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Time Histories of Horizontal-Tail Loads, Elevator Loads, and Deformations on a Jet-Powered Bomber Airplane During Abrupt Pitching Maneuvers at Approximately 20,000 Feet

Description: "Time histories are presented of horizontal-tail loads, elevator loads, and deformations on a jet-powered bomber during abrupt pitching maneuvers at a pressure altitude of approximately 20,000 feet. The normal and pitching accelerations measured varied from -0.90b to 3.41g and from -0.73 to 0.80 radian per second per second (sic), respectively, with a Mach number variation of from 0.40 to o.75. The maximum horizontal-tail load measured was 17,250 pounds down. The maximum elevator load was 1900 … more
Date: November 29, 1950
Creator: Wiener, Bernard & Harris, Agnes E.
Partner: UNT Libraries Government Documents Department
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Measurements of Aerodynamic Heat Transfer and Boundary-Layer Transition on a 15 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.2

Description: Report presenting measurements of aerodynamic heat transfer at several stations on the 15 degree total angle conical nose of a rocket-propelled model in free flight at Mach numbers up to 5.2. Laminar, transitional, and turbulent heat-transfer coefficients are provided. Results regarding skin temperature time histories, transition, and computed skin temperatures are provided.
Date: October 15, 1956
Creator: Rumsey, Charles B. & Lee, Dorothy B.
Partner: UNT Libraries Government Documents Department
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Surface-Pressure Distributions on a Systematic Group of NACA 1-Series Cowlings With and Without Spinners

Description: "A method for calculating the flow fields of axially symmetric bodies from their pressure distributions is reported in NACA RM No. L8I17. In order to facilitate application of this method to the important case of the cowling-spinner combination, for use in the design of propellers, the present paper presents static-pressure distributions on the tops of 79 high-critical-speed NACA 1-series cowling-spinner combinations over wide ranges of inlet-velocity ratio at angles of attack of 0 degrees, 2 d… more
Date: November 30, 1948
Creator: Boswinkle, Robert W., Jr. & Keith, Arvid L., Jr.
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics of a Circular Cylinder at Mach Number 6.86 and Angles of Attack Up to 90 Degrees

Description: "Pressure-distribution and force tests of a circular cylinder have been made in the Langley 11-inch hypersonic tunnel at a Mach number of 6.86, a Reynolds number of 129,000 based on diameter, and angles of attack up to 90 degrees. The results are compared with the hypersonic approximation of Grimminger, Williams, and Young and with a simple modification of the Newtonian flow theory. The comparison of experimental results shows that either theory gives adequate general aerodynamic characteristic… more
Date: March 11, 1954
Creator: Penland, Jim A.
Partner: UNT Libraries Government Documents Department
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Comparison With Theory of Landing Impacts of a Model of a Seaplane Incorporating a Hydro-Ski With and Without a Shock Absorber

Description: Report presenting experimental data from calm- and rough-water landing impacts with a dynamic model of a seaplane incorporating a flat-bottom hydro-ski mounted on a rigid strut and on a shock-absorber strut. Results regarding the fixed-ski case and translating-ski case are provided.
Date: July 11, 1956
Creator: Hoffman, Edward L.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of effects of primary jet flow and secondary flow through a zero-length ejector on base and boattail pressures of a body of revolution at free-stream Mach numbers of 1.62, 1.93, and 2.41

Description: An investigation was made at free-stream Mach numbers of 1.62, 1.93, and 2.41 to determine the effects of a primary jet and secondary air flow on the base pressure and pressures acting over the boattailsurface of a body of revolution for two secondary discharge areas. The Mach numbers of the primary nozzles were 1 and 3.23 with the secondary mass flow being varied from 0 to 10 percent of the primary mass flow. The ratio of jet stagnation temperature to tunnel stagnation temperature was about 0.… more
Date: December 6, 1954
Creator: O'Donnell, Robert M. & McDearmon, Russell W.
Partner: UNT Libraries Government Documents Department
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Altitude performance and operational characteristics of 29-inch-diameter tail-pipe burner with several fuel systems and flame holders on J35 turbojet engine

Description: From Summary: "An investigation of turbojet-engine thrust augmentation by means of tail-pipe burning has been conducted in the NACA Lewis altitude wind tunnel. Several fuel systems and flame holders were investigated in a 29-inch-diameter tail-pipe burner to determine the effect of fuel distribution and flame-holder design on tail-pipe-burner performance and operational characteristics over a range of simulated flight conditions. At an altitude of 5000 feet, the type of flame holder used had on… more
Date: November 8, 1949
Creator: Conrad, E. William & Prince, William R.
Partner: UNT Libraries Government Documents Department
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Some experiments relating to the problem of simulation of hot jet engines in studies of jet effects on adjacent surfaces at a free-stream Mach number of 1.80

Description: Report presenting an investigation at a free-stream Mach number of 1.80 in a blowdown tunnel to study the effect on the pressure distribution of a zero-angle-of-attack wing surface when certain exhaust parameters of a hot turbojet engine are varied. Results regarding shock wave and pressure coefficients are provided.
Date: July 11, 1956
Creator: Bressette, Walter E.
Partner: UNT Libraries Government Documents Department
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Altitude-wind-tunnel investigation of J47 turbojet-engine performance

Description: From Introduction: "Data are presented in graphical form to show the engine performance over a range of altitudes from 5000 to 50,000 feet and flight Mach numbers from 0.21 to 0.97. Curves are presented to show the windmilling characteristics of the engine. All engine performance data obtained in the investigation are also presented in tabular form."
Date: November 15, 1949
Creator: Conrad, E. William & Sobolewski, Adam E.
Partner: UNT Libraries Government Documents Department
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Use of a diffuser Mach number as a supersonic-inlet control parameter

Description: A Mach number measured in the subsonic diffuser was used experimentally as the inlet control parameter of a bypass control system for an axisymmetric supersonic inlet operated in combination with a J34 turbo-jet engine at Mach numbers from 1.6 to 2.0. The control maintained the inlet in either critical or supercritical operation, and, when set for critical diffuser operation, the control recovered from disturbances that placed the inlet in both subcritical buzz and supercritical operation. A sl… more
Date: September 14, 1956
Creator: Whalen, Paul P. & Wilcox, Fred A.
Partner: UNT Libraries Government Documents Department
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The Variation With Wing Aspect Ratio of Flap Effectiveness on Thin Rectangular Wings at Transonic Speeds

Description: Report presenting an investigation in the high-speed tunnel using the transonic bump technique in order to study the effectiveness of full-span flap-type controls on 31 unswept rectangular wings. Results regarding lift-curve slope, flap-effectiveness parameter, and the agreement between predicted and experimental results are also provided.
Date: August 23, 1956
Creator: Lowry, John G. & Taylor, Robert T.
Partner: UNT Libraries Government Documents Department
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Some considerations regarding the application of the supersonic area rule to the design of airplane fuselages

Description: Report presenting some considerations and techniques pertinent to the application of the supersonic area rule to the design of airplane fuselages. Some of the factors to consider are an extension of the rule to account for the interference effects of the wing and tail on general flow field, the determination of fuselage area developments which result in minimum wave drag, and the influence of wing parameters and Mach number on the effectiveness of fuselage shaping.
Date: July 3, 1956
Creator: Whitcomb, Richard T.
Partner: UNT Libraries Government Documents Department
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Extended operation of turbojet engine with pentaborane

Description: A full-scale turbojet engine was operated with pentaborane fuel continuously for 22 minutes at conditions simulating flight at a Mach number of 0.8 at an altitude of 50,000 feet. This period of operation is approximately three times longer than previously reported operation times. Although the specific fuel consumption was reduced from 1.3 with JP-4 fuel to 0.98 with pentaborane, a 13.2-percent reduction in net thrust was also encountered. A portion of this thrust loss is potentially recoverabl… more
Date: May 22, 1957
Creator: Useller, James W. & Jones, William L.
Partner: UNT Libraries Government Documents Department
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Flight Investigation of Factors Affecting Pilots' Ability to Utilize a Radarscope Display of Steering Information

Description: Report presenting results of a flight investigation of a radar fire-control system installed in a fighter airplane. Some of the factors included in the radar evaluation are "noise" of the steering dot, lack of target-attitude information, and sensitivity and linearity of the display.
Date: November 23, 1956
Creator: Faber, Stanley; Cheatham, Donald C. & Champine, Robert A.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of acceleration characteristics of a turbojet engine including regions of surge and stall for control applications

Description: The acceleration characteristics, in the region of maximum acceleration and compressor stall and surge, of an axial-flow turbojet engine with a fixed-area exhaust nozzle were determined by subjecting the engine to fuel flow steps, ramps, and ramps with a sine wave superimposed. From the data obtained, the effectiveness of an optimalizer type of control for this engine was evaluated. At all speeds above 40 percent of rated, a maximum acceleration was not obtained until the engine reached the poi… more
Date: December 20, 1954
Creator: Stiglic, Paul M.; Schmidt, Ross D. & Delio, Gene J.
Partner: UNT Libraries Government Documents Department
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A Semiempirical Procedure for Estimating Wing Buffet Loads in the Transonic Region

Description: Report presenting wing buffeting data obtained from a flight loads investigation of two jet-propelled swept-wing airplanes to study the effects of Mach number and reduced frequency on the wing buffet loads. Consistent trends were noted between the flight testing and wind-tunnel testing that the results of this particular test were compared with. Results regarding variation with penetration and dynamic pressure, variation with Mach number and reduced frequency, and estimation of wing buffet load… more
Date: September 14, 1956
Creator: Skopinski, T. H. & Huston, Wilber B.
Partner: UNT Libraries Government Documents Department
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Component performance investigation of J71 experimental turbine 1: Over-all performance with 97-percent-design stator areas

Description: From Summary: "The over-all component performance characteristics of a J71 experimental three-stage turbine with 97 percent design stator areas were determined over a range of speed and pressure ratio at inlet-air conditions of approximately 35 inches of mercury absolute and 700 degrees R. The turbine break internal efficiency at design operating conditions was 0.877; the maximum efficiency of 0.886 occurred at a pressure ratio of 4.0 at 120 percent of design equivalent rotor speed. In general,… more
Date: April 11, 1956
Creator: Schum, Harold J. & Davison, Elmer H.
Partner: UNT Libraries Government Documents Department
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Temperature in a J47-25 Turbojet-Engine Combustor and Turbine Sections During Steady-State and Transient Operation in a Sea-Level Test Stand

Description: From Summary: "In order to determine the conditions of engine operation causing the most severe thermal stresses in the hot parts of a turbojet engine, a J47-25 engine was instrumented with thermocouples and operated to obtain engine material temperatures under steady-state and transient conditions. Temperatures measured during rated take-off conditions of nozzle guide vanes downstream of a single combustor differed on the order of 400 degrees F depending on the relation of the blades position … more
Date: June 3, 1955
Creator: Morse, C. R. & Johnston, J. R.
Partner: UNT Libraries Government Documents Department
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Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed 6: experimental performance of two-stage turbine

Description: The brake internal efficiency of the highly loaded two-stage turbine was 0.79 equivalent design work and speed. The maximum brake internal efficiency was 0.84. A radial survey revealed these major defects: (1) the first-rotor throat area was too large, and a large area of underturned flow existed near the tip;(2) considerable underturning existed at the second-stator outlet; and (3) tangential components of velocity at the turbine outlet amounted to 2.5 points in turbine efficiency.
Date: August 20, 1956
Creator: Davison, Elmer H.; Schum, Harold J. & Petrash, Donald A.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation at Mach Numbers From 0.8 to 1.4 of Static Longitudinal and Lateral-Directional Characteristics of an Unswept-Wing Airplane Model

Description: "Results are presented for a wind-tunnel investigation of an airplane model with a 3.4-percent-thick unswept wing of aspect ratio 2.45 at Mach numbers from 0.8 to 1.4 at a Reynolds number of 1.5 million. Longitudinal characteristics are presented for the basic model and for configuration variations involving two types of wing camber, an area-rule fuselage modification, various external-store arrangements, several conventional missile installations and one designed according to the moment-of-are… more
Date: December 13, 1956
Creator: Summers, James L.; Treon, Stuart L. & Graham, Lawrence A.
Partner: UNT Libraries Government Documents Department
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Aerodynamic design of axial-flow compressors: Volume 3

Description: Chapters XI to XIII concern the unsteady compressor operation arising when compressor blade elements stall. The fields of compressor stall and surge are reviewed in Chapters XI and XII, respectively. The part-speed operating problem in high-pressure-ratio multistage axial-flow compressors is analyzed in Chapter XIII. Chapter XIV summarizes design methods and theories that extend beyond the simplified two-dimensional approach used previously in the report. Chapter XV extends this three-dimension… more
Date: August 1, 1956
Creator: Johnsen, Irving A.; Bullock, Robert O.; Graham, Robert W.; Costilow, Eleanor L.; Huppert, Merle C.; Benser, William A. et al.
Partner: UNT Libraries Government Documents Department
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