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Optimum Lifting Bodies at High Supersonic Airspeeds

Description: Memorandum presenting a determination of the shapes of bodies with minimum pressure drag for a given lift at high supersonic speeds and satisfying conditions of given length and width with the aid of Newton's law of resistance. The resulting shapes have flat bottoms which are also rectangular. To determine if the bodies do actually have improved lift-drag ratios at high supersonic speeds, several wedges satisfying numerically different sets of given conditions were tested at Mach number 5.
Date: May 7, 1954
Creator: Rosnikoff, Meyer M.
Partner: UNT Libraries Government Documents Department

Preliminary Analysis of Problem of Determining Experimental Performance of Air-Cooled Turbine 2: Methods for Determining Cooling-Air-Flow Characteristics

Description: In the determination of the performance of an air-cooled turbine, the cooling-air-flow characteristics between the root and the tip of the blades must be evaluated. The methods, which must be verified and the unknown functions evaluated, that are expected to permit the determination of pressure, temperature, and velocity through the blade cooling-air passages from specific investigation are presented.
Date: June 7, 1950
Creator: Ellerbrock, Herman H., Jr.
Partner: UNT Libraries Government Documents Department

Identification of Foreign Objects Damaging Compressor Blades in Turbojet Engines

Description: "Damage to the compressor blades of turbojet engines due to ingestion of foreign objects is a growing problem, the solution of which has been made more difficult by the large percentage of damaging materials that have remained unknown. A rapid emission spectroscopic method was devised to identify the chemical composition of these foreign objects. Results on laboratory-prepared specimens and blades from damaged engines show that the method can be utilized to determine the nature of the ingested foreign objects" (p. 1).
Date: January 7, 1957
Creator: Spakowski, A. E. & Graab, J.
Partner: UNT Libraries Government Documents Department

Langley 9-Inch Supersonic Tunnel Tests of Several Modifications of a Supersonic Missile Having Tandem Cruciform Lifting Surfaces: Three-Component Data Results of Models Having Ratios of Wing Span to Tail Span Equal to 1

Description: Memorandum presenting tests in the 9-inch supersonic tunnel to investigate the factors that determine the magnitude of the wing-tail interference effects on the static longitudinal stability of supersonic missile configurations with low-aspect-ratio, tandem, cruciform lifting surfaces and to develop a missile configuration with a minimum variation in static margin due to wing-tail interference effects.
Date: March 7, 1951
Creator: Rainey, Robert W.
Partner: UNT Libraries Government Documents Department

Langley 9-Inch Supersonic Tunnel Tests of Several Modifications of a Supersonic Missile Having Tandem Cruciform Lifting Surfaces: Three-Component Data Results of Models Having Ratios of Wing Span to Tail Span Equal to and Less Than 1 and Some Static Rolling-Moment Data

Description: Memorandum presenting lift, drag, and pitching-moment data and some static rolling-moment data are presented for missile configurations having wing-tail-span ratios equal to and less than 1. The configurations include variations in wing and tail plan forms, wing-tail-span ratios, body length, and nose shape.
Date: March 7, 1951
Creator: Rainey, Robert W.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation at Low Speed of a Wing Having 63 Degree Sweepback and a Drooped Tip

Description: From Summary: "The results of force tests made at low speed are presented to show the effect of longitudinal static stability produced by drooping the tip of a 63 degree sweptback wing. Five semispan wing models were tested: two incorporated curved drooped tips, two with abruptly drooped tips, and one without droop. The most favorable stability characteristics were measured for a model with an abruptly drooped tip, a fence, and a leading-edge flap; however, the use of these same auxiliary devices on the undrooped wing was nearly as effective."
Date: April 7, 1955
Creator: Blackaby, James R.
Partner: UNT Libraries Government Documents Department

Method of Determining Centrifugal-Flow-Compressor Performance With Water Injection

Description: Memorandum presenting a method for computing the isentropic and actual enthalpy change between the inlet and outlet of a centrifugal-flow compressor when water injection is used. The method of calculation is based on fluid property values given in steam and air tables.
Date: September 7, 1949
Creator: Hamrick, Joseph T. & Beede, William L.
Partner: UNT Libraries Government Documents Department

Cooperative Investigation of Relationship Between Static and Fatigue Properties of Heat-Resistant Alloys at Elevated Temperatures

Description: Memorandum presenting a study of the relationship between the static and dynamic properties of heat-resistant alloys at high temperatures. An auxiliary objective is to provide a better basis for evaluating the results from the various types of fatigue machines.
Date: March 7, 1951
Creator: NACA Subcommittee on Heat-Resisting Materials
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of the Motion of a 1/10-Scale Model of the Douglas XF4D-1 Escape Capsule When Jettisoned by Jet Ejection: TED No. NACA DE 359

Description: Memorandum presenting a wind-tunnel investigation at low speed to determine the path and motion of a scale model of the Douglas XF4D-1 escape capsule without the drogue parachute when jettisoned by jet ejection. The investigation included determination of the vertical and horizontal accelerations of the capsule. Results regarding the ejection at zero airspeed, ejection at 570 feet per second, and at 863 feet per second are provided.
Date: October 7, 1953
Creator: Johnson, Harold S.
Partner: UNT Libraries Government Documents Department

Data From Large-Scale Low-Speed Tests of Airplane Configurations With a Thin 45 Degree Swept-Wing Incorporating Several Leading-Edge Contour Modifications

Description: Memorandum presenting force tests that have been made of airplane configurations with a thin swept wing incorporating several wing-contour modifications forward of maximum thickness. Both longitudinal and lateral characteristics are provided.
Date: May 7, 1956
Creator: Evans, William T.
Partner: UNT Libraries Government Documents Department

The Effect of Air Jets Simulating Chines or Multiple Steps on the Hydrodynamic Characteristics of a Streamline Fuselage

Description: Memorandum presenting preliminary tests in order to determine the effect of forced ventilation on the hydrodynamic characteristics of a scale model of a streamline fuselage of a hypothetical transonic airplane. The forced ventilation consisted of air ejected at about 300 feet per second through small orifices distributed over the fuselage bottom in a series of patterns simulating chines or multiple steps. Results regarding resistance, effective hydrodynamic lift, trim, spray, and air flow are provided.
Date: January 7, 1949
Creator: Weinflash, Bernard
Partner: UNT Libraries Government Documents Department

The Effects of Leading-Edge Extensions, a Trailing-Edge Extension, and a Fence on the Static Longitudinal Stability of a Wing-Fuselage-Tail Combination Having a Wing With 35 Degrees of Sweepback and an Aspect Ratio of 4.5

Description: Memorandum presenting an investigation of the leading-edge extensions, a trailing-edge extension, and a fence on the static longitudinal stability of a wing-fuselage-tail combination with a wing with 35 degrees of sweepback and an aspect ratio of 4.5. The investigation involved the use of force measurements and tuft studies on stall progression. Results regarding a model with unmodified wing, the effect of leading-edge modifications, the effects of the fence, a summary of the effects of compressibility, and some remarks on flow separation are provided.
Date: August 7, 1953
Creator: Selan, Ralph & Bandettini, Angelo
Partner: UNT Libraries Government Documents Department

Free-flight-tunnel investigation of the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with self-supporting free-floating fuel tanks attached to the wing tips

Description: Report presenting an investigation in the free-flight tunnel to determine the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with self-supporting, free-floating fuel tanks attached to the wing tips. The results showed that the flight behavior of the configuration could be made satisfactory when sufficient restoring moment was supplied. Results regarding the flight behavior, rolling motions, motions of the bomber and attached tanks, and flight records for different gearing ratios are provided.
Date: August 7, 1951
Creator: Bennett, Charles V. & Cadman, Robert B.
Partner: UNT Libraries Government Documents Department

Theoretical study of the tunnel-boundary lift interference due to slotted walls in the presence of the trailing-vortex system of a lifting model

Description: Report presenting some equations that give the interference on the trailing-vortex system of a uniformly loaded finite-span wing in a circular tunnel containing partly open and partly closed walls, with special reference to symmetrical arrangements of the open and closed portions. Methods are given for extending the equations to include tunnel shapes other than circular.
Date: April 7, 1953
Creator: Matthews, Clarence W.
Partner: UNT Libraries Government Documents Department

Pressure distribution at low speed on a model incorporating a W wing with aspect ratio 6, 45 degrees sweep, taper ratio 0.6, and an NACA 65A009 airfoil section

Description: Report presenting results of pressure-distribution measurements at low speed on a wing-fuselage combination with a wing of W plan form with aspect ratio 6, 45 degrees sweep, taper ratio 0.6, and an NACA 65A009 airfoil section placed parallel to the plane of symmetry. Results regarding aerodynamic characteristics, pressure distribution on the wing, pressure distribution on the fuselage, aerodynamic section characteristics, and stall patterns are provided.
Date: August 7, 1952
Creator: Polhamus, Edward C. & Few, Albert G., Jr.
Partner: UNT Libraries Government Documents Department

An investigation of single-degree-of-freedom snaking oscillations on a model of a high-speed research airplane by the NACA wing-flow method

Description: Report presenting an investigation by the wing-flow method to determine the snaking characteristics of a scale partial-model of a research airplane. Additionally, the snaking characteristics of 11 modified configurations of the research-airplane model were determined as well as a model that had a greater fineness ratio.
Date: August 7, 1951
Creator: Johnson, Harold I. & Faber, Stanley
Partner: UNT Libraries Government Documents Department

Preliminary investigation of combustion in flowing gas with various turbulence promoters

Description: Report presenting an investigation of combustion occurring downstream of various turbulence promoters in a 20-inch length of a 1 7/8-inch inside-diameter, water-jacketed tubing using premixed vaporized fuel and air. Among the turbulence promoters investigated were flat plates perforated with 1/8-inch diameter holes, 1/4-inch diameter holes, and a single large hole to give 12.4, 17.2, and 21.5 percent open area respectively.
Date: June 7, 1948
Creator: Haddock, Gordon W. & Childs, J. Howard
Partner: UNT Libraries Government Documents Department

An investigation of three NACA 1-series nose inlets at subsonic and transonic speeds

Description: Report presenting an investigation of three NACA 1-series nose inlets at subsonic and transonic speeds in the 8-foot transonic tunnel. Drag, surface-pressure, and pressure-recovery measurements and schileren photographs were obtained at zero angle of attack through a range of Mach numbers and mass-flow-ratios. Results regarding tunnel boundary interference, surface pressure distribution, external drag, and pressure recovery are provided.
Date: January 7, 1953
Creator: Pendley, Robert E.; Milillo, Joseph R. & Fleming, Frank F.
Partner: UNT Libraries Government Documents Department

Measurements of fluctuating pressures on a 1/4-scale model of the X-1 airplane with a 10-percent-thick wing in the Langley 16-foot transonic tunnel

Description: Report presenting pressure fluctuations measured near the trailing edge of the wing and near the leading edge of the tail of a scale model of the X-1 airplane with a 10-percent-thick wing in the 16-foot transonic tunnel. Results regarding frequency analyses are also provided.
Date: January 7, 1953
Creator: Habel, Louis W. & Steinberg, Seymour
Partner: UNT Libraries Government Documents Department

Static longitudinal stability and control of a convertible-type airplane as affected by articulated- and rigid-propeller operation

Description: Report presenting the results of an investigation in the full-scale tunnel of the static longitudinal stability and control of a convertible-type airplane as affected by articulated- and rigid-propeller operation. The investigation included force measurements for a large angle-of-attack range with the all-movable horizontal tail installed and removed.
Date: November 7, 1949
Creator: Lange, Roy H. & McLemore, Huel C.
Partner: UNT Libraries Government Documents Department

A flight investigation at transonic speeds of a model having a triangular wing of aspect ratio 2

Description: Report presenting free-falling recoverable model tests conducted at transonic speeds on a model with a triangular wing of aspect ratio 2 and a 45 degree swept tail in the chord plane of the wing. Static- and dynamic-longitudinal-stability data for the complete model, force and moment data for the major components of the model, and load distributions over the fuselage of the model were evaluated at several angles of attack.
Date: September 7, 1955
Creator: White, Maurice D.
Partner: UNT Libraries Government Documents Department

Bonded lead monoxide films as solid lubricants for temperatures up to 1250 degrees F

Description: Report presenting a friction, wear, and endurance-lift study made with bonded films of mixed oxides containing lead monoxide (PbO) as the main component. The coatings lubricated over the entire temperature range, but were far more effective from 500 to 1250 degrees Fahrenheit than at the lower temperatures. Results regarding the effect of silica additions on coating formation, determination of coating composition, effect of coating thickness on friction and wear, effect of temperature on friction and wear, and endurance properties are provided.
Date: May 7, 1957
Creator: Sliney, Harold E. & Johnson, Robert L.
Partner: UNT Libraries Government Documents Department

Longitudinal stability and control characteristics at Mach numbers of 1.41 and 2.01 of a 67 degree swept-wing airplane configuration with canard control surfaces

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41 and 2.01 to determine the stability and control characteristics of a canard-controlled airplane configuration with potentially high values of lift-drag ratio. The configurations investigated included a plane and a twisted wing with approximately 67 degrees of sweep and an aspect ratio of 2.91 and three trapezoidal canard surfaces with ratios of exposed area to wing area of 0.032, 0.076, and 0.121.
Date: July 7, 1958
Creator: Spearman, M. Leroy & Robinson, Ross B.
Partner: UNT Libraries Government Documents Department