National Advisory Committee for Aeronautics (NACA) - 209 Matching Results

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A study of the motion and aerodynamic heating of ballistic missiles entering the earth's atmosphere at high supersonic speeds

Description: From Summary: "A simplified analysis of the velocity and deceleration history of ballistic missiles entering the earth's atmosphere at high supersonic speeds is presented. The results of this motion analysis are employed to indicate means available to the designer for minimizing aerodynamic heating. The heating problem considered involves not only the total heat transferred to a missile by convection, but also the maximum average and local time rates of convective heat transfer."
Date: April 28, 1953
Creator: Allen, H. Julian & Eggers, A. J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of a blunt-lip side inlet with ramp bleed, bypass, and a long constant-area duct ahead of the engine : Mach number 0.66 and 1.5 to 2.1

Description: Unsteady shock-induced separation of the ramp boundary layer was reduced and stabilized more effectively by external perforations than by external or internal slots. At Mach 2.0 peak total-pressure recovery was increased from 0.802 to 0.89 and stable mass-flow range was increased 185 percent over that for the solid ramp. Peak pressure recovery occurred just before instability. The 7 and one-third-diameter duct ahead of the engine reduced large total-pressure distortions but was not as successfu… more
Date: December 28, 1956
Creator: Allen, John L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of a Blunt-lip Side Inlet With Ramp Bleed, Bypass, and a Long Constant-area Duct Ahead of the Engine- Mach Numbers 0.66 and 1.5 to 2.1

Description: Report presenting the performance of a side inlet with a fixed 12 degree two-dimensional compression surface for a range of Mach numbers, angles of attack, and yaw. The effects of several methods of compression-surface boundary-layer removal were investigated as well as a solid ramp.
Date: December 28, 1956
Creator: Allen, John L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measurement and Calculation of Blade Torsional Deflection of Three Supersonic-Type Propellers

Description: Report presenting an investigation to determine the blade torsional deflection of three supersonic-type propellers at various operating conditions. Blade-torsional deflection was found to produce appreciable results that can be predicted by theory with good accuracy. Results regarding the efficiency, thrust coefficient, and power coefficient are provided.
Date: May 28, 1954
Creator: Allis, Arthur E. & Foss, Willard E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-flight Investigation at Transonic Speeds of the Stability Characteristics of a Tailless Missile Configuration Having a 45 Deg Sweptback Wing of Aspect Ratio 4

Description: Free flight test of tailless missile configuration with 45-deg sweptback wing of aspect ratio 4 - stability at transonic speeds. The longitudinal flexible-wing results indicated a gradual transonic trim change a lift-curve slope comparable with that for the same configuration with a wing of aspect ratio 5.5. Results regarding trim characteristics, lift and longitudinal stability, and side-force and lateral stability are provided.
Date: August 28, 1956
Creator: Arbic, Richard G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Flight Investigation at Transonic Speeds of the Stability Characteristics of a Tailless Missile Configuration Having a 45 Degree Sweptback Wing of Aspect Ratio 4

Description: Memorandum presenting a flight test of a long-range missile configuration with a 45 degree sweptback wing of aspect ratio 4 conducted at a range of Mach and Reynolds numbers. The longitudinal flexible-wing results indicated a gradual transonic trim change and a lift-curve slope comparable with that for the same configuration with a wing of aspect ratio 5.5.
Date: August 28, 1956
Creator: Arbic, Richard G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Longitudinal Stability and Control Characteristics as Determined by the Rocket-Model Technique for an Inline, Cruciform, Canard Missile Configuration With a Low-Aspect-Ratio Wing Having Trailing-Edge Flap Controls for a Mach Number Range of 0.7 to 1.

Description: Report presenting tests of two models of an inline, cruciform, canard missile configuration with a low-aspect-ratio wing equipped with flap-type controls to determine the missile's longitudinal aerodynamic characteristics. Stability derivatives and control and drag characteristics are presented for a range of Mach numbers.
Date: September 28, 1955
Creator: Baber, Hal T., Jr. & Moul, Martin T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Longitudinal Stability and Control Characteristics as Determined by the Rocket-Model Technique for an Inline, Cruciform, Canard Missile Configuration With a Low-Aspect-Ratio Wing Having Trailing-Edge Flap Controls for a Mach Number Range of 0.7 to 1.8

Description: Report presenting testing of two full-scale models of an inline, cruciform, canard missile configuration with a low-aspect-ratio wing equipped with flap-type controls to determine the missile's longitudinal aerodynamic characteristics. Stability derivatives and control and drag characteristics are provided.
Date: September 28, 1955
Creator: Baber, Hal T., Jr. & Moul, Martin T.
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
open access

Some Measurements of the Buffet Region of a Swept-Wing Research Airplane During Flight to Supersonic Mach Numbers

Description: Report presenting measurements of the intensity of buffeting experienced by the Douglas D-558-II research airplane at a range of Mach numbers. Buffeting was encountered at both subsonic and supersonic Mach numbers and the intensity of the buffeting varied with Mach number and airplane normal-force coefficient.
Date: May 28, 1953
Creator: Baker, Thomas F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Measurements at Transonic Speeds of the Buffeting Characteristics of the XF-92A Delta-Wing Research Airplane

Description: Report presenting testing on a 60 degree delta-wing XF-92A airplane at a variety of Mach numbers to obtain measurements regarding buffet-induced fluctuations in normal acceleration and of fluctuations in structural shear load of the left wing. The altitudes tested ranged from 25,000 to 38,000 feet. Results regarding the buffet boundary, wing flow conditions, buffet frequencies, buffet intensities, and a comparison to buffeting of other airplanes are provided.
Date: April 28, 1955
Creator: Baker, Thomas F. & Johnson, Wallace E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Application of wing-body theory to drag reduction at low supersonic speeds

Description: Report presenting a method for extending to higher Mach numbers the region of low drag attainable for wing-body combinations by the use of the transonic area rule. To a good approximation, the drag depends only on the longitudinal distributions of area and moments of area about the vertical plane of symmetry parallel to the free-stream direction. The experimental results confirm the theory in that the zero-lift wave drag of a wing-body configuration over a range of low supersonic Mach numbers.
Date: January 28, 1955
Creator: Baldwin, Barrett S., Jr. & Dickey, Robert R.
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
open access

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
open access

Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine 12: Cooling Effectiveness of a Blade With an Insert and With Fins Made of a Continuous Corrugated Sheet

Description: Memorandum presenting an investigation conducted in a modified turbojet engine to determine the cooling effectiveness of an air-cooled turbine-rotor blade employing a corrugated metal sheet brazed to the inner surface of the blade shell to increase the internal heat-transfer area. The corrugated fin blade had a lower integrated average wall temperature at the section investigated than the more promising shell-supported blade types previously investigated. Results regarding the temperature distr… more
Date: August 28, 1952
Creator: Bartoo, Edward R. & Clure, John L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Internal Performance of Two-Dimensional Wedge Exhaust Nozzles

Description: Memorandum presenting an experimental investigation of four rectangular-throat two-dimensional wedge exhaust nozzles. Three of the nozzles were designed to conform to Prandtl-Meyer streamlines for pressure ratios of 5, 10, and 24, and a fourth, arbitrarily contoured, with a length less than that required for isentropic expansion, was designed for a pressure ratio of about 9.
Date: February 28, 1957
Creator: Beale, William T. & Povolny, John H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of J-33-A-21 and J-33-A-23 Compressors With and Without Water Injection

Description: "In an investigation of the J-33-A-21 and the J-33-A-23 compressors with and without water injection, it was discovered that the compressors reacted differently to water injection although they were physically similar. An analysis of the effect of water injection on compressor performance and the consequent effect on matching of the compressor and turbine components in the turbojet engine was made. The analysis of component matching is based on a turbine flow function defined as the product of … more
Date: January 28, 1948
Creator: Beede, William L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flame Quenching by a Variable-Width Rectangular-Slot Burner as a Function of Pressure for Various Propane-Oxygen-Nitrogen Mixtures

Description: "Flame quenching by a variable-width rectangular-slot burner as a function of pressure for various propane-oxygen-nitrogen mixtures was investigated. It was found that for cold gas temperatures of 27 degrees C, pressures of 0.1 or 1.0 atmosphere, and volumetric oxygen reactions of the oxidant of 0.17, 0.21, 0.30, 0.50, and 0.70, the relation between pressure p and quenching distance d is approximately given by d (unity) p (superscript -r) with r = 1, for equivalence ratios approximately equal t… more
Date: January 28, 1954
Creator: Berlad, Abraham L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the McDonnell XP-88 Airplane with a Vee Tail

Description: "An investigation of the spin and recovery characteristics of a 1/24-scale model of the McDonnell XP-88 airplane has been conducted in the Langley 20-ft free-spinning tunnel. Results of tests with a conventional tail have been previously reported; the results presented herein are for the model with a vee tail installed. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model. In the normal loading were determined" (p. 1).
Date: November 28, 1947
Creator: Berman, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A transonic wind-tunnel investigation of the longitudinal stability and control characteristics of a 0.09-scale model of the Bell X-5 research airplane and comparison with flight

Description: Report presenting an investigation conducted in the 8-foot transonic tunnel to determine the longitudinal stability and control characteristics of a 0.09-scale model of the Bell X-5 research airplane. Lift, drag, pitching-moment, elevator hinge-moment, and pressure-distribution results are presented for a range of Mach and Reynolds numbers. Results regarding lift and drag characteristics, longitudinal stability and control characteristics, dynamic-response characteristics, elevator hinge-moment… more
Date: October 28, 1953
Creator: Bielat, Ralph P. & Campbell, George S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The design of fins for air-cooled cylinders

Description: From Summary: "An analysis was made to determine the proportions of fins made of aluminum, copper, magnesium, and steel necessary to dissipate maximum quantities of heat for different fin widths, fin weights, and air-flow conditions. The analysis also concerns the determination of the optimum fin proportions when specified limits are placed on the fin dimensions. The calculation of the heat flow in the fins is based on experimentally verified, theoretical equations. The surface heat-transfer co… more
Date: June 28, 1939
Creator: Biermann, Arnold E. & Ellerbrock, Herman H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Metal-Bonding Adhesives for High-Temperature Service

Description: Report presenting the results of an investigation to develop a metal-bonding adhesive with improved heat-resistant properties. The most promising results were obtained with a formulation of a phenol resin and epoxy resin with certain heat stabilizers and catalysts. Results regarding the strength of bonds, resistance of adhesives to aging, and heat-resistant properties are provided.
Date: July 28, 1955
Creator: Black, John M. & Blomquist, R. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Results of a Power-on Flight of a 1/10-Scale Rocket-Propelled Model of the Convair XF2Y-1 Airplane at a Mach Number of 1.53

Description: Report discussing testing on a scale model of the Convair XF2Y-1 airplane with solid-fuel rocket motors that simulate full-scale turbojet-engine characteristics at a height of 35,000 feet with full afterburning at Mach number 1.53. The model was found to have dynamic lateral instability, but these results were not likely to be found in a full-scale airplane. Information about the pitching moment, directional stability, lift-curve slope, and drag coefficients is provided.
Date: September 28, 1953
Creator: Bland, William M., Jr. & Nelson, Robert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of wing-tip turrets on the aerodynamic characteristics of a typical bomber-wing model

Description: Report presenting wind-tunnel tests up to a Mach number of 0.85 to determine the effects of wing-tip gun turrets on the aerodynamic characteristics of a typical bomber-wing model. Lift, drag, and pitching-moment data are presented for the wing alone; for the wing with the turrets in the clean condition; and for the wing and the turrets with guns and sighting equipment. The turrets had negligible effect on the lift and pitching-moment characteristics of the wing.
Date: March 28, 1949
Creator: Boddy, Lee E. & Sutton, Fred B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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