Claims
- 1. In a laser system having a housing, laser cavity, an aperture located within said housing adjacent said cavity, a passageway extending from and surrounding said aperture and an aerodynamic window optically aligned with said aperture in said housing, the improvement therein residing in said aerodynamic window, said aerodynamic window comprising means having its longitudinal axis extending transversely across said passageway for allowing a supersonic flow of gas to pass therethrough, means for providing gas to said supersonic flow passing means, said supersonic flow passing means being divided into an entrance duct and a capture duct, a wedge-shaped element located in said entrance duct and a diffuser vane located in said capture duct, at least two shock waves being generated at said wedge-shaped element and crossing said passageway, said diffuser vane intersecting at least one of said pair of shock waves, whereby said aerodynamic window substantially reduces flow separation in said capture duct.
- 2. In a laser system as defined in claim 1 wherein said pair of generated shock waves are formed of a first shock wave generated at the leading edge of said wedge-shaped element and a second shock wave generated at the exit edge of said wedge-shaped element, said diffuser vane intersecting said second shock wave.
- 3. In a laser system as defined in claim 1 wherein said wedge-shaped element protrudes into said passageway.
- 4. In a laser system as defined in claim 3 wherein said pair of generated shock waves are formed of a first shock wave generated at the leading edge of said wedge-shaped element and a second shockwave generated at the exit edge of said wedge-shaped element, said diffuser vane intersecting said second shock wave.
- 5. In a laser system as defined in claim 4 wherein said diffuser vane is adjustably mounted within said capture duct for movement in a direction both transverse and parallel to said longitudinal axis of said supersonic flow passing means.
- 6. In a laser system as defined in claim 1 wherein said capture duct has an entrance wall, said entrance wall diverging at a preselected angle with respect to said longitudinal axis of said supersonic flow passing means.
- 7. In a laser system as defined in claim 6 wherein said preselected angle is approximately 16.degree..
- 8. In a laser system as defined in claim 7 wherein said diffuser vane is adjustably mounted in said capture duct for movement in a direction both transverse and parallel to said longitudinal axis of said supersonic flow passing means.
- 9. A multiple shock aerodynamic window for providing a separation between two regions of differing pressures comprising a passageway having an inlet and an outlet, said inlet being connected to one region of pressure and said outlet being connected to another region of pressure, means having its longitudinal axis extending transversely across said passageway for allowing a supersonic flow of gas to pass therethrough, means for providing gas to said supersonic flow passing means, said supersonic flow passing means being divided into an entrance duct and a capture duct, a wedge-shaped element located in said entrance duct and a diffuser vane located in said capture duct, at least two shock waves being generated at said wedge-shaped element and crossing said passageway, said diffuser vane intersecting at least one of said shock waves thereby substantially reducing the flow separation in said capture duct.
- 10. A multiple shock aerodynamic window as defined in claim 9 wherein said wedge-shaped element protrudes into said passageway.
- 11. A multiple shock aerodynamic window as defined in claim 10 wherein said pair of generated shock waves are formed of a first shock wave generated at the leading edge of said wedge-shaped element and a second shock wave which is generated at the exit edge of said wedge-shaped element, said diffuser vane intersecting said second shock wave.
- 12. A multiple shock aerodynamic window as defined in claim 11 wherein said capture duct has an entrance wall, said entrance wall diverging at a preselected angle with respect to said longitudinal axis of said supersonic flow passing means.
STATEMENT OF GOVERNMENT INTEREST
The invention described herein may be manufactured and used by or for the Government for governmental purposes without the payment of any royalty thereon.
US Referenced Citations (6)