A monolithic bullet has a tapered nose and a cylindrical shank. The shank has a sealing boss, a groove, a case alignment boss, and a bore riding surface. The case alignment boss is adjacent the nose and has a diameter greater than the nominal groove diameter of a rifle barrel of the same caliber as the bullet. The groove is adjacent the sealing boss and has a diameter less than the nominal groove diameter of the barrel. The case alignment boss is adjacent the groove and has a diameter approximately equal to or less than the nominal groove diameter of the barrel. The bore riding surface has a diameter approximately equal to the nominal bore diameter of the barrel.

A method for making an improved projectile 360, 460 by defining a discontinuity, groove or trough in a distal ogive section of the projectile to provide an external ballistic. effect uniforming surface feature (e.g., nose ring groove 369, 469) which makes an unsupported gap in the ogive profile that beneficially affects the flow of air over the front half of the ogive. The improved bullet's external surface discontinuity feature (369 or 469) creates effects in the flowfield that dominate any dynamic effects from bullet-to bullet manufacturing inconsistency and resultant differences in dynamic behavior.

A method of reducing low-energy flow in a flight vehicle engine includes an isolator of the engine having a swept-back wedge to improve flow mixing. The wedge includes forward shock-anchoring locations, such as edges or rapidly-curved portions, that anchor oblique shocks in situations where the isolator has sufficient back pressure. The swept-back wedge may also create swept oblique shocks along its length. Boundary layer flow streamlines are diverted running parallel to or parallel but moving outward conically to the swept-wedge leading edge moving outboard and upward. The non-viscous flow outside the boundary layer is processed through the swept-back ramp shock and diverted outboard and upward as well. The outboard aft portion of the wedge at the sidewall intersection may also induce shocks and divert flow near the walls closer toward the walls and upward, and/or improve flow mixing.

A method of reducing low-energy flow in a flight vehicle engine includes an isolator of the engine having a swept-back wedge to improve flow mixing. The wedge includes forward shock-anchoring locations, such as edges or rapidly-curved portions, that anchor oblique shocks in situations where the isolator has sufficient back pressure. The swept-back wedge may also create swept oblique shocks along its length. Boundary layer flow streamlines are diverted running parallel to or parallel but moving outward conically to the swept-wedge leading edge moving outboard and upward. The non-viscous flow outside the boundary layer is processed through the swept-back ramp shock and diverted outboard and upward as well. The outboard aft portion of the wedge at the sidewall intersection may also induce shocks and divert flow near the walls closer toward the walls and upward, and/or improve flow mixing.

Intermediate for the production of a projectile in particular a deformable bullet, consisting of a ductile blank, which is cold-formed into the intermediate by means of pressing, a cylindrical solid base end section and a press end section with a central press recess incorporated by means of pressing and a wall limiting the press recess to form an ogival shaped tip, wherein the wall is formed with at least two slots extending in the axial direction of the intermediate, which separate at least two prongs in the circumferential direction of the intermediate, wherein the at least two slots extend by more than 10% of an axial total longitudinal extension of the intermediate from the wall end towards the base end section.

Intermediate for the production of a projectile in particular a deformable bullet, consisting of a ductile blank, which is cold-formed into the intermediate by means of pressing, a cylindrical solid base end section and a press end section with a central press recess incorporated by means of pressing and a wall limiting the press recess to form an ogival shaped tip, wherein the wall is formed with at least two slots extending in the axial direction of the intermediate, which separate at least two prongs in the circumferential direction of the intermediate, wherein the at least two slots extend by more than 10% of an axial total longitudinal extension of the intermediate from the wall end towards the base end section.

A ballistically enhanced projectile 360, 460 includes a body having a distal ogive section with external ballistic effect uniforming surface discontinuity (e.g., nose ring groove 369, 469) defined therein to provide an unsupported gap in the ogive profile which affects the flow of air over the front half of the ogive to provide greater aerodynamic uniformity and shot-to-shot consistency with more uniform observed external ballistics and superior terminal ballistics. The bullet's external surface discontinuity feature (369 or 469) creates effects in the flowfield that dominate any dynamic effects from bullet-to-bullet manufacturing inconsistency and resultant differences in dynamic behavior.

A water penetrating blowgun dart is provided. The blowgun dart has a funnel removably attached to a tail end of the dart shaft so that upon contact with a water surface, the funnel moves from an engaged configuration to a disengaged configuration. The tail end may provide a slot for snugly receiving an eye, wherein the tail end and the eye have cooperating grooves so that when in the engaged configuration, the eye and tail end are secured with a filament that slightly protrudes from the flush outer surface of the shaft and eye. The protruding filament frictionally engages the funnel in the engaged configuration so that the funnel remains engaged with the shaft prior to hitting the water's surface.

A cover 10 and method for protecting a missile 15 with stowed wings 20 and connected to a vessel carrying it. The cover 10 includes a spoiler shaped front part 25 for covering a gap between the wings 20 of the missile 15 and the fuselage of the missile 15 for minimizing aerodynamic forces.

Waveguide or flow guide surfaces can improve the efficiency of fluid flow through tubes or over surfaces. When incorporated in a tube, the waveguides improve flow and function as sound absorbers making them useful in engine mufflers, firearm silencer/suppressors and jet engine exhaust attenuators. On surfaces, the waveguides can reduce fluid drag and find use on projectiles (e.g., bullets), airfoils for aircraft, and land borne vehicles. The waveguide array in either a tubular chamber or on a surface comprises a plurality of successive wave-like undulations inclined generally in the direction of flow and when employed in tubes extending inwardly to permit an unobstructed path for the fluid gas from entry to exit. The waves define annular wave cavities between their successive inwardly extending edges and the wall of the chamber with each cavity having a cavity mouth open to the unobstructed path. The waveguides are sized and spaced so that gas vortices are created within the cavities when gas flow occurs which vortices create a fluid boundary layer that assists the gas flow.