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NACA Research Memorandums
211
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90
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48
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37
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25
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22
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Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics 1: effect of air bleed at compressor outlet
From Summary: "An analytical investigation was made to determine from component performance characteristics the effect of air bleed at the compressor outlet on the acceleration characteristics of a typical high-pressure-ratio single-spool turbojet engine. Consideration of several operating lines on the compressor performance map with two turbine-inlet temperatures showed that for a minimum acceleration time the turbine-inlet temperature should be the maximum allowable, and the operating line on the compressor map should be as close to the surge region as possible throughout the speed range. Operation along such a line would require a continuously varying bleed area."
Date:
March 10, 1953
Creator:
Rebeske, John J., Jr. & Rohlik, Harold E.
Object Type:
Report
System:
The UNT Digital Library
Accident in Continuous-Dissolver Pilot Plant of Fluoride Volatility Project on May 15, 1957
The so-called Fluoride Volatility Processes refer to several proposed non-aqueous methods of processing irradiated fuel elements. In each of these methods, the uranium is fluorinated to UF6 and then decontaminated by distillation. One of those methods, involving the direct fluorination of the uranium by bromine trifluoride (BTF), has been under investigation at BNL since 1950. In 1952, it was demonstrated at BNL that uranium, as UF6, could be satisfactorily decontaminated by distillation in small-scale pilot plant equipment; end in 1953, BNL undertook the job of determining the technical feasibility of a continuous dissolver on a pilot-plant scale. The reason for the project was that the economic superiority of the process seemed to depend upon its amenability to continuous operation.
Date:
July 10, 1957
Creator:
Strickland, Gerald; Horn, F. L.; Johnson, Richard & Dwyer, O. E.
Object Type:
Report
System:
The UNT Digital Library
Additional Fatigue Tests on Effects of Design Details in 355-T6 Sand-Cast Aluminum Alloy
From Introduction: "Reported herein are results of the additional direct-stress fatigue tests on: (1) a plate-type specimen with cored centrally located hole and (2) 0.300-inch-diameter round polished specimens with various degrees of porosity."
Date:
March 10, 1954
Creator:
Eaton, I. D. & Youra, John A.
Object Type:
Report
System:
The UNT Digital Library
Additional Results on the Static Longitudinal and Lateral Stability Characteristics of a 0.05-Scale Model of the Convair F2Y-1 Airplane at High Subsonic Speeds
"Additional results on the static longitudinal and lateral stability characteristics of a 0.05-scale model of the Convair F2Y-1 water-based fighter airplane were obtained in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.50 to 0.92. The maximum angle-of-attack range (obtained at the lower Mach numbers) was from -2 degrees to 25 degrees. The sideslip-angle range investigated was from -4 degrees to 12 degrees" (p. 1).
Date:
August 10, 1954
Creator:
Spreeman, Kenneth P. & Few, Albert G., Jr.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics at a Mach Number of 1.38 of Four Wings of Aspect Ratio 4 Having Quarter-Chord Sweep Angles of 0 Degrees, 35 Degrees, 45 Degrees, and 60 Degrees
Report discussing testing to determine the supersonic aerodynamic characteristics of four sweptback wings and wing-body configurations at several angles. Information about basic wing data, modifications to the 60 degree wing, the effects of sweep, and effects of fuselage are included.
Date:
October 10, 1950
Creator:
Kemp, William B., Jr.; Goodson, Kenneth W. & Booth, Robert A.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics at Mach Numbers From 2.5 to 3.5 of a Canard Bomber Configuration Designed for Supersonic Cruise Flight
Report presenting an investigation of a canard-type configuration designed for supersonic cruise flight in the Unitary Plan wind tunnel. Tests were conducted over a range of angles of attack and angles of sideslip. Results regarding the effect of forebody configuration, effects of Reynolds number and transition, effect of canard and elevon deflection, and effect of vertical surfaces are provided.
Date:
September 10, 1958
Creator:
Carmel, Melvin M.; Kelly, Thomas C. & Gregory, Donald T.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2: Effects of sweep angle and thickness ratio on the aerodynamic characteristics in pitch
Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.60 to determine the effects of sweep and thickness on the longitudinal characteristics of a series of wing-body combinations with cambered wings with an aspect ratio of 3.5 and taper ratio of 0.2. The results show the effects of sweep, thickness, and the horizontal canard surface on the lift, drag, and pitching-moment coefficients and lift-drag ratios. The lift-curve slope, aerodynamic-center locations, maximum lift-drag ratios, lift coefficients for maximum lift-drag ratio, and drag-rise factor are presented.
Date:
January 10, 1952
Creator:
Robinson, Ross B. & Driver, Cornelius
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics of a full-span trailing-edge control on a 60 degree delta wing with and without a spoiler at Mach number 1.61
Report presenting an investigation at Mach number 1.61. to determine the aerodynamic characteristics of a full-span trailing-edge control on a 60 degree delta wing with and without a partial-span spoiler mounted on the wing just ahead of the control. Pressure distribution and hinge-moment measurements were made over a range of angles of attack and control deflection. Results indicated that regions of increase pressure due to flow separation ahead of the control at the larger control deflections and ahead of the spoiler exist.
Date:
March 10, 1954
Creator:
Lord, Douglas R. & Czarnecki, K. R.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of Flying-Boat Hulls Having Length-Beam Ratios of 20 and 30
Report discussing the aerodynamic effects of length-beam ratios 20 and 30 as compared to length-beam ratios from 6 to 15. There was slightly more longitudinal stability and slightly less directional stability than in the lower ratios and not much change in the minimum drag coefficient.
Date:
November 10, 1948
Creator:
Riebe, John M.
Object Type:
Report
System:
The UNT Digital Library
An Air-Borne Target Simulator for Use With Scope-Presentation Type Fire-Control Systems
Report describing the design and flight evaluation of an air-borne target simulator using precomputed relative kinematics for use in tracking studies of fighter aircraft equipped with scope-presentation type fire-control systems. Testing occurred in an F86D airplane equipped with a Hughes E-4 fire-control system. Results regarding relative kinematic programming considerations and restrictions to system evaluation are provided.
Date:
May 10, 1957
Creator:
Foster, John V.; Fulcher, Elmer C. & Heinle, Donovan R.
Object Type:
Report
System:
The UNT Digital Library
An air-flow-direction pickup suitable for telemetering use on pilotless aircraft
From Summary: Test results are presented which indicate that the pickup is aerodynamically stable and has accuracy, obtained from a bench calibration, of better than 0.3^o under conditions including acceleration up to 20g in any direction, Mach numbers from 0.5 to 2.8, and dynamic pressures up to at least 65 psi. Equations and curves which can be used to obtain flow direction at the center of gravity of a maneuvering model are presented."
Date:
March 10, 1954
Creator:
Ikard, Wallace L.
Object Type:
Report
System:
The UNT Digital Library
An Alpha, Beta, Gamma Transistorized Survey Meter
A portable, light weight transistorized alpha, beta, and gamma survey meter was designed and fabricated.
Date:
February 10, 1956
Creator:
Spear, W. G.
Object Type:
Report
System:
The UNT Digital Library
Altitude-Chamber Performance of British Rolls-Royce Nene II Engine 3 - 18.00-Inch-Diameter Jet Nozzle
An altitude-chamber investigation of British Rolls-Royce Nene II turbojet engine was conducted over range of altitudes from sea level to 65,000 feet and ram pressure ratios from 1.10 to 3.50, using an 18.00-inch-diameter jet nozzle. The 18.00-inch-diameter jet nozzle gave slightly lower values of net-thrust specific fuel consumption than either the 18.41- or the standard 18.75-inch-diameter jet nozzles at high flight speeds. At low flight speeds, the 18.41-inch-diameter jet nozzle gave the lowest value of net-thrust specific fuel consumption.
Date:
July 10, 1950
Creator:
Grey, Ralph E.; Brightwell, Virginia L. & Barson, Zelmar
Object Type:
Report
System:
The UNT Digital Library
Altitude Component Performance of the YJ73-GE-3 Turbojet Engine
Memorandum presenting an investigation to determine the altitude performance characteristics of the YJ73-GE-3 turbojet engine in an altitude chamber. The component performance was determined at two positions of the inlet guide vanes over a range of engine speeds, exhaust-nozzle areas, and flight conditions. Results regarding compressor performance, combustor performance, turbine performance, and altitude performance of components at rated conditions are provided.
Date:
January 10, 1955
Creator:
McAulay, John E. & Campbell, Carl E.
Object Type:
Report
System:
The UNT Digital Library
Altitude investigation of three flame-holder and fuel-systems configurations in a short converging afterburner on a turbojet engine
From Introduction: "Previous investigations of a number of internal configurations in the same afterburner shell are reported in reference 1 and 2. In the investigation reported herein, the performance and operational characteristics of three afterburner internal configurations were evaluated."
Date:
September 10, 1952
Creator:
Braithwaite, Willis M.; Renas, Paul E. & Jansen, Emmert T.
Object Type:
Report
System:
The UNT Digital Library
Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, 7, Pressure and Temperature Distributions
Temperature and pressure distributions for an original and modified 3000 pound thrust axial flow turbojet engine were investigated. Data are included for a range of simulated altitudes from 5000 to 45000 feet, Mach numbers from 0.24 to 1.08, and corrected engine speeds from 10,550 to 13,359 rpm.
Date:
December 10, 1948
Creator:
Saari, Martin J. & Prince, William R.
Object Type:
Report
System:
The UNT Digital Library
Altitude-wind-tunnel investigation of tail-pipe burner with converging conical burner section on J35-A-5 turbojet engine
An investigation of turbojet-engine thrust augmentation by means of tail-pipe burning has been conducted in the NACA Lewis altitude wind tunnel.
Date:
February 10, 1950
Creator:
Thorman, H. Carl & Campbell, Carl E.
Object Type:
Report
System:
The UNT Digital Library
Analysis of 2-Spar Cantilever Wings With Special Reference to Torsion and Load Transference
"This paper deals with the analysis of 2-spar cantilever wings in torsion, taking cognizance of the fact that the spars are not independent, but are interconnected by ribs and other structural members. The principles of interaction are briefly explained, showing that the mutual relief action occurring depends on the "pure torsional stiffness" of the wing cross section. Various practical methods of analysis are outlined" (p. 45).
Date:
April 10, 1934
Creator:
Kuhn, Paul
Object Type:
Report
System:
The UNT Digital Library
Analysis of a flight investigation at supersonic speeds of a simple homing system
From Introduction: "The purpose of the flight investigation described herein was as a "proof" check of the system and to determine what effect several variables which could not be practicably simulated would have on the operation."
Date:
January 10, 1956
Creator:
Gardiner, Robert A.; Gillis, Clarence L. & Graves, G. B., Jr.
Object Type:
Report
System:
The UNT Digital Library
An Analysis of Airspeeds and Mach Numbers Attained by Lockheed Constellation Airplanes in Transcontinental Operations During the Early Summer of 1946
Report presenting airspeed and altitude data obtained from Lockheed Constellation airplanes flying between New York and San Francisco during May and June of 1946 in order to determine the probability of reaching or exceeding given values of airspeed and Mach number. Analysis indicated that the total probability of exceeding the placard "never extend" speed depends primarily on the probability of exceeding this speed in descent. The probability of exceeding the critical Mach number is very negligible.
Date:
October 10, 1947
Creator:
Steiner, Roy
Object Type:
Report
System:
The UNT Digital Library
Analysis of Iron in Thorium, Beryllium, and Cerium
Introduction. the colorimetric determination of iron based on the formation of the colored ferrous-1,10-phenanthroline complex has been used successfully by a number of investigators. In this technical report, its adaptation to the routine determination of iron in cerium, thorium, and beryllium metals and their compounds is described.
Date:
September 10, 1945
Creator:
Ericson, R. P & Fornefeld, E. J.
Object Type:
Report
System:
The UNT Digital Library
Analysis of parameters for thrust control of a turbojet engine equipped with air-inlet throttle and variable-area exhaust nozzle
From Introduction: "In this report, altitude, airplane velocity, exhaust-nozzle area, and turbine-inlet temperature were chosen and corresponding engine speed, fuel flow, and throttle pressure ratio were found. A detailed discussion of the engine analysis and the calculations used are presented in Appendix A. The derivations of the principal equations used are presented in appendix B."
Date:
August 10, 1948
Creator:
Boksenbom, Aaron S. & Feder, Melvin S.
Object Type:
Report
System:
The UNT Digital Library
Analysis of the dynamic lateral stability characteristics of the Bell X-2 airplane as affected by variations in mass, aerodynamic, and dimensional parameters
Report presenting an analysis of the dynamic-lateral-stability characteristics of the Bell X-2 airplane as affected by variations in mass, aerodynamic, and dimensional parameters by means of calculations of the period and rate of damping of the lateral oscillation. Results regarding the airplane with flaps and gear retracted, airplane with flaps and gear lowered, and effects of assumed modifications to the airplane are provided.
Date:
August 10, 1949
Creator:
Michael, W. H., Jr. & Queijo, M. J.
Object Type:
Report
System:
The UNT Digital Library
An Analysis of the Effect of Structural Feedback on the Flutter of a Control Surface Having a Power-Boost System
From Summary: "Such devices as leading- and trailing-edge flaps which are now in use on operational aircraft permit the attainment of maximum airplane lift coefficients, power-off, of the order of 2.8 (reference 1). Airfoil-section maximum lift coefficients as high as 5.5 have been obtained in wind-tunnel tests (see, for example, reference 2), and in a limited flight investigation airplane lift coefficients of 4.2 were obtained (reference 3)."
Date:
June 10, 1952
Creator:
Barnes, Robert H.
Object Type:
Report
System:
The UNT Digital Library