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Free Flight Investigation at Transonic Speeds of the Power-on Characteristics Including Some Effects of Sonic Propulsive Jets of a Four Engine Delta Wing Configuration

Description: Report discussing a model of a delta-wing configuration with four engines mounted two to a nacelle below the wing that was tested a variety of Mach numbers and Reynolds numbers. The wing static-pressure coefficients, wing pressure coefficients, and lift coefficient of different configurations are described.
Date: August 16, 1957
Creator: Falanga, Ralph A. & Judd, Joseph H.
Partner: UNT Libraries Government Documents Department
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Performance of Inconel 550 Turbine Blades in a Turbojet Engine and Effects of Different Forging Temperatures and Heat Treatments

Description: Report presenting an investigation to determine the effects of forging at 1950 degrees and 2150 degrees Fahrenheit as well as the effects of several heat treatments on the performance of Inconel 550 in a turbojet engine. Differences in engine performance of the different turbine blades could not be associated with consistent differences in microstructure or grain size. Results regarding blade performance, blade elongation during engine operation, microstructure of as-heat-treated blades, grain … more
Date: August 16, 1955
Creator: Gyorgak, C. A.; Johnston, J. R. & Weeton, J. W.
Partner: UNT Libraries Government Documents Department
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Preliminary Report on Experimental Investigation of Engine Dynamics and Controls for a 48-Inch Ram-Jet Engine

Description: Engine dynamics and controls data are presented for a ram-jet engine which was operated in a free-jet facility at a Mach number of 2.76 and altitudes from 68,000 to 82,000 feet. The predominant engine dynamic characteristics was dead time, with values ranging from 0.018 to 0.053 sec. The control systems were designed to hold a constant ratio of a diffuser static pressure to an inlet-cone reference static pressure.
Date: March 16, 1956
Creator: Vasu, George; Hart, Clint E. & Dunbar, William R.
Partner: UNT Libraries Government Documents Department
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Investigation of impulse-type supersonic compressor with hub-tip ratio of 0.6 and turning to axial direction 2: stage performance with three different sets of stators

Description: Report presenting an impulse-type supersonic compressor designed for turning to the axial direction that was tested in air with three different sets of stator blades at eight angle settings.
Date: August 16, 1955
Creator: Wilcox, Ward W.
Partner: UNT Libraries Government Documents Department
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A special method for finding body distortions that reduce the wave drag of wing and body combinations at supersonic speeds

Description: For a given wing and supersonic Mach number, the problem of shaping an adjoining fuselage so that the combination will have a low wave drag is considered. Only fuselages that can be simulated by singularities (multipoles) distributed along the body axis are studied. However, the optimum variations of such singularities are completely specified in terms of the given wing geometry. An application is made to an elliptic wing having a biconvex section, a thickness-chord ratio equal to 0.05 at the r… more
Date: May 16, 1956
Creator: Lomax, Harvard & Heaslet, Max A.
Partner: UNT Libraries Government Documents Department
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An investigation of the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA RM-10) at a Mach number of 1.61

Description: Report presents the results of an investigation conducted to determine the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA rm-10 without fins) at Mach number of 1.61 and over a Reynolds number range from 2.5 x 10(6) to 35 x 10(6). The maximum cooling of the model used in these tests corresponded to a temperature ratio (ratio of model-surface temperature to free-stream temperature) of 1.12, a value somewhat higher than the theoretical value required … more
Date: February 16, 1953
Creator: Czarnecki, K. R. & Sinclair, Archibald R.
Partner: UNT Libraries Government Documents Department
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Determination of Rate, Area, and Distribution of Impingement of Waterdrops on Various Airfoils From Trajectories Obtained on the Differential Analyzer

Description: "The trajectories of waterdrops in air flowing over airfoils are determined for three airfoil - angle-of-attack combinations using the differential analyzer to solve the differential equations of motion of the waterdrops. From these trajectories the rate of water impingement, the area of impingement, and the distribution of impingement are determined as functions of two dimensionless moduli. Comparisons are made of the rate of water impingement on these airfoils and the rate of water impingemen… more
Date: February 16, 1949
Creator: Guibert, A. G.; Janssen, E. & Robbins, W. M.
Partner: UNT Libraries Government Documents Department
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Static Lateral and Directional Stability and Control Characteristics of a Revised 1/22-Scale Model of the Republic F-105 Airplane at Mach Numbers of 1.41 and 2.01

Description: Report discussing testing to determine the static lateral and directional stability and control characteristics of a model of the Republic F-105 airplane. The effects of various vertical tails and ventral fins, wing-tip fences, a canopy fin, fuselage nose shape, external stores, and deflection of horizontal tail, spoiler, and rudder were explored.
Date: October 16, 1956
Creator: Robinson, Ross B. & Foster, Gerald V.
Partner: UNT Libraries Government Documents Department
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Analysis of pressure distributions for a series of tip and trailing-edge controls on a 60 deg wing at Mach numbers of 1.61 and 2.01

Description: Report presenting an investigation at Mach numbers of 1.61 and 2.01 to determine the pressure distributions for a series of 20 controls on a 60 degree delta wing. Tests occurred at a range of angles of attack and control deflections. Results regarding basic pressure distributions, comparison of experimental and theoretical results, and experimental comparisons are provided.
Date: May 16, 1958
Creator: Lord, Douglas R. & Czarnecki, K. R.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of air-side performance of liquid-metal to air heat exhangers

Description: Report describing an experiment to obtain heat-transfer and pressure-drop data for the air side of a liquid-metal to air, shell-and-tube heat exchanger. Testing was conducted in a 500 kilowatt facility using sodium as the shell-side heating fluid. Results regarding the shell-and-tube heat exchanger and finned-tube heat exchanger friction factor are provided.
Date: March 16, 1956
Creator: Gedeon, Louis; Conant, Charles W. & Kaufman, Samuel J.
Partner: UNT Libraries Government Documents Department
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Characteristics of a Hydraulic Control Determined from Transient Data Obtained with a Turbojet Engine at Altitude

Description: Memorandum presenting characteristics of a hydraulic control as determined by analyzing transient data obtained with a turbojet engine operating in the altitude wind tunnel. The excellent overall performance of the speed control is attributed to the elimination of large lags in the control system, thereby permitting the use of relatively high loop gains while still maintaining satisfactory damping in transients. Some information regarding the frequency-response analysis of speed control, simula… more
Date: June 16, 1954
Creator: Vasu, George; Hinde, William L. & Craig, R. T.
Partner: UNT Libraries Government Documents Department
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Requirements for Auxiliary Stiffeners Attached to Panels Under Combined Compression and Shear

Description: "Panels of aluminum alloy sheets, framed by side and end stiffeners, were subjected to combined loading by means of offset knife edges applying loads to top and bottom end plates with reacting forces against the end plates supplied by laterally acting rollers. The test specimens were 17S-T aluminum alloy shoots 0.040 inch thick in panels of 10-inch width and three different lengths (approximately 10, 26, and 30 inch). Data were obtained for the bowing of transverse and longitudinal ribs of rect… more
Date: September 16, 1943
Creator: Scott, Merit & Weber, Robert L.
Partner: UNT Libraries Government Documents Department
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A Method for Estimating the Components of Lift of Wing-Body Combinations at Supersonic Speeds

Description: Report presenting the lift of wing-body combinations at supersonic speeds as obtained by means of an approximate linearized-theory analysis involving an assumption concerning the geometry of the body. A comparison with several groups of data is provided to show the accuracy of the method.
Date: September 16, 1952
Creator: Tucker, Warren A.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of effects of simulated nacelles and wing-root freedoms on supersonic flutter characteristics of a cambered, modified, swept, tapered wing

Description: Report presenting an investigation to determine the effects of simulated engine nacelles and wing-root freedoms on the flutter characteristics of a cambered, modified, swept, tapered, semispan wing through a range of Mach numbers. Wings were tested with and without nacelles and with the model restrained, free to roll, and free to translate in the vertical direction. Results regarding the effect of nacelles, flutter boundary, and effect of wing-mount freedom are provided.
Date: October 16, 1957
Creator: Hanson, Perry W.
Partner: UNT Libraries Government Documents Department
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A Flight and Analog Study of the Effect of Elevating the Radar-Boresight Axis Upon Stability and Tracking Performance of an Automatically Controlled Interceptor

Description: Report presenting flight and analog-simulator tests with a prototype automatic interceptor in order to study the effects of elevating the radar-boresight axis on the stability and tracking performance of the system. Results regarding effects of interceptor rolling motion upon tracking errors, similarity of flight results and analog-computer results, effect of elevating the radar-boresight axis upon stability, effect of elevating the radar-boresight axis upon the required bank-angle feedback, an… more
Date: October 16, 1957
Creator: Cheatham, Donald C. & Mathews, Charles W.
Partner: UNT Libraries Government Documents Department
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Preliminary Analysis of Performance of Turbojet Engines Used as Pumps for Boundary-Layer Control

Description: Memorandum presenting a determination of the effects on engine performance of using turbojet engines for boundary-layer control by suction at the engine inlet or by bleeding air from the compressor outlet for three current production engines. Results regarding bleed, suction, and variable-area turbine are provided.
Date: August 16, 1955
Creator: Conrad, E. William
Partner: UNT Libraries Government Documents Department
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Determination of rate, area, and distribution of impingement of of waterdrops on various airfoils from trajectories obtained on the differential analyzer

Description: From Summary: "The trajectories of waterdrops in air flowing over airfoils are determined for three airfoil-angle-of-attack combinations using the differential analyzer to solve the differential equations of motion of the waterdrops. From these trajectories the rate of water impingement, the area of impingement, and the distribution of impingement are determined as functions of two dimensionless moduli. Comparisons are made of the rate of water impingement on these airfoils and the rate of wate… more
Date: February 16, 1949
Creator: Guibert, A. G.; Janssen, E. & Robbins, W. M.
Partner: UNT Libraries Government Documents Department
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Preliminary Survey of Icing Conditions Measured During Routine Transcontinental Airline Operation

Description: "Icing data collected on routine operations by four DC-4-type aircraft equipped with NACA pressure-type icing-rate meters are presented as preliminary information obtained from a statistical icing data program sponsored by the NACA with the cooperation of many airline companies and the United States Air Force. The program is continuing on a much greater scale to provide large quantities of data from many air routes in the United States and overseas. Areas not covered by established air routes a… more
Date: December 16, 1952
Creator: Perkins, Porter J.
Partner: UNT Libraries Government Documents Department
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Preliminary Evaluation of the Wing Leading Edge as a Missile-Mounting Location

Description: Report discussing testing to evaluate some of the major aspects of mounting and launching missiles from the leading edge of a wing, including experimentation with six missile models at several Mach numbers. Information from flight tests and launching tests is provided.
Date: January 16, 1957
Creator: Hill, P. R. & Hoffman, S.
Partner: UNT Libraries Government Documents Department
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Investigation of Control Signals for Variable Ramps of Twin-Duct Side Inlets

Description: Report presenting an investigation to determine the effectiveness of experimental control signals applied to a theoretical inlet throat Mach number control system and normal-shock-position control system for varying the inlet geometry of a twin-duct prototype aircraft. Results regarding inlet instability, control requirements, individual throat Mach number control signals, average throat Mach number control signals, theoretical thraot Mach number control analysis, effect of angle of attack, and… more
Date: January 16, 1958
Creator: Beheim, Milton A. & Yeager, Richard A.
Partner: UNT Libraries Government Documents Department
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The Effects of Extensible Rocket Racks on Lift, Drag, and Stability of a 1/10 Scale Rocket-Boosted Model of the McDonnell XF3H-1 Airplane for a Mach Number Range of 0.60 to 1.34

Description: Report presenting testing of the transonic longitudinal characteristics of a model of the McDonnell XF3H-1 airplane. The model had a center-of-gravity location of 28.5 percent of the mean aerodynamic chord and a stabilizer setting of -5.91 degrees relative to the wing chord plane with extensible rocket racks. Results regarding Reynolds number, rocket-rack program, flight time history, trim, lift, drag, longitudinal stability, directional stability, and inlet pressure recovery are provided.
Date: June 16, 1953
Creator: Crabill, Norman L.
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of a High Subsonic Mach Number Turbine Having a 40-Blade Rotor With Zero Suction-Surface Diffusion

Description: Memorandum presenting an experimental turbine designed for a high weight flow per unit frontal area, a high specific work output, a relative critical velocity ratio of 0.82 at the rotor hub inlet, and zero rotor blade suction-surface diffusion. Results regarding a comparison of overall performance of subject turbine with that of configurations I and II and comparison of rotor blade momentum thickness of subject turbine with that of configurations I and II are provided.
Date: January 16, 1958
Creator: Nusbaum, William J.; Wasserbauer, Charles A. & Hauser, Cavour H.
Partner: UNT Libraries Government Documents Department
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Preliminary Report on Experimental Investigation of Engine Dynamics and Controls for a 48-Inch Ramjet Engine

Description: Experimental investigation of engine dynamics and controls for 48-inch ramjet engine in free jet facility at Mach number 2.76 and altitudes 68,000 to 82,000 feet. The engine data presented include steady-state performance, indical response, frequency response, and ignition characteristics. Ignition data are presented for representative fuel-air ratios which show that the normal shock overshoots its final position by several feet during ignition transients.
Date: March 16, 1956
Creator: Vasu, George; Hart, Clint E. & Dunbar, William R.
Partner: UNT Libraries Government Documents Department
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Comparison of Wind-Tunnel, Rocket, and Flight Drag Measurements for Eight Airplane Configurations at Mach Numbers Between 0.7 and 1.6

Description: Report presenting comparisons of low-lift drag measurements on eight airplane configurations at a range of Mach numbers by various techniques. Data was obtained from wind tunnel testing, rocket propelled model tests, and airplane flight tests. The agreement of data is generally good and no consistent Reynolds number effects are observed.
Date: September 16, 1954
Creator: Purser, Paul E.
Partner: UNT Libraries Government Documents Department
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