National Advisory Committee for Aeronautics (NACA) - 13,806 Matching Results

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A Method for Prevention of Screaming in Rocket Engines

Description: From Summary: "Lateral and longitudinal combustion-pressure oscillations that occurred in screaming combustion of a 1000-pound-thrust rocket engine using white fuming nitric acid and JP-4 fuel as propellants were successfully prevented by means of longitudinal fins in the combustion chamber. Fin position was critical, and complete attenuation was achieved only when the fins were located in a zone approximately 8 to 16 inches from the injector. Fins located in other zones, that is, near the injector or far downstream from the injector, did not stop the oscillations."
Date: August 19, 1954
Creator: Male, Theodore & Kerslake, William R.
Partner: UNT Libraries Government Documents Department

A Body Modification to Reduce Drag Due to Wedge Angle of Wing with Unswept Trailing Edge

Description: From Summary: "Ward's slender-body-theory formula for zero-lift drag contains three integrals plus a base-drag term. Two of these integral terms depend only upon the cross-sectional area distribution of the body. The third integral term depends only upon the body shape and axial slopes at the base of the body. This term is neglected in the transonic area rule because in many cases it is zero; however, there are also many cases in which it is not zero. This paper examines the term for the possibility of drag reduction for a particular case."
Date: July 1958
Creator: Pitts, William C. & Nielsen, Jack Norman
Partner: UNT Libraries Government Documents Department

The Interference Effects of a Body on the Spanwise Load Distributions of Two 45 Degree Sweptback Wings of Aspect Ratio 8.02 from Low-Speed Tests

Description: From Summary: "Tests of two wing-body combinations have been conducted in the Langley 19-foot pressure tunnel at a Reynolds number of 4 x 10(exp 6) and a Mach number of 0.19 to determine the effects of the bodies on the wing span load distributions. The wings had 45 degrees sweepback of the quarter-chord line, aspect ratio 8.02, taper ratio 0.45, and incorporated 12-percent-thick airfoil sections streamwise. One wing was untwisted and uncambered whereas the second wing incorporated both twist and camber. Identical bodies of revolution, of 10:1 fineness ratio, having diameter-to-span ratios of 0.10, were mounted in mid-high-wing arrangements."
Date: April 1956
Creator: Martina, Albert P.
Partner: UNT Libraries Government Documents Department

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. Iii - Swept-wing Fighter-bomber Configuration With Large and Small Stores. Mach Number, 1.61

Description: Origin of supersonic store interference from measurements of individual forces - swept-wing fighter-bomber with large & small stores.
Date: September 15, 1955
Creator: Carlson, H. W. & Smith, N. F.
Partner: UNT Libraries Government Documents Department

The Origin and Distribution of Supsonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. V - Swept-wing Heavy-bomber Configuration With Large Store Nacelle . Mach Number 2.01

Description: Origin & distribution of supersonic store interference/measurement of individual forces - swept-wing heavy bomber with large store figure.
Date: February 13, 1956
Creator: Carlson, H. W. & Geier, D. J.
Partner: UNT Libraries Government Documents Department

Performance of five short multielement turbojet combustors for hydrogen fuel in quarter-annulus duct

Description: Report described five short multielement turbojet combustors for use with hydrogen fuel and their performance. Information about the combustion efficiency, temperature profiles, pressure loss, durability, and comparison with previous short combustors is included.
Date: July 22, 1958
Creator: Jones, Robert E. & Rayle, Warren D.
Partner: UNT Libraries Government Documents Department

Performance of an All-internal Conical Compression Inlet With Annular Throat Bleed at Mach Number 5.0

Description: Report presenting an investigation of an all-internal conical compression inlet with annular bleed at the throat at Mach number 5.0 and zero angle of attack. Results regarding the performance of the diffuser alone, a Pitot-pressure survey of the flow leaving the diffuser, total-pressure distribution, and inlet efficiencies are provided.
Date: August 6, 1958
Creator: Stitt, Leonard E. & Obery, Leonard J.
Partner: UNT Libraries Government Documents Department

Performance of several half-conical side inlets at supersonic and subsonic speeds

Description: Report discussing an evaluation of a series of half-conical side inlets mounted on the fuselage of a supersonic aircraft at various Mach numbers. Information about the maximum total-pressure recovery, asymmetrical operation of the twin-duct system, potential reduction in stable mass-flow range, boundary-layer diverter height, and engine mass flow is described.
Date: February 1, 1956
Creator: Stitt, Leonard E.; Cubbison, Robert W. & Flaherty, Richard J.
Partner: UNT Libraries Government Documents Department

Performance of twin-duct variable-geometry side inlets at mach numbers of 1.5 to 2.0

Description: Report presenting testing of the performance of a twin-duct air-intake system mounted on the sides of a 1/8-scale fuselage forebody model of a proposed aircraft at several Mach numbers, angles of attack, and yaw. Results regarding the inlet survey, compression-surface boundary-layer removal and effects of second-ramp position, instability, effect of cant on inlet performance, inlet performance with 0 and 30 degree second ramp angles, performance with fixed second-ramp angles, and effect of canards are provided.
Date: January 21, 1957
Creator: Yeager, Richard A.; Beheim, Milton A. & Klann, John L.
Partner: UNT Libraries Government Documents Department

Performance of Pentaborane, Pentaborane - JP-4 Fuel Mixtures, and Trimethylborate Azeotrope Fuel in a Full-scale Turbojet Engine

Description: Report presenting summaries of full-scale engine tests of pentaborane, pentaborane-JP-4 fuel mixtures, and trimethylborate-methyl-alcohol-azeotrope fuels. Tests were conducted at an altitude of 50,000 feet and Mach number of 0.8. Results regarding the fuel effects on overall performance, effects on component performance, effect of turbine-outlet temperature on engine performance, and miscellaneous observations are provided.
Date: November 20, 1956
Creator: Breitwieser, Roland & Useller, James W.
Partner: UNT Libraries Government Documents Department

Performance of an Inlet Having a Variable-angle Two-dimensional Compression Surface and a Fixed-geometry Subsonic Diffuser for Application to Reduced Engine Rotative Speeds- Mach Numbers 0.66, 1.5, 1.7, and 2.0

Description: Report presenting the performance of a two-dimensional side inlet with a technique of varying compression-surface angle while retaining a fixed-geometry diffuser at several Mach numbers and zero angle of attack. A 12 degree compression ramp was faired into the diffuser contour in this conventional manner. Results regarding the inlet flow field, application to reduced engine speeds, and a inlet performance with a sudden expansion in the diffuser are provided.
Date: January 30, 1958
Creator: Allen, John L.
Partner: UNT Libraries Government Documents Department

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselage-store Configurations. Ii - Swept-wing Heavy-bomber Configuration With Large Store Nacelle . Lateral Forces and Pitching Moments, Mach Number, 1.61

Description: Effect of large store /nacelle/ on a swept-wing heavy bomber - lateral force and pitching moments.
Date: July 6, 1955
Creator: Carlson, H. W. & Smith, N. F.
Partner: UNT Libraries Government Documents Department

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. 1.-swept-wing Heavy-bomber Configuration With Large Store Nacelle . Lift and Drag, Mach Number, 1.61

Description: Supersonic store interference - 1, swept-wing heavy bomber with large stores - lift & drag at mach 1.61.
Date: March 11, 1955
Creator: Carlson, H. W. & Smith, N. F.
Partner: UNT Libraries Government Documents Department

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wingfuselage-store Configurations. Iv.-delta-wing Heavy-bomber Configuration With Large Store. Mach Number, 1.61

Description: Origin and distribution of supersonic store interference/measurement of individual forces on delta-wing heavy bomber configuration mach 1.61.
Date: December 15, 1955
Creator: Morris, O. A.
Partner: UNT Libraries Government Documents Department