UNT Libraries Government Documents Department - 242 Matching Results

Search Results

Aerodynamic and hydrodynamic characteristics of a deck-inlet multijet water-based-aircraft configuration designed for supersonic flight

Description: From Introduction: "In the present investigation, lift, drag, and pitching moment were determined over a Mach number range 0.6 to 1.42. Smooth-water takeoff and landing stability and resistance were investigated. A brief check of the rough-water spray and behavior was also made."
Date: December 5, 1956
Creator: Bielat, Ralph P.; Coffee, Claude W., Jr. & Petynia, William W.

Aerodynamic and hydrodynamic characteristics of models of some aircraft-towed mine-sweeping devices : TED No. NACA AR 8201

Description: This report details a study that was conducted by the U.S. Naval Air Development Center to "determine the feasibility of several airborne magnetic mine-sweeping methods. The advantages of a satisfactory airborne method are greater safety and speed than are possible with existing surface methods." The configurations and results of the double Q-sweep, the modified double-catenary sweep, and the M-sweep are examined.
Date: December 1, 1955
Creator: Shanks, Robert E.

Aerodynamic characteristics at Mach number of 4.06 of a typical supersonic airplane model using body and vertical-tail wedges to improve directional stability

Description: Report presenting an investigation at Mach number 4.06 on a typical supersonic airplane model with a 40 degree sweptback wing. The purpose of the investigation was to determine the effectiveness of using wedges on the body and on the vertical tail to increase the static directional stability. Results regarding the longitudinal characteristics and lateral characteristics are provided.
Date: December 3, 1957
Creator: Dunning, Robert W.

Aerodynamic characteristics of NACA RM 10 missile in 8 by 6 foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98. 3: analysis of force distribution at angle of attack (stabilizing fins removed)

Description: Report presenting an analysis of the force distribution on a slender pointed body of revolution at angle of attack utilizing pressure-distribution data and balance measurements. The data were obtained in the supersonic tunnel at a variety of Mach numbers and angles of attack. Results regarding normal forces and axial force are provided.
Date: December 12, 1950
Creator: Luidens, Roger W. & Simon, Paul C.

Aerodynamic characteristics of two delta wings at Mach number 4.04 and correlations of lift and minimum-drag data for delta wings at Mach numbers from 1.62 to 6.9

Description: Report presenting tests of the aerodynamic characteristics of two delta wings of the same aspect ratio and airfoil sections at Mach number 4.04. The results indicated that the ratio of the experimental lift-curve slope to the theoretical two-dimensional lift-curve slope from previous testing is valid at this Mach number.
Date: December 23, 1952
Creator: Ulmann, Edward F. & Dunning, Robert W.

Aerodynamic characteristics of two rectangular-plan-form, all moveable controls in combination with a slender body of revolution at Mach numbers from 3.00 to 6.25

Description: Report presenting the results of force and moment tests at a range of Mach numbers on two rectangular-plan-form, all-movable controls in combination with a slender body of revolution are presented and compared with the predictions of theory. The results showed that lift variations with angle of attack were somewhat nonlinear for both control-body combinations tested.
Date: December 28, 1955
Creator: Wong, Thomas J. & Gloria, Hermilo R.

Aerodynamic load distribution over a 45 degree swept wing having a spoiler-slot-deflector aileron and other spoiler ailerons for Mach numbers from 0.60 to 1.03

Description: Report discussing an investigation of a 45 degree swept-back-wing-body combination with flap spoiler ailerons, deflector ailerons, and a spoiler-slot-deflector aileron. The pressures were measured from Mach numbers 0.60 to 1.03 and at various angles of attack.
Date: December 5, 1957
Creator: West, F. E., Jr.; Whitcomb, Charles F. & Schmeer, James W.

Altitude-chamber investigation of J73-GE-1A turbojet engine component performance

Description: Report presenting an investigation to determine the altitude performance characteristics of a J73-GE-1A turbojet engine conducted in an altitude chamber. The engine had a ten-percent oversize turbine-nozzle are compared with the production J73 engine. Results regarding radial pressure and temperature profiles, compressor performance, combustor performance, turbine performance, and tail-pipe-diffuser and exhaust-nozzle performance.
Date: December 9, 1954
Creator: Campbell, Carl E. & Sobolewski, Adam E.

Altitude investigation of 16 flame-holder and fuel-system configurations in tail-pipe burner

Description: From Introduction: "The data obtained for each configuration are presented in a manner to show the effects of fuel distribution and flame-holder design on net thrust, specific fuel consumption, exhaust-gas temperature, combustion efficiency, operable range of tail-pipe-burner fuel-air ratios, and maximum altitude limit."
Date: December 12, 1951
Creator: Grey, Ralph E.; Krull, H. G. & Sargent, A. F.

Altitude Performance Characteristics of Tail-Pipe Burner With Converging Conical Burner Section on J47 Turbojet Engine

Description: From Introduction: "The effect of flame-holder and fuel-system design on the burner performance and the effect of altitude and flight Mach number on over-all performance with a fixed-area exhaust nozzle are reported in reference 1 to 4. Altitude performance characteristics of a tail-pipe burner having a converging conical burner section are presented in this report. Tail-pipe burner performance at several flight conditions is given in both tabular and graphical forms and compared with performance of the standard engine and of the tail-pipe burner reported in reference 2."
Date: December 19, 1950
Creator: Prince, William R. & McAulay, John E.

Altitude Performance Characteristics of the J73-GE-1A Turbojet Engine

Description: From Introduction: "The over-all altitude-performance characteristics of this engine are reported herein, and the component performance characteristics are given in reference 1. The data are presented in the form of engine pumping characteristics to allow accurate calculation of engine performance at any operating or flight condition within the range covered by the experimental data. A curve is also presented that will allow determination of thrust in flight by the measurement of ambient static pressure and total pressure in the exhaust nozzle."
Date: December 9, 1954
Creator: Campbell, Carl E. & Conrad, E. William

Altitude performance characteristics of turbojet-engine tail-pipe burner with variable-area exhaust nozzle using several fuel systems and flame holders

Description: From Introduction: "The performance of several tail-pipe burners with fixed area exhaust nozzles is reported in references 1 to 4, and the performance of an NACA-designed tail-pipe burner with a variable-area exhaust nozzle is reported in reference 5. Operational characteristics of the tail-pipe burner are also discussed."
Date: December 29, 1950
Creator: Johnson, LaVern A. & Meyer, Carl L.

Altitude performance of J71-A-2(600-D1) turbojet engine

Description: From Introduction: "As part of a complete investigation of the J71-A-2(600-D1) turbojet engine conducted in an altitude test chamber at the NACA Lewis laboratory, the steady-state altitude performance, with afterburner inoperative and ejector shroud removed, was obtained and is presented herein. The component performance of the J71-A-2(600-D1) turbojet engine is presented in reference 1. The effects of compressor interstage bleed and adjustable inlet guide vanes on compressor-stall characteristics are described in reference 2."
Date: December 28, 1956
Creator: Smith, Ivan D. & Sivo, Joseph N.

Altitude-Wind-Tunnel Investigation of Combustion-Chamber Performance on J47 Turbojet Engine

Description: From Introduction: "Results are presented to indicate the effect of altitude, flight Mach number, and exhaust-nozzle-outlet area on the combustion efficiency, the losses in total pressure occurring in the combustion chamber, and the fractional loss in engine cycle efficiency resulting from combustion-chamber pressure losses. The engine cycle efficiency is also presented.These results are shown graphically as a fraction of corrected engine speed and in tabular form."
Date: December 15, 1950
Creator: Campbell, Carl E.

Altitude Wind Tunnel Investigation of the Performance of Compressor, Combustor, and Turbine Components of Prototype J47D (RX1-1) Turbojet Engine

Description: As a portion of an over-all performance investigation of the prototype J47D (RX-1) turbojet engine, performance of the compressor, combustor, and turbine components has been determined in the Lewis altitude wind tunnel over a range of altitude from 5000 to 55,000 feet and at flight Mach numbers from 0.19 to 0.92. Investigations were conducted with the engine operating on an electronic control schedule and slow with a two-lever control system by which fuel flow and exhaust-nozzle area could be controlled separately. Two combustor configurations were investigated.
Date: December 21, 1951
Creator: Farley, John M.

Amplitude of Supersonic Diffuser Flow Pulsations

Description: A theoretical method for evaluating the stability characteristics and the amplitude and the frequency of pulsation of ram-jet engines without heat addition is presented herein. Experimental verification of the theoretical results are included where data were available. Theory and experiment show that the pulsation amplitude of a high mass-flow-ratio diffuser having no cone surface flow separation increases with decreasing mass flow. The theoretical trends for changes in amplitude, frequency, and mean-pressure recovery with changes in plenum-chamber volume were experimentally confirmed. For perforated convergent-divergent-type diffusers, a stability hysteresis loop was predicted on the pressure-recovery mass-flow-ratio curve. At a given mean mass-flow ratio, the higher.value of mean pressure recovery corresponded to oscillatory flow in the diffuser while the lower branch was stable. This hysteresis has been observed experimentally. The theory indicates that for a ram-jet engine of given diameter, the amplitude of pulsation of a supersonic diffuser is increased by decreasing the relative size of the plenum chamber with respect to the diffuser volume down to a critical value at which oscillations cease. In the region of these critical values, the stable mass-flow range of the diffuser may be increased either by decreasing the combustion chamber volume or by increasing the length of the diffuser.
Date: December 16, 1952
Creator: Sterbentz, William H. & Davids, Joseph

Analysis of a nuclear-powered liquid-metal ducted-fan cycle

Description: From Introduction: "The results are presented for flight Mach numbers of 0.9 to 1.5 at an altitude of 50,000 feet. The effect of flight altitude on optimum engine design-point airplane performance is also shown."
Date: December 17, 1952
Creator: Rom, F. E. & Wachtl, W. W.

Analysis of a Nuclear-Powered Liquid-Metal Ducted-Fan Cycle

Description: From Introduction: "The results are presented for flight Mach numbers of 0.9 to 1.5 at an altitude of 50,000 feet. The effect of flight altitude on optimum engine design-point airplane performance is also shown."
Date: December 17, 1952
Creator: Rom, F. E. & Wachtl, W. W.

Analysis of Limitations Imposed on One-Spool Turboprop-Engine Designs by Compressors and Turbines at Flight Mach Numbers of 0.06, and 0.8

Description: Turbine centrifugal stress is a limiting factor for all flight conditions studied. This stress is more severe for sea-level operations than for subsonic flight at the tropopause. Turbines designed for a stress of 30,000 psi are capable of driving a light, compact, high-spedd compressor but only at high values of specific fuel consumption. An increase in turbine-inlet temperature is accompanied by an increase in turbine centrifugal stress. If stresses in excess of 50,000 psi can be tolerated, compressor aerodynamics may become a primary limitation.
Date: December 6, 1956
Creator: Cavicchi, Richard H.

Analysis of part-speed operation for high-pressure-ratio multistage axial-flow compressors

Description: From Introduction: "For the analysis reported herein, the same hypothetical 12-stage compressor discussed in reference 6 was chosen, and the effects of inlet-stage stall characteristics and stage interactions were estimated by arbitrary adjustment of the stall characteristics and stage interactions were estimated by arbitrary adjustment of the stalled characteristics of the individual stages."
Date: December 4, 1953
Creator: Benser, William A.

The Application of a Simplified Lifting-Surface Theory to the Prediction of the Rolling Effectiveness of Plain Spoiler Ailerons at Subsonic Speeds

Description: From Introduction: "It is the purpose to describe a method of predicting spoiler rolling-moment effectiveness based on the simplified lifting-surface flap theory of reference 12. The results of applying the present method to the configurations described in references 1 to 8 (see table I and fig. 1) and the comparison with the experimental data are presented herein."
Date: December 6, 1954
Creator: Franks, Ralph W.

Arrangement of Bodies of Revolution in Supersonic Flow to Reduce Wave Drag

Description: The wave drag of a combination of slender bodies of revolution at zero angle of attack is studied with a view to determining the arrangements for which the total drag is a minimum.Linearized theory is used to calculate the pressure distribution in the field surrounding the bodies. The interference drag coefficient is computed for different arrangements. The special cases of two bodies and of a three-body combination with bilateral symmetry are considered. The bodies treated are of the form determined by Sears and Haack as having minimum wave drag for prescribed volume and length. They also have equal fineness ratios. Numerical calculations of the drag coefficient of interference are carried out and curves are drawn which show the relative positions at which minimum drag occurs. A three-body configuration is found for which the total wave drag is about 35 percent less than the sum of the individual wave drags of the three bodies.
Date: December 17, 1951
Creator: Friedman, Morris D