-air cooling channel network simultaneously manages conducted heat through the spacecraft skin, together constituting an integrated active thermal protection system reducing,or eliminating reliance on passive heat shield materials.

[0048] 15. Application to Stationary Objects in Moving Fluid Streams

[0049] The Anti-Drag Penetrator applies equally to stationary or fixed objects positioned within a moving fluid stream, including wind turbine blades, bridge pylons, offshore oil and gas platform legs, buildings and antenna masts. Fluid flow impinging on the leading s rface is captured by one or more inlets, routed through a duct and emitted as a forward-directed counterflow jet into the oncoming fluid stream, modifying the stagnation region and reducing pressure drag and fluid loading. For wind turbines reduced blade drag increases aerodynamic efficiency and power output For offshore structures reduced fluid loading reduces fatigue stress and extends structural service life.

[0050] This invention will now be described by way of example with reference to the following drawings where in:

[0051] FIGURE 1 illustrates a perspective view of an aeroplane with an anti-drag penetrator positioned at the nose 1, emiting a counterflow jet or series of jets 2 that penetrate and deflect the air or atmosphere ahead of the aeroplane, forming a boundary layer that reduces resistance and drag. The jet is emited via an aperture shaped relative to the cross-section of the aeroplane at the required scale, velocity, temperature, and distance. Numerous anti-drag penetrators can additionally be located on the wings, engines, and tail.

[0052] FIGURE 2 illustrates a side elevation view of a motor car with an anti-drag penetrator at position 3, emitting a counterflow jet or series of jets 4 that penetrate and deflect the air or atmosphere ahead of the vehicle, forming a boundary layer that reduces resistance and drag. The jet is emited via an aperture shaped relative to the cross-section of the motor car at the required scale, shape, temperature, distance, and speed. Numerous anti-drag penetrators can additionally be located on the windscreen and side mirrors.

Claims

CLAIMSClaim 1 — An anti drag penetrator is a device that users ram air to form a counterflow jet on a moving vehicle or object.Claim 2 — broad device -independent; An anti-drag penetrator is a device that uses ram air or fluid flow generated by the forward motion of a vehicle, projectile or object, or by a moving fluid stream acting upon a stationary object, and emits it as a forward-directed counterflow jet ahead of the vehicle or object, reducing pressure drag and aerodynamic or hydrodynamic resistance and / or to increase vehicle speed, the device being self-powered by the kinetic energy of the ram air or fluid flow alone without any external energy source, compressor or pressurised storage.Claim 3 — mechanism anchor — independent; An anti-drag penetrator is a device that captures ram air or fluid flow from a moving vehicle, projectile or object, or from a moving fluid stream acting upon a stationary object, and generates a forward-directed counterflow jet that modifies the stagnation region ahead of the vehicle or object before the oncoming fluid medium contacts any surface thereof, controlling airflow and reducing pressure drag or aerodynamic or hydrodynamic resistance.Claim 4— method — independent; A method of reducing aerodynamic or hydrodynamic drag on any moving vehicle, projectile or object, or any stationary object within a moving fluid stream, comprising: capturing fluid flow generated by relative motion between the object and the fluid medium; routing said fluid through a duct or via a parabolic device, reversing flow direction by at least 90 degrees; emitting the fluid as a counterflow jet directed into the oncoming fluid stream such that the jet displaces and deflects the oncoming medium before it contacts any surface of the object; and optionally circulating a portion of said captured and compressed fluid through cooling channels within or beneath the surface of the object to absorb and remove aerodynamic heat; the method being self-powered by the relative motion between object and fluid medium alone without any external energy source.Claim 5— self-powered duct and additive velocity; An anti-drag penetrator as claimed in Claims 1 to 4, wherein the ram air is captured solely by the forward motion of the vehicle, projectile or object through a fluid medium and routed through a duct that reverses the flow direction by at least 90 degrees and converges continuously from inlet to outlet, accelerating the captured flow such that its absolute velocity in the ground reference frame exceeds the forward speed of the vehicle, projectile or object, the device requiring no external energy source, compressor or pressurised storage at operating speed.Claim 6 — pre-emptive displacement zone; An anti-drag penetrator as claimed in any preceding claim, wherein the counterflow jet is emited across a cross-sectional area at least equal to and optionally larger than the frontal cross-section of the vehicle, projectile or object, forming a displacement zone or aerodynamic pre-tunnel ahead of the vehicle through which it continuously travels with a defined clearance margin on all sides, such that the atmosphere encountered by its leading surfaces has already been displaced and deflected before contact, reducing edgeturbulence and extending the effective displacement zone beyond the physical envelope of the vehicle.Claim 7 — rear wake, heated jet and pulsed emission; An anti-drag penetrator as claimed in any preceding claim, wherein the device additionally comprises one or more rearward-facing outlets emitting a pressurising jet into the low-pressure wake to reduce base drag, a heating element powered by a ram-air turbine to reduce the density of the atmosphere ahead of the vehicle, and a pulsed or oscillating emission mode in which jet frequency is tuned to cancel oncoming pressure waves including atmospheric turbulence and tunnel-generated micro-pressure waves, all functions powered by the same ram-air system without any external power source.Claim 8 — components and inlet configurations; An anti-drag penetrator as claimed in any preceding claim, wherein the device comprises one or more of the following in any combination: inlets of fixed or variable geometry including NACA submerged ducts, diffusers, plenum chambers, manifold(s), pitot-style forward-facing inlets, oblique shock inlets, isentropic spike inlets, bifurcated inlets and ram water-flow inlets; flow-reversing ducts of U-shaped, S-shaped or any geometry of fixed or variable cross-section including parabolic inlet-outlet configuration without duct; outlets shaped to match or exceed the vehicle cross-sectional profile; distributed duct networks with independently controllable outlets; ram-air-powered turbines driving heating elements, cooling devices, generators, compressors or vacuum pumps; boundary layer suction and blowing panels; pressure, temperature, angle of attack, yaw, sideslip, humidity and icing sensors; onboard aerodynamic management systems with automated real-time jet parameter adjustment; and supplementary power sources with automatic transition to ram-air-only operation at speed.Claim 9 — rail and racing applications An anti-drag penetrator as claimed in any preceding claim, when applied to a high-speed train, wherein the counterflow jet pre-compresses and deflects the air column ahead of the train on tunnel entry, reducing tunnel sonic boom and micro-pressure waves at tunnel portals, and directed jets seal inter-carriage gaps to prevent turbulent air ingestion; and when applied to a high-downforce racing vehicle including Formula 1, Formula E and Le Mans prototype vehicles, wherein the counterflow jet simultaneously reduces frontal pressure drag and modifies aerodynamic flow conditions acting on downforce-generating surfaces including front wings, diffusers, bargeboards and underbody surfaces; both applications powered by the same ram-air system.Claim 10 — aircraft An anti-drag penetrator as claimed in any preceding claim, when applied to an aircraft, wherein the entire active aerodynamic management of the aircraft including boundary layer suction, boundary layer blowing, surface anti-icing and counterflow jet emission is powered solely by ram air routed through the device without any use of engine bleed air, thereby reducing engine load and improving propulsive efficiency, with heated ram air automatically allocated between the forward counterflow jet and surface anti-icing functions based on real-time temperature, humidity and icing risk sensor data.Claim 11 ~~ watercraft above and below waterline An anti-drag penetrator as claimed in any preceding claim, when applied to a watercraft, wherein a first system applies a forwardcounterflow jet to the above-wateriine superstructure surfaces to reduce aerodynamic pressure drag, and a second system routes ram water-flow captured by inlets on the submerged hull and / or from the above waterline inlets, through a duct and emits it through micro-perforations, slots or porous panels across the submerged hull surface, forming a continuous air lubrication layer reducing hydrodynamic skin friction drag, both systems powered entirely by the forward motion of the watercraft through their respective fluid media without any external energy source; and wherein for high-speed watercraft a ram-water-flow-powered compressor generates a gaseous cavitation envelope around the hull replacing water-hull contact with a lower-resistance gas-hull boundary.Claim 12 ~ spacecraft and hypersonic thermal management An anti-drag penetrator as claimed in any preceding claim, when applied to a spacecraft during atmospheric flight phases including launch ascent and re-entry, wherein the counterflow jet displaces and deflects the superheated plasma layer ahead of the spacecraft reducing aerodynamic heating and reliance on passive heat shield materials, and wherein ram air captured by the inlet and compressed by a ram-air-powered turbine is simultaneously circulated as a coolant flow through cooling channels within or beneath the outer surface of the spacecraft, absorbing and venting conducted heat, the two functions together constituting an integrated active thermal protection system powered entirely by ram air; the device being inactive during orbitai or deep space flight where no fluid medium is present and / or active pending future discovery of space fluid medium; and wherein the active ram-air cooling channel function applies equally to all high-speed vehicles, projectiles and objects subject to aerodynamic heating including supersonic, hypersonic aircraft and ballistic missiles.Claim 13 - virtual aero spike; An anti drag penetrator as claimed in any preceding and subsequent claim where the counterflow jet is a virtual aerodynamic spike thus replacing an aerodynamic spike, to reduce drag and aerodynamic heating and form detached shock wave that alters airflow. Claim 14 — confined bore and metro systems An anti-drag penetrator as claimed in any preceding claim, when applied to a train operating in a tightly confined tunnel bore where cross-sectional clearance is insufficient for significant lateral air displacement, wherein the counterflow jet actively manages the compression wave ahead of the train within the confined air column, reducing the sustained piston effect pressure differential between the leading and trailing faces of the train throughout tunnel transit; and wherein when operating in an interconnected underground tunnel network the device simultaneously reduces pressure wave propagation through the network, reducing pressure pulses at stations and platforms, and provides forced ventilation airflow reducing tunnel thermal load; the device automatically detecting tunnel confinement via pressure sensors and switching between open displacement mode and compression wave management mode without manual adjustment.Claim 15 — tunnel ventilation shaft coordination and energy recovery An anti-drag penetrator as claimed in any preceding claim, when applied to a train operating m a tunnel equipped with ventilation shafts, cross-passages or pressure relief openings, wherein the counterflow jet drives displaced air towards the nearest ventilation shaft ahead of the train, the shaft acting as a controlled pressure relief outlet reducin the piston effect pressure differential and simultaneouslyperforming forced ventilation of the tunnel environment to remove accumulated heat; and wherein air driven through the ventilation shafts powers one or more turbines positioned within said shafts, generating electrical energy from the kinetic energy of the displaced airflow and recovering aerodynamic energy that would otherwise constitute drag on the train as useful electrical power within the tunnel infrastructure.Claim 16 — stationary objects in moving fluid streams An anti-drag penetrator as claimed in any preceding claim, when applied to a stationary or fixed object within a moving fluid stream including wind turbine blades, bridge pylons, offshore platform structures and buildings, wherein the fluid flow impinging on the leading surface of the object is captured by one or more inlets, routed through a duct, and emitted as a forward-directed counterflow jet into the oncoming fluid stream, modifying the stagnation region and reducing pressure drag and fluid loading, the device operating from the kinetic energy of the moving fluid alone without any external power source. Claim 17 — active ram-air cooling for all high-speed vehicles An anti-drag penetrator as claimed in any preceding claim, wherein ram air captured by the inlet and compressed by a ram-air-powered turbine is circulated as a coolant flow through cooling channels within or beneath the surface of any vehicle, projectile or object subject to aerodynamic heating at any speed, absorbing and venting frictional and stagnation-point heat from the vehicle structure without any dedicated coolant fluid, pump or external power source, the cooling channel network being independently operable from the counterflow jet function or operating simultaneously with it.Claim 18 - an Anti drag penetrator as claimed in any preceding and subsequent claim where the emitted ram air powered jet(s) or counterflow jet(s) is / are of any form including pulsating, oscillating, cyclonic, angled, intersecting and annular and from any position(s) on the vehicle or object.Claim 19 — two-wheeled vehicle stability An anti-drag penetrator as claimed in any preceding claim, when applied to a two-wheeled vehicle including a motorcycle or bicycle, wherein one or more directional outlets are positioned on the lateral surfaces of the vehicle or rider fairing and configured to emit stabilising jets in response to real-time sensor detection of crosswind, lateral yaw or aerodynamic imbalance, counteracting lateral aerodynamic forces and improving vehicle stability, the stabilising jets being powered by the same ram-air system as the forward counterflow jet and additionally where an anti drag penetrator can be positioned on the rider helmet or as an attachable accessory to reduce resistance and drag and increase speed of the vehicle.Claim 20 — omnibus combination An anti-drag penetrator as claimed in any preceding claim, comprising any additional components including diffusers, plenum chambers, manifolds and combination of the features, components, configurations, inlet types, duct geometries, outlet profiles, thermal management functions, sensor systems, control systems and application-specific embodiments described in Claims 1 to 16, applied to any moving vehicle, aircraft, drone, projectile or object or any stationary object within a moving fluid stream, operating in any fluid medium including air, water, gas or plasma, at any speed from rest to hypersonic, the device in all cases being powered primarily by the kinetic energy of the relative motion between the object and thefluid medium. being powered primarily by the kinetic energy of the relative motion between the object and the fluid medium.

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