US3137460A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Improving supersonic lift-to-drag ratio by compression shock
Assignee: North American Aviation Corp
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Filing: 1957-11-01
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Granted: 1964-06-16
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Expires: 1977-11-01
Abstract
No abstract record available.
Inventors
- 👤 Jr George A Owl
- 👤 Arthur C Ley
- 👤 Donald J Beck
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 04:18
CPC Classifications
B; B64; B64C; B64C30/00; B64C23/00; B64C23/005
Claims Analysis
Total Claims: 2
Claim 1
Independent Claim
133 words
IN AN AIRCRAFT POWERED BY AN AIR-BREATHING ENGINE AND CAPABLE OF SUPERSONIC FLIGHT, THE COMBINATION OF AN AIRFOIL HAVING A SWEPT BACK LEADING EDGE, AN ENGINE AIR INLET DUCT BENEATH SAID AIRFOIL SURFACE, AN ADJUSTABLE VERTICAL WEDGE MEANS POSITIONED IN SAID INLET DUCT AND EXTENDING FORWARDLY THEREFROM FOR ACHIEVING OPTIMUM PRESSURE RECOVERY OF THE ENGINE INLET AIR AND ATTAINING OPTIMUM ENGINE THRUST, SAID WEDGE MEANS FURTHER HAVING AN INCLUDED ANGLE AND BEING LOCATED RELATIVE TO SAID LEADING EDGE SUCH THAT THE OBLIQUE SHOCK WAVE GENERATED BY SAID WEDGE MEANS AT A PREDETERMINED MACH NUMBER SUBSTANTIALLY COINCIDES IN PLANFORM WITH THE AIRFOIL SWEPT BACK LEADING EDGE WHEREBY THE SHOCK PRESSURE FIELD GENERATED BY SAID WEDGE ACTS ON THE UNDERSURFACE OF SAID AIRFOIL TO PROVIDE GREATER LIFT AND INCREASE THE LIFT-TO-DRAG RATIO OF THE AIRCRAFT.
Claim 2
Dependent Claim
133 words
IN AN AIRCRAFT POWERED BY AN AIR-BREATHING ENGINE AND CAPABLE OF SUPERSONIC FLIGHT, THE COMBINATION OF AN AIRFOIL HAVING A SWEPT BACK LEADING EDGE, AN ENGINE AIR INLET DUCT BENEATH SAID AIRFOIL SURFACE, AN ADJUSTABLE VERTICAL WEDGE MEANS POSITIONED IN SAID INLET DUCT AND EXTENDING FORWARDLY THEREFROM FOR ACHIEVING OPTIMUM PRESSURE RECOVERY OF THE ENGINE INLET AIR AND ATTAINING OPTIMUM ENGINE THRUST, SAID WEDGE MEANS FURTHER HAVING AN INCLUDED ANGLE AND BEING LOCATED RELATIVE TO SAID LEADING EDGE SUCH THAT THE OBLIQUE SHOCK WAVE GENERATED BY SAID WEDGE MEANS AT A PREDETERMINED MACH NUMBER SUBSTANTIALLY COINCIDES IN PLANFORM WITH THE AIRFOIL SWEPT BACK LEADING EDGE WHEREBY THE SHOCK PRESSURE FIELD GENERATED BY SAID WEDGE ACTS ON THE UNDERSURFACE OF SAID AIRFOIL TO PROVIDE GREATER LIFT AND INCREASE THE LIFT-TO-DRAG RATIO OF THE AIRCRAFT.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1967-06-16 | 1967-12-16 | 1968-06-16 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1971-06-16 | 1971-12-16 | 1972-06-16 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1975-06-16 | 1975-12-16 | 1976-06-16 | $7700.00 | Window Closed / Lapsed |