Topics: DTIC Archive, JOINT PUBLICATIONS RESEARCH SERVICE ARLINGTON VA, *VELOCITY, *SUPERSONIC...

Topics: DTIC Archive, JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB, *SUPERSONIC CHARACTERISTICS,...

Topics: DTIC Archive, JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB, *SUPERSONIC CHARACTERISTICS,...

A test was conducted in a propulsion wind tunnel to determine the aerodynamic performance of four types of decelerators. Data were obtained at Mach numbers from 1.8 to 2.5 at free-stream dynamic pressures from 80 to 200 psf. Increasing the Mach number resulted in a decrease in the steady-state drag coefficient and an increase in the dynamics of the cross parachutes. At Mach number 2.5, increasing the free-stream dynamic pressure resulted in a decrease in the dynamics and an increase in the...

Topics: DTIC Archive, Homan, M L, *DROGUE PARACHUTES, BALLOONS, FLEXIBLE STRUCTURES, MACH NUMBER,...

A derivation is presented of a point-source method based on the linearized theory for obtaining the pressure coefficient on thin wings at supersonic speeds. The method is applied to calculate the lift distribution of a thin flat-plate wing having a straight leading edge and an arbitrarily curved wing tip whose elements are swept behind the Mach angle. A qualitative basis for obtaining solutions that satisfy the Kutta-Joukowski condition is included. The analysis is continued to formulate the...

Topics: DTIC Archive, Evvard, John C, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC,...

A semi empirical profile-correction factor is discussed which enables the estimation of the wave drag due to thickness at supersonic speeds for three-dimensional wings with arbitrary airfoil section (subject to the restrictions of thin-airfoil theory) through use of previously calculated drag coefficients. Application of the proposed correction factor to the known drag coefficients of some rhombic-profile wings yielded estimates for the drag coefficients of parabolic-arc-profile wings that were...

Topics: DTIC Archive, Margolis, Kenneth, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC,...

A lift cancellation technique is presented for determining load distributions on thin wings at supersonic speeds. The technique retains certain features of the method recently introduced by Theodore P. Goodman, while simplifying and generalizing others. A general expression is derived for the load distribution over a cancellation wing. This expression permits the determination of lift distributions on wings that cannot be solved by cancellation techniques based on the superposition of conical...

Topics: DTIC Archive, Mirels, Harold, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC,...

Topics: DTIC Archive, Lomax, Harvard, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC,...

Topics: DTIC Archive, Gibber, Philip F, NAVAL POSTGRADUATE SCHOOL MONTEREY CA, *DETONATION WAVES,...

Topics: DTIC Archive, FEDERAL AVIATION AGENCY WASHINGTON DC, *SUPERSONIC CHARACTERISTICS, *SUPERSONIC...

The cited references pertain primarily to the following aerodynamic information on ring wings, also known as annular wings or circular wings: Calculation of circumferential velocity and pressure distribution, studies on flow separation phenomena at the wing leading and trailing edges, measurement of lift, drag and pitching moment, application of linearized theory to subsonic and supersonic gas flow, theory and measurement of vortex drag, measurement of three-dimensional turbulent boundary...

Topics: DTIC Archive, Terry, John E, REDSTONE SCIENTIFIC INFORMATION CENTER REDSTONE ARSENAL AL,...

A computer program was developed which is particularly well suited for use in parametric flutter investigations where a large quantity of numerical data required. The underlying analysis used exact, linearized, three-dimensional aerodynamic theory so the program can be used to investigate the critical low supersonic regime. Finite panel arrays can be treated, and wind tunnel installations can be simulated. A limited quantity of informative numerical data is presented Most of the data pertains...

Topics: DTIC Archive, Kobett, D R, MIDWEST RESEARCH INST KANSAS CITY MO, *FLUTTER, COMPUTER PROGRAMS,...

Approximate analytical relations are developed for several possible ''conical'' flow fields resulting from the steady supersonic flow of a uniform, non-viscous, non-heat conducting, combustible-gas mixture past a semi-infinite cone (at zero angle of attack) for instantaneous chemical reaction. The flow fields considery-are of the shock-deflagration, detonation, and detonation-shock types with attached adiabatic and diabatic discontinuities. Particular emphasis is placed upon the Chapman-Jouguet...

Topics: DTIC Archive, Woolard, Henry W, JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB, *SHOCK WAVES,...

Data obtained from free flight tests on pointed cones having semi-angles from 5 to 35 degrees at Mach numbers from 2 to 5 and Reynolds numbers up to 1.7 x 10 to the 8th power are correlated with simple theoretical formulae. A detailed analysis of the errors in the experimental measurements is presented and from correlations of data having an accuracy of =10% or better, the following conclusions were made: (a) For Reynolds numbers greater than 2 x 10 to the 7th power the experimental Stanton...

Topics: DTIC Archive, Seel, M W, BRISTOL AIRCRAFT LTD (UNITED KINGDOM), *SUPERSONIC CHARACTERISTICS,...

Topics: DTIC Archive, Lomax, Harvard, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES...

Topics: DTIC Archive, BAUGHMAN, L. E., NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC,...

Topics: DTIC Archive, JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB, *SUPERSONIC CHARACTERISTICS,...

The perturbation field induced by a line vortex in a supersonic stream and the downwash behind a supersonic lifting surface are examined for the purpose of establishing approximate methods for determining the downwash behind supersonic wings. Lifting-line methods are presented for calculating supersonic downwash. An unbent lifting line (horseshoe-vortex system) is used to compute the downwash behind rectangular and triangular wings and the results are compared with the exact linearized...

Topics: DTIC Archive, Mirels, Harold, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC, *SWEPT...

Topics: DTIC Archive, Brown, Clinton E, NAVAL AIR TEST CENTER PATUXENT RIVER MD, *DELTA WINGS, ROLL,...

Unsteady actuators with a high amplitude output and tunable frequency are needed for the effective control of many sub and supersonic flows. The development, design, characterization, modeling and implementation of a novel high-bandwidth micro fluidic actuator were the main focus of this project and are described in this report. This micro fluidic actuator system essentially consists of an underexpanded primary source jet impinging upon (and exiting) a short cylindrical cavity where the array...

Topics: DTIC Archive, FLORIDA AGRICULTURAL AND MECHANICAL UNIV TALLAHASSEE, *AMPLITUDE, *SUPERSONIC...

A thin axisymmetric wing in a supersonic flow is studied to determine the profile of least resistance of an annular wing.

Topics: DTIC Archive, Borisov, B I, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *RING WINGS,...

We investigate the feasibility of using optically generated channels of reduced air density to provide trajectory correction (guiding) for a supersonic projectile. It is shown that the projectile experiences a force perpendicular to its direction of motion as one side of the projectile passes through a channel of reduced air density. A single channel of reduced air density can be generated by the energy deposited from filamentation of an intense laser pulse. We propose changing the laser pulse...

Topics: DTIC Archive, NAVAL RESEARCH LAB WASHINGTON DC PLASMA PHYSICS DIV, *GUIDED PROJECTILES, AIR,...

A general theory of steady three-dimensional flow of a nonviscous fluid in subsonic and supersonic turbomachines having arbitrary hub and casing shapes and a finite number of blades is presented, The solution of the three-dimensional direct and inverse problem is obtained by investigating an appropriate combination of flows on relative stream surfaces whose intersections with a z-plane either upstream of or some- where inside the blade row form a circular arc or a radial line. The equations...

Topics: DTIC Archive, Wu, Chung-Hua, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC, *THREE...

The report is a presentation of graphs of the oblique-shock relationships for several ratios of specific heats at several Mach numbers. The specific heat ratios vary from 1.10 to 1.66 in increments of 0.02, and a plot is also shown for a specific heat ratio equal to 1.667. The Mach numbers range from 1.5 to 6.0 with increments of 0.5 and from 6.0 to 10.0 with increments of 1.0; Mach number 15.0 is presented separately.

Topics: DTIC Archive, Armstrong, W C, ARO INC ARNOLD AFS TN, *SHOCK WAVES, *SPECIFIC HEAT, HYPERSONIC...

Linearized, compressible-flow analysis is applied to the study of quasi-conical supersonic wing theory. Single-integral equations are derived which relate either the loading to the shape of a lifting surface or the thickness of a symmetrical wing to the pressure distribution for triangular wings with subsonic leading edges. The forms of these equations and their inversions are simplified through the introduction of the finite part and the generalized principal part of an integral.

Topics: DTIC Archive, Lomax, Harvard, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC,...

Development of a Mach 1.2 rain erosion test apparatus is described. This rotating arm apparatus is capable of evaluating the relative rain erosion resistance of materials and can be operated at speeds of 450 to 900 mph in a 1 or 2 inch/hour simulated rainfall. The report describes the design and development of the apparatus including the rotating arm, power train, test enclosure, rain simulation and control systems. Calibration and correlation experiments are also described.

Topics: DTIC Archive, Hurley, Charles J, DAYTON UNIV OH RESEARCH INST, *MATERIALS, *TEST EQUIPMENT,...

Topics: DTIC Archive, Luce, Richard W , Jr, MASSACHUSETTS INST OF TECH CAMBRIDGE DIV OF INDUSTRIAL...

Topics: DTIC Archive, BOATRIGHT, WILLIAM B., NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER...

Topics: DTIC Archive, WINKLER, E. M., NAVAL ORDNANCE LAB WHITE OAK MD, *AERODYNAMIC HEATING, *STAGNATION...

Topics: DTIC Archive, Dugan, Jr, James F., NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC,...

Contents: The Supersonic Flow Around Symmetrical Torsioned and Curved Delta Wings, Taking Into Consideration the Separation of Flow at the Leading Edges; and The Thin Delta Wing, With Variable Geometry, Optimum for Two Supersonic Cruising Speeds.

Topics: DTIC Archive, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO, *SUPERSONIC CHARACTERISTICS, *DELTA...

Topics: DTIC Archive, Lampert, Seymour, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES...

Expressions for the velocity potential and the lift and moment are derived for thin, oscillating, arrowhead type wings with supersonic edges moving at a constant supersonic speed. The triangular wing and any one of the series of wings obtained from it by cutting its rearward part so that the flow normal to the resulting trailing edges remains supersonic are included in the term arrowhead type. Explicit results for the lift and moment are given for the wings undergoing harmonic pitching and...

Topics: DTIC Archive, Nelson, Herbert C, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC,...

The results of a study of the factors involved in the design of total-temperature probes for use at supersonic speeds have been applied to the design of an instrument to be used in wind-tunnel calibrations. Tests of the probe showed that the calibration factor required in the conversion of the measured temperature to the true total temperature was 0.992 +/- 0.002 for a range of Mach numbers between 1.36 and 2.01. The calibration factor was insensitive to angles of inclination relative to the...

Topics: DTIC Archive, Goldstein, David L, UNIVERSITY OF SOUTHERN CALIFORNIA LOS ANGELES AERONAUTICAL LAB,...

A comprehensive wind tunnel investigation on a cone-cylinder body with and without fins was conducted over a Mach number range of 2 to 4. The tests were conducted as a function of angle of attack varying from -5 to +15 at different roll orientations. The experimental programme consisted of flow visualization, aerodynamic force and moments, static pressure and flow velocity measurements taken in the DREV indraft wind tunnel. The wind tunnel had an up stream sting support system to conduct...

Topics: DTIC Archive, DEFENCE RESEARCH ESTABLISHMENT VALCARTIER (QUEBEC), *PROJECTILES, *WIND TUNNEL TESTS,...

METHOD IS DESCRIBED FOR CALIBRATING AIRSPEED INSTALLATIONS ON AIRPLANES AT TRANSONIC AND SUPERSONIC SPEEDS IN VERTICAL-PLANE MANEUVERS IN WHICH USE IS MADE OF MEASUREMENTS OF NORMAL AND LONGITUDINAL ACCELERATIONS AND ATTITUDE ANGLE. The method involves starting or ending a calibration run near level flight at a speed for which the airspeed calibration is known and hence for which the free-stream static pressure may be determined.

Topics: DTIC Archive, Zalovcik, John A, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC,...

Topics: DTIC Archive, EGGERS, JR , A J, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC,...

Topics: DTIC Archive, Nielsen, Jack N, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC,...

Guidelines for developing techniques for the prediction of fatigue and creep failure of supersonic aircraft structures. The solution of the problem of attaining adequate safety and reliability in supersonic aircraft structures operating under conditions under which the damaging effects of cycle sensitivity (fatigue) and time-sensitivity (creep) of the structural material combine in gradually reducing the resistance of the structure requires the de development of simplified procedures for the...

Topics: DTIC Archive, Freudenthal, A M, OHIO STATE UNIV COLUMBUS, *CREEP, *FATIGUE(MECHANICS),...

The work gives the results of an experimental investigation of acoustic emission of cavities of diverse configuration on a flat plate in a supersonic streamline flow of air at M = 1.7. From the investigation it is concluded that travelling waves on the interface result from the appearance of natural oscillations in a system consisting of the interface and the volume of air in the depression.

Topics: DTIC Archive, Morozov, M G, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSONAFB OH, *AERODYNAMIC NOISE,...

Topics: DTIC Archive, WEATHERILL, WARREN H., MASSACHUSETTS INST OF TECH CAMBRIDGE AEROELASTIC AND...

In this paper, the results of a series of experiments funded by DARPA to determine the feasibility of using small actuators to provide directional control for a supersonic projectile are presented. Controlling the flight of the projectile was accomplished by taking advantage of complex shock-boundary layer interactions produced by mechanical devices. One set of wind tunnel tests performed at the Georgia Tech Research Institute characterized the force levels produced by the small actuators on a...

Topics: DTIC Archive, Massey, K C, GEORGIA INST OF TECH ATLANTA, *WIND TUNNEL TESTS, *GUIDED PROJECTILES,...

This report details the development of electromagnetic probes for S, X, and K-band insertion loss studies on supersonic flames and of associated automatic VSWR equipment. Evaluation of the life of the probes is set forth, along with information on flame-loading of probes and certain insertion loss data taken with a 1500-lb oxygen-alcohol and a 400-lb acid-aniline motor.

Topics: DTIC Archive, Gager, F M, NAVAL RESEARCH LAB WASHINGTON DC, *FLAMES, *SUPERSONIC CHARACTERISTICS,...

This China Report contains articles on Science and Technology.

Topics: DTIC Archive, JOINT PUBLICATIONS RESEARCH SERVICE ARLINGTON VA, *FOREIGN TECHNOLOGY, *CHINA,...

Topics: DTIC Archive, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH, *HYPERSONIC CHARACTERISTICS,...

Topics: DTIC Archive, EPSTEIN, MELVIN, AERONAUTICAL SYSTEMS DIV WRIGHT-PATTERSON AFB OH FLIGHT CONTROL LAB,...

ODIN/MFV is a digital computing system for the synthesis and optimization of military flight vehicle preliminary designs. The system consists of a library of technology modules in the form of independent computer programs and an executive program, DIALOG, which operates on the technology modules. The technology module library contains programs for estimating military flight vehicle characteristics, for example, aerodynamics, trajectory and geometry. In addition a generalized optimization...

Topics: DTIC Archive, Hague, D S, AEROPHYSICS RESEARCH CORP BELLEVUE WA, *AEROSPACEPLANES, COMPUTER...

The study of detonation waves in a flowing combustible mixture of gas could lead to a better understanding of combustion instability in rocket motors and to possible application to supersonic combustion. Apparatus was designed to measure the relative wave velocity and to photograph the wave profile as a fully developed detonation wave propagated against a flow of stoichiometric mixture of hydrogen-oxygen gases. The Mach number of the flowing gas was varied from 0.14 to 4. The subsonic flow...

Topics: DTIC Archive, AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH, *COMBUSTION, *DETONATION WAVES,...

A test was conducted in a supersonic wind tunnel, to determine deployment characteristics and aerodynamic performance of disk-gap-band parachutes of various geometric porosities and ballutes with various ram-air inlet configurations. Deployments were made from a reentry-type model at nominal free-stream Mach numbers from 2.0 to 3.7 at a nominal free-stream dynamic pressure of 70 psf.

Topics: DTIC Archive, Galigher, Lawrence L, ARO INC ARNOLD AFS TN, *BALLUTES, *PARACHUTES, ATMOSPHERE...

A method is presented by which the pressure distribution on a slender, arbitrary body of revolution moving at supersonic speed at zero angle of attack may be calculated with an appreciable saving of time as compared with that required by other methods. The method was developed from the linearized potential-flow relations given by Jones and Margolis in NACA TN No. 1081 an(1 is essentially a graphical computing technique based on the assumption that a body may be represented satisfactorily by a...

Topics: DTIC Archive, Thompson, Jim R, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY...