National Advisory Committee for Aeronautics (NACA) - 766 Matching Results

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Investigations toward simplification of missile control systems

Description: Paper presenting three ideas regarding potential simplifications of missile-control systems in order to make them more reliable without sacrificing system performance. The three methods presented include an autorotating-vane spoiler, a bellows flap, and free controls. All are based on modified airplane control systems.
Date: November 12, 1953
Creator: Curfman, Howard J., Jr.; Strass, H. Kurt & Crane, Harold L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings

Description: Report presenting an investigation of an 18-foot-radius helicopter rotor powered by tip-mounted ramjet engines in the helicopter test tower. The engine performance is compared with the performance determined in a previous investigation of a 9-foot-radius rotor with the same engines at similar speeds but with twice the centrifugal forces. Results regarding the propulsive characteristics, minimum specific fuel consumption and corresponding propulsive thrust, and operational characteristics are pr… more
Date: October 7, 1953
Creator: Radin, Edward J. & Carpenter, Paul J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation to Determine the Horizontal- and Vertical-Tail Contributions to the Static Lateral Stability Characteristics of a Complete-Model Swept-Wing Configuration at High Subsonic Speeds

Description: Results regarding an investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. Generally, Mach number effects within the range studied and wing effects on the tail contribution were small and the overall trends of the data of the present investigation agreed with those which have been established at low speeds.
Date: July 10, 1953
Creator: Wiggins, James W.; Kuhn, Richard E. & Fournier, Paul G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Rocket-Model Investigation to Determine the Hinge-Moment and Normal-Force Properties of a Full-Span, Constant-Chord, Partially Balanced Trailing-Edge Control on a 60 Degree Clipped Delta Wing Between Mach Numbers of 0.50 and 1.26

Description: Report presenting a free-flight investigation of a rocket-powered research model to determine the hinge-moment and normal-force characteristics of a trailing-edge control on a delta wing between Mach numbers of 0.50 and 1.26. The hinge-line location of 40 percent control chord satisfactorily reduced the high hinge moments associated with plain flap-type controls. Results regarding hinge moments and normal force are provided.
Date: October 30, 1953
Creator: Martz, C. William & Goslee, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel

Description: Report presenting an investigation to study the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel. The results indicated that the large increases in allowable center-of-gravity travel could be obtained using the devices. Results regarding the basic aerodynamic data, effect of tail configuration on the allowable center-of-gravity travel, and a comparison of measured and predicted values of the allowa… more
Date: January 21, 1953
Creator: Johnson, Joseph L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An experimental study of five annular air inlet configurations at subsonic and transonic speeds

Description: Report presenting an investigation of an NACA 1-80-100 nose inlet fitted alternately with an elliptical, a parabolic, a 14 degree-inch conical, and a 22 degree-inch conical central body at subsonic and transonic speeds in the 8-foot transonic tunnel. Drag, surface-pressure, and pressure-recovery measurements were obtained at 0 degrees angle of attack through a range of Mach numbers. Results regarding tunnel boundary interference, surface-pressure distribution, external drag, pressure recovery, … more
Date: August 19, 1953
Creator: Pendley, Robert E.; Milillo, Joseph R.; Fleming, Frank F. & Bryan, Carroll R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculated Lateral Frequency Response and Lateral Oscillatory Characteristics for Several High-Speed Airplanes in Various Flight Conditions

Description: "Calculations have been made to determine the effects of Mach number and altitude on the lateral frequency response, the lateral response to a lateral sinusoidal gust distribution, and the period and damping of the lateral oscillation for the North American F-86A, Grumman F9F-2, Republic F-84, Douglas D-558-II, and Bell X-1 airplanes without autopilots. Aeroelastic and unsteady lift effects have not been included in the calculations and may have a large effect on the results for certain flight … more
Date: December 10, 1953
Creator: Jaquet, Byron M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental and theoretical investigation of rotating-stall characteristics of single-stage axial-flow compressor with hub-tip ratio of 0.76

Description: Report presenting the overall performance and rotating stall characteristics of a single-stage compressor with a hub-tip ratio of 0.76 and a symmetrical velocity diagram over a wide range of weight flow for several different design speed percentages. No discontinuities in performance were noted at an operating condition. Results regarding the overall performance, types of rotating stall observed, circumferential extent of stall zones, flow fluctuations incited by rotating stall, rotating-stall … more
Date: November 30, 1953
Creator: Graham, Robert W. & Prian, Vasily D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation at Transonic Speeds of the Effects of Fences, Drooped Nose, and Vortex Generators on the Aerodynamic Characteristics of a Wing-Fuselage Combination Having a 6-Percent-Thick, 45 Degree Sweptback Wing

Description: Report presenting an investigation at transonic speeds to determine the effects of fences, drooped nose, combination fences and drooped nose, and vortex generators on a 45 degree sweptback wing-fuselage combination. The purpose of undertaking this investigation was due to the pitch-up tendency that results from leading-edge vortex-type flow on thin sweptback wings. The data for each component and their interaction with one another is also provided.
Date: March 31, 1953
Creator: Hieser, Gerald
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Drawbar Upstream Location on Air Velocity Distribution at the Inlet Face of Reactor Segment Designed by the General Electric Company

Description: The results of flow tests on a drawbar for the General Electric reactor segment test in the MTR are reported. The drawbar is a T-shaped obstruction located as close to the upstream face of the reactor test segment as possible without serious flow distortion ; the drawbar is required for instrumentation leads and segment insertion and removal in the MTR. The effect of drawbar upstream distance on velocity distribution across the segment face is evaluated for several Reynolds numbers.
Date: January 1953
Creator: Nagey, T. F. & Sams, E. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of diffuser design, diffuser-exit velocity profile and fuel distribution on altitude performance of several afterburner configurations

Description: "An investigation was conducted in the NACA Lewis altitude wind tunnel to improve the altitude performance and operational characteristics of an afterburner primarily by modifying the diffuser-exit velocity profile by changes in diffuser design and by changing the fuel distribution and the flame holder. Twenty configurations, consisting of combinations of six diffuser geometries, six flame-holder types, and twelve fuel systems, were investigated. Data were obtained over a range of afterburner f… more
Date: July 9, 1953
Creator: Conrad, E. William; Schultz, Frederick W. & Usow, Karl H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a Ram-Jet-Powered Helicopter Rotor on the Langley Helicopter Test Tower

Description: Report discussing tests on a helicopter rotor powered by ram-jet engines located at the rotor blade tips. Information about the basic hovering characteristics of the rotor and the propulsive characteristics of the ram-jet engine were obtained over a range of speeds and fuel rates. Results were also obtained in the power-off condition and with the engines removed.
Date: June 3, 1953
Creator: Carpenter, Paul J. & Radin, Edward J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of rotor-and stator-blade modifications on surge performance of an 11-stage axial-flow compressor 1: original production compressor of XJ40-WE-6 engine

Description: Report presenting an investigation to increase the compressor surge-limit pressure ratio of the XJ40-WE-6 turbojet engine at high equivalent speeds. The two compressor modifications investigated included twisting rotor blades to change blade section angles and inserting new stator diaphragms with different blade angles. Results regarding the effect of surge limit on engine performance, performance map of original compressor with mixer, effect of blade modifications on surge line, effect of mixe… more
Date: May 20, 1953
Creator: Finger, Harold B.; Essig, Robert H. & Conrad, E. William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Matched performance characteristics of a 16-stage axial-flow compressor and a 3-stage turbine

Description: Report presenting component performance data for one modification of a 16-stage compressor and a 3-stage turbine to determine the matched performance characteristics of an engine with those components. The compressor surge line and infinite exhaust-nozzle-area equilibrium operating line restricted the region of matched compressor-turbine operation. Results regarding the engine operation with modified compressor and three-stage turbine, effect of leakage on engine operation, component efficienci… more
Date: April 28, 1953
Creator: Rebeske, John J., Jr. & Dugan, James F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An investigation of some factors affecting the drag of relatively large nonlifting bodies of revolution in a slotted transonic wind tunnel

Description: Report presenting an investigation to study some factors affecting the drag of relatively large nonlifting bodies of revolution at transonic speeds in the 8-foot transonic tunnel. Drag and surface pressure measurements were made for two geometrically similar bodies of revolution of 8-inch and 4-inch maximum diameter at zero angle of attack through a range of Mach numbers.
Date: January 15, 1953
Creator: Pendley, Robert E. & Bryan, Carroll R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of the turbojet engine for propulsion of supersonic fighter airplanes

Description: An analytical investigation was made of two supersonic interceptor type airplanes to determine the most desirable turbojet engine characteristics for this application The airplanes were designed differently primarily because of the amount of subsonic flight incorporated in the flight plan--one flight having none and the other, a cruise radius of 400 nautical miles. Several power plant design variables were varied independently to determine the effect of changes in each parameter on airplane per… more
Date: October 26, 1953
Creator: Gabriel, David S.; Krebs, Richard P.; Wilcox, E. Clinton & Koutz, Stanley L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Vertical-Tail Loads Measured During a Flight Investigation on a Jet-Powered Bomber Airplane

Description: Report presenting results of a flight investigation using a jet-powered bomber airplane to determine the vertical tail loads. Strain-gage measurements were made of the fin and rudder loads in abrupt rudder kicks and in gradual sideslip maneuvers.
Date: May 1, 1953
Creator: Cooney, T. V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Engine and Control Limits on Steady-State and Transient Performance of Turbojet Engine With Variable-Area Exhaust Nozzle

Description: Memorandum presenting steady-state and transient characteristics of the J34-WE-32 turbojet engine with electronic power regulator as obtained in the altitude wind tunnel to determine the effects of engine and control limits on the performance. Limits on the fuel valve and exhaust nozzle area influence any schedule of speed and temperature. Results regarding the effect of limits on operating schedule, effect of altitude on safe operating range, effect of minimum fuel flow settings on transient p… more
Date: January 16, 1953
Creator: Vasu, George & Hinde, William L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude performance characteristics of the J47-25 turbojet engine: data presentation

Description: From Introduction: "An investigation was conducted in an NACA Lewis altitude chamber to determine the altitude performance characteristics of a J47-25 axial-flow turbojet engine over a range of engine-inlet Reynolds number indices corresponding to altitudes from 18,000 to 54,000 feet and flight Mach numbers from 0.50 to 1.10. Reynolds number at a given corrected engine speed and is a function only of engine-inlet total pressure and temperature, was used instead of various set altitudes and flig… more
Date: September 29, 1953
Creator: Renas, Paul E. & Jansen, Emmert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Some fundamental aspects of nitric acid oxidants for rocket applications

Description: From Summary: "The literature pertaining to the preparation, physical properties, corrosiveness, thermal stability, constitution, and analysis of various nitric acids is reviewed primarily with respect to their use as rocket oxidants. Conflicting data are evaluated and recommendations for additional experimental work are indicated. Reactions of nitric acid which could occur during the starting and steady-stage phases of rocket operation are discussed and probable mechanisms are selected on the … more
Date: January 14, 1953
Creator: Ladanyi, Dezso J.; Miller, Riley O.; Karo, Wolf & Feiler, Charles E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Spark ignition of flowing gases III : effect of turbulence promoter on energy required to ignite a propane-air mixture

Description: Report presenting an investigation to determine the effect of turbulence generated by different sizes of wire grid on the minimum spark-ignition energy of a flowing propane-air mixture. Gas-stream velocity, size of turbulence promoter, and distance from the promoter plate to the electrodes on minimum ignition energy were evaluated and the effects are shown in figures.
Date: January 14, 1953
Creator: Swett, Clyde C., Jr. & Donlon, Richard H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical comparison of turbine-blade cooling systems designed for a turbojet engine operating at supersonic speed and high altitude 1: liquid-cooling systems

Description: Report presenting an investigation of the influence of high-altitude supersonic flight on the operation and effectiveness of turbine-blade liquid-cooling systems for application in turbojet engines in guided missiles and in supersonic aircraft. The problems encountered in liquid-cooling systems were investigated with reference to several specific designs for alternate heat-rejection mediums.
Date: February 20, 1953
Creator: Schramm, Wilson B.; Nachtigall, Alfred J. & Arne, Vernon L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-speed wind-tunnel investigation of a thin 60 degree delta wing with double slotted, single slotted, plain, and split flaps

Description: Report presenting a low-speed wind-tunnel investigation to determine the longitudinal aerodynamic characteristics of a thin delta wing equipped with various arrangements of double slotted, single slotted, plain, and split flaps. The wing was a flat plate with beveled leading and trailing edges and had a maximum thickness ratio of 0.045, and 60 degrees sweepback of the leading edge.
Date: January 6, 1953
Creator: Riebe, John M. & MacLeod, Richard G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical comparison of turbine-blade cooling systems designed for a turbojet engine operating at supersonic speed and high altitude 2: air-cooling systems

Description: Report presenting an investigation of the influence of high-altitude supersonic flight on the operation and effectiveness of turbine-blade air- and liquid-cooling systems for turbojet application in guided missiles and supersonic interceptor aircraft. Results regarding the coolant passage heat-transfer-coefficients, nonrefrigerated air-cooling-system characteristics, and refrigerated-air-cooling-system characteristics are provided.
Date: February 19, 1953
Creator: Schramm, Wilson B.; Arne, Vernon L. & Nachtigall, Alfred J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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