National Advisory Committee for Aeronautics (NACA) - 80 Matching Results

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Aerodynamic Research on Fuselages with Rectangular Cross Section

Description: The influence of the deflected flow caused by the fuselage (especially by unsymmetrical attitudes) on the lift and the rolling moment due to sideslip has been discussed for infinitely long fuselages with circular and elliptical cross section. The aim of this work is to add rectangular cross sections and, primarily, to give a principle by which one can get practically usable contours through simple conformal mapping. In a few examples, the velocity field in the wing region and the induced flow p… more
Date: July 1958
Creator: Maruhn, K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude Performance of the Afterburner on the Iroquois Turbojet Engine. Coord. No. AF-P-6

Description: "The performance and operational characteristics of two afterburner configurations for the Iroquois turbojet engine were evaluated in an altitude test chamber over a range of afterburner equivalence ratios at afterburner-inlet pressures from 733 to 3186 pounds per square foot absolute. These conditions correspond to an altitude range from 38,700 to 66,800 feet at a flight Mach number of 1.5. The only difference between the two afterburner configurations was in the pattern of afterburner fuel in… more
Date: July 28, 1958
Creator: Groesbeck, Donald E. & Peters, Daniel J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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 possib… more
Date: July 1958
Creator: Pitts, William C. & Nielsen, Jack Norman
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Boundary-Layer-Transition Measurements in Full-Scale Flight

Description: Report presenting tests of the extent of laminar flow that can be obtained with practical wing-surface conditions. Chemical sublimation was used for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight. A method of continuous monitoring using heat temperature resistance gauges was also used on one wing.
Date: July 28, 1958
Creator: Banner, Richard D.; McTigue, John G. & Petty, Gilbert, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Boundary-Layer-Transition Measurements in Full-Scale Flight

Description: Chemical sublimation has been employed for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight at speeds near a Mach number of 2.0. The tests have shown that laminar flow can be obtained over extensive areas of the wing with practical wing-surface conditions. In addition to the flow visualization tests, a method of continuously monitoring the conditions of the boundary layer has been applied to flight testing, using heated temperature resistance gages… more
Date: July 28, 1958
Creator: Banner, Richard D.; McTigue, John G. & Petty, Gilbert, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Characteristics of the Langley 8-Foot Transonic Tunnel With Slotted Test Section

Description: "A large wind tunnel, approximately 8 feet in diameter, has been converted to transonic operation by means of slots in the boundary extending in the direction of flow. The usefulness of such a slotted wind tunnel, already known with respect to the reduction of the subsonic blockage interference and the production of continuously variable supersonic flows, has been augmented by devising a slot shape with which a supersonic test region with excellent flow quality could be produced. Experimental l… more
Date: July 3, 1958
Creator: Wright, Ray H.; Ritchie, Virgil S. & Pearson, Albin O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Chemical and physical factors affecting combustion in fuel-nitric acid systems

Description: Report presenting characteristic exhaust-velocity measurements made of the JP-4 fuel-red fuming nitric acid propellant combination in 40-pound-thrust rocket engines with various combustion-chamber lengths and diameters. The results are compared to those from previous studies and discussed in terms of a vaporization model of combustion. Results regarding the effect of UDMH, effect of water on performance of hydrocarbon fuels, effect of water on performance of hydrazine fuel, and some of the chem… more
Date: July 28, 1958
Creator: Baker, Louis, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Compressive Strength and Creep of 17-7 PH Stainless-Steel Plates at Elevated Temperatures

Description: Note presenting compressive strength test results from room temperature to 1000 degrees Fahrneheit and compressive creep test results from 700 to 1000 degrees Fahrenheit for plates of 17-7 PH stainless steel, Condition TH 1050, which were edge-supported in V-groove fixtures. The combinations of average stress, temperature, and time that produce given amounts of creep strain or failure are shown on master curves which facilitate interpolation of the test results.
Date: July 1958
Creator: Stein, Bland A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Dynamic stability of vehicles traversing ascending or descending paths through the atmosphere

Description: From Summary: "An analysis is given of the oscillatory motions of vehicles which traverse ascending and descending paths through the atmosphere at high speed. The specific case of a skip path is examined in detail, and this leads to a form of solution for the oscillatory motion which should recur over any trajectory. The distinguishing feature of this form is the appearance of the Bessel rather than the trigonometric function as the characteristic mode of oscillation."
Date: July 1958
Creator: Tobak, Murray & Allen, H. Julian
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Compressor-Inlet Water Injection on Engine and Afterburner Performance

Description: "A turbojet engine incorporating a conventional-type afterburner was operated over a range of afterburner pressure levels from 1000 to 2000 pounds per square foot absolute and a range of engine-inlet water-air ratios from 0 to 0.08. At each pressure level and water-air ratio, the afterburner fuel flow was varied from lean blowout to maximum burner-outlet temperature" (p. 1).
Date: July 22, 1958
Creator: Sivo, Joseph N.; Wanhainen, John P. & Jones, William L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Compressor-Inlet Water Injection on Engine and Afterburner Performance

Description: Report presenting testing of a turbojet engine incorporating a conventional-type afterburner over a range of afterburner pressure levels and engine-inlet water-air ratios. At each pressure level and water-air ratio, the afterburner fuel flow was varied from lean blowout to maximum burner-outlet temperature. Results regarding the effects of water vapor on engine performance, effects of water vapor on afterburner performance, and high Mach number performance with water injection are provided.
Date: July 22, 1958
Creator: Sivo, Joseph N.; Wanhainen, John P. & Jones, William L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Design Variables on Performance of Mach 4.0 Hydrogen Expansion Engines

Description: Memorandum presenting performance calculations for hypothetical hydrogen expansion engines in which only a small part of the engine airflow passes through the heat exchanger. The flight path was representative of those for long-range, high-speed aircraft. Results regarding the off-design operation and engine performance are provided.
Date: July 22, 1958
Creator: Dugan, James F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Design Variables on Performance of Mach 4.0 Hydrogen Expansion Engines

Description: Memorandum presenting performance calculations made for hypothetical hydrogen expansion engines in which only a small part of the engine airflow passes through the heat exchanger. The prescribed flight path was representative of those for long-range, high-speed aircraft. Results regarding the off-design operation and engine performance are provided.
Date: July 22, 1958
Creator: Dugan, James F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of favorable pressure gradients on transition for several bodies of revolution at Mach 3.12

Description: Report presenting experimental results relating to the effect of pressure gradient on the location of transition for several constant-pressure-gradient models an two power-profile models. Results regarding the local flow conditions, recovery-factor distributions, effect of unit Reynolds number, and effect of pressure gradient are provided.
Date: July 1958
Creator: Jack, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of leading-edge-flap deflection on the wing loads, load distributions , and flap hinge moments of the Douglas X-3 research airplane at transonic speeds

Description: Report presenting wing loads and load distributions obtained by differential-pressure measurements between the upper and lower surfaces of the wing of the Douglas X-3 research airplane with various leading-edge-flap deflections. The load and hinge-moment characteristics of the leading-edge flap are presented for a range of Mach numbers with and without flap deflection. Results regarding chordwise load distributions, wing-section and wing-panel characteristics, span load and pitching-moment dist… more
Date: July 15, 1958
Creator: Keener, Earl R.; McLeod, Norman J. & Taillon, Norman V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of screens in reducing distortion and diffusion length for a 'dump' diffuser at a Mach number of 3.85

Description: Report presenting an investigation of the effect of screens in a dump-type diffuser in the 2- by 2-foot supersonic wind tunnel at Mach number 3.85. Results of a slanted half screen of 0.41 solidity, positioned 0.263 inlet diameter from the cowl lip, are presented on a range basis, as this configuration allows for shortening of the subsonic diffuser.
Date: July 15, 1958
Creator: Wasserbauer, Joseph F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of Boattail Area Contouring and Simulated Turbojet Exhaust on the Loading and Fuselage-Tail Component Drag of a Twin-Engine Fighter-Type Airplane Model

Description: Effects of boattail area contouring and simulated turbojet exhaust on loading and fuselage-tail component drag of twin-engine fighter-type airplane model.
Date: July 14, 1958
Creator: Foss, Willard E., Jr.; Runckel, Jack F. & Lee, Edwin E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of Boattail Area Contouring and Simulated Turbojet Exhaust on the Loading and Fuselage-Tail Component Drag of a Twin-Engine Fighter-Type Airplane Model

Description: "An investigation of a twin-engine fighter-type airplane model has been conducted in the Langley 16-foot transonic tunnel to determine the effect on drag of a fuselage volume addition incorporating streamline contouring and more extensive boattailing of the engine shrouds. The effect of hot exhausts from the turbojet engines was simulated with hydrogen peroxide gas generators using scaled nonafterburning engine nozzles. Afterbody pressure distributions, base drag coefficients, and forces on the… more
Date: July 14, 1958
Creator: Foss, Willard E., Jr.; Runckel, Jack F. & Lee, Edwin E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Boundary-Layer Displacement and Leading-Edge Bluntness on Pressure Distribution, Skin Friction, and Heat Transfer of Bodies at Hypersonic Speeds

Description: "Results are presented of an investigation to determine the effect of boundary-layer displacement and leading-edge bluntness on surfaces in hypersonic flow. The presence of the boundary layer and the blunt leading edge induce pressure gradients which in turn affect the skin friction and heat transfer to the surface. Methods for predicting these phenomena on two-dimensional surfaces are given and a brief review of recent three-dimensional results is presented" (p. 1).
Date: July 1958
Creator: Bertram, Mitchel H. & Henderson, Arthur, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of canards on airplane performance and stability

Description: Report presenting an investigation on canard airplane configurations in preference to a trailing-edge flap or tail control. Wide ranges in control plan form, size, and position and in wing plan form were found. Interference effects between the canard and other configuration components were not serious, and those that might be can be reduced by rearrangement of the vertical tail.
Date: July 7, 1958
Creator: Hall, Charles F. & Boyd, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of fabrication-type roughness on turbulent skin friction at supersonic speeds

Description: Report presenting an investigation of the effects of fabrication-type surface roughness on turbulent skin-friction drag at supersonic speeds. It was found that fabrication of the thin-skin constructions could be done sufficiently well in practice so as to cause no increase in drag over the smooth body; however, the juncture-type roughnesses produced significant increases in drag as compared with the smooth body. Results indicated that increasing the unit Reynolds number has a detrimental effect… more
Date: July 1958
Creator: Czarnecki, K. R.; Sevier, John R., Jr. & Carmel, Melvin M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of fixing transition on the transonic aerodynamic characteristics of a wing-body configuration at Reynolds numbers from 2.4 to 12 million

Description: Report presenting a wind-tunnel investigation of the effects of fixing boundary-layer transition with wires on the aerodynamic characteristics of a wing-body configuration at a range of Mach numbers. The model consisted of an aspect-ratio-3 trapezoidal wing with a 3-percent-thick biconvex section in combination with a Sears-Haack body of revolution. Results regarding lift characteristics, pitching-moment characteristics, and drag characteristics are provided.
Date: July 1958
Creator: Hunton, Lynn W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Nose Shape and Spray Control Strips on Emergence and Planing Spray of Hydro-Ski Models

Description: Report presenting the emergence- and planing-spray characteristics of flat-bottom surfaces representing hydro-skis with various bow shapes and deflectors. The most favorable emergence spray was obtained with a bow of triangular plan form and sharp profile. Results regarding practical design considerations are also provided.
Date: July 1958
Creator: McGehee, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of vertical location of the wing and horizontal tail on the static lateral and directional stability of a trapezoidal-wing airplane model at Mach numbers of 1.41 and 2.01

Description: Report presenting an investigation to determine the effects of vertical location of the wing and horizontal tail on the static lateral and directional stability at various combined angles of attack and sideslip for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The configurations investigated included a high-wing, midwing, and low-wing arrangement in combination with horizontal-tail positions varying from a location of 0.208 wing semispan below to 0.556 semispan above the… more
Date: July 9, 1958
Creator: Robinson, Ross B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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