352
352

May 23, 2011
05/11

by
Fricke, Robert W., Jr

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STS-79 was the fourth of nine planned missions to the Russian Mir Space Station. This report summarizes the activities such as rendezvous and docking and spaceborne experiment operations. The report also discusses the Orbiter, External Tank (ET), Solid Rocket Boosters (SRB), Reusable Solid Rocket Motor (RSRM) and the space shuttle main engine (SSME) systems performance during the flight. The primary objectives of this flight were to rendezvous and dock with the Mir Space Station and exchange a...

Topics: ALGORITHMS, STRUCTURED GRIDS (MATHEMATICS), GRID GENERATION (MATHEMATICS), ERROR ANALYSIS, THREE...

Topics: DTIC Archive, PROBSTEIN, RONALD F., PRINCETON UNIV NJ JAMES FORRESTAL RESEARCH CENTER, *SUPERSONIC...

Topics: NASA Technical Reports Server (NTRS), SUPERSONIC AIRFOILS, TRANSONIC FLOW, UNSTEADY FLOW,...

The Supersonic Cruise Aircraft Research (SCAR) team analyzed six major topics: (1) aerodynamics, (2) stability and control, (3) propulsion, (4) environmental factor, (5) airframe structures and materials, and (6) design integration.

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CONFIGURATIONS, CONFERENCES, SUPERSONIC AIRCRAFT,...

An approximate linearized solution is presented for the wave drag and lift of an airfoil generated by rotating a thin supersonic profile about an axis parallel, or nearly parallel, to its chord. The aerodynamic coefficients are obtained from a surface distribution of sources, of strengths proportional to the local airfoil slopes, about a cylinder whose radius and chord equal those of the original ring airfoil. This source distribution satisfies the boundary conditions when the part of the wing...

Topics: DTIC Archive, Mirels, Harold, FLIGHT PROPULSION RESEARCH LAB CLEVELAND OH, *SUPERSONIC AIRFOILS,...

Topics: DTIC Archive, Martin, John C., Gerber, Nathan, ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND...

A program called TRANDES is presented that is used for the analysis of steady, irrotational transonic flow over specified two-dimensional airfoils in free air or for the design of airfoils having a prescribed pressure distribution, including the effects of weak viscous interaction. Instructions on program usage, listings of the program, and sample cases are given.

Topics: NASA Technical Reports Server (NTRS), COMPUTER PROGRAMS, FORTRAN, SUPERCRITICAL WINGS, SUPERSONIC...

585
585

Jul 21, 2010
07/10

by
Hancock, J. P

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The inlet duct test for the Propfan Testbed Assessment (PTA) program was completed in November 1984. The basic test duct was designed using the Lockheed QUADPAN computational code. Test objectives were to experimentally evaluate, modify as required, and eventually verify satisfactory performance as well as duct/engine compatibility. Measured total pressure recovery for the basic duct was 0.993 with no swirl and 0.989 for inflow with a 30 degree simulated swirl angle. This compared to a...

Topics: CAMBERED WINGS, LIFT, STATIC PRESSURE, WIND TUNNEL TESTS, REATTACHED FLOW, SUPERCRITICAL FLOW,...

The present paper derives Van Karman's Fourier integral method in supersonic wing theory directly from the basic concepts of the harmonic source and doublet. The method is first applied to investigate the general solution of the wave drag of a tapered swept wing with a symmetrical diamond airfoil profile. The general solution includes all kinds of wing plan forms which may be swept backward or forward, and tapered or reversely tapered to any ratio. A number of the limiting cases are also...

Topics: DTIC Archive, Chang, Chieh-Chien, JOHNS HOPKINS UNIV BALTIMORE MD, *SWEPT WINGS, *AERODYNAMIC DRAG,...

A new blade profile, RAE(NPL) 9615, has been developed for the Lynx helicopter using two-dimensional aerofoil tests. The complex nature of the rotor environment makes it essential to confirm that the designed improvements are realised in flight. The present tests, planned before the Lynx first flew, have simultaneously compared the new profile with the NACA 0012 profile in hovering flight. Each profile took the form of a fairing or 'glove' on a pair of opposing blades of the Wessex helicopter...

Topics: DTIC Archive, Riley,M J, AERONAUTICAL RESEARCH COUNCIL LONDON (ENGLAND), *ROTOR BLADES(ROTARY...

A numerical method, based on linearized theory, for designing minimum-drag supersonic wing camber surfaces of arbitrary planform for a given lift, with options for constraining the pitching moment and/or the surface deformation at the trailing edge of the root chord and for selecting any desired combination of eight specified wing-loading distributions to be employed in the optimization procedure is presented. Two examples are given to illustrate applications of the method. The results indicate...

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CONFIGURATIONS, AIRCRAFT DESIGN, SUPERSONIC...

An experimental and theoretical study was conducted to investigate the supersonic aerodynamic characteristics of delta and double-delta wings. Testing was conducted in the Langley Unitary Plan Wind Tunnel at Mach numbers of 1.60, 1.90, and 2.16. The double-delta wings exhibited lower zero-lift drag values than the delta wings having the same aspect ratio, whereas delta wings provided the lower drag due to lift. Deflections of the trailing-edge flaps for pitch control revealed that the induced...

Topics: NASA Technical Reports Server (NTRS), DELTA WINGS, SUPERSONIC AIRFOILS, SUPERSONIC FLOW, SWEPTBACK...

This paper describes experimental studies of leading edge boundary layer receptivity for imposed stream disturbances. Studies were conducted in the supersonic T-325 facility at ITAM and include data for both sharp and blunt leading edges. The data are in agreement with existing theory and should provide guidance for the development of more complete theories and numerical computations of this phenomena.

Topics: NASA Technical Reports Server (NTRS), BOUNDARY LAYERS, SHARP LEADING EDGES, DATA ACQUISITION, WIND...

Grid adaptation for structured meshes is the art of using information from an existing, but poorly resolved, solution to automatically redistribute the grid points in such a way as to improve the resolution in regions of high error, and thus the quality of the solution. This involves: (1) generate a grid vis some standard algorithm, (2) calculate a solution on this grid, (3) adapt the grid to this solution, (4) recalculate the solution on this adapted grid, and (5) repeat steps 3 and 4 to...

Topics: NASA Technical Reports Server (NTRS), ALGORITHMS, STRUCTURED GRIDS (MATHEMATICS), GRID GENERATION...

Some major milestones in the progression of airplane speeds from subsonic to supersonic are traced. Historical background is included on work done prior to the Twentieth Century, but the major emphasis is on the Twentieth Century developments after the man carrying airplane became a practical reality. The techniques of increasing airplane speed revolve around means of increasing the propulsive force and means of reducing the airframe resistance (drag). With the changes in speed, the attendant...

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CONFIGURATIONS, AIRCRAFT DESIGN, AIRSPEED,...

A method is presented for calculating the aerodynamic influence coefficients (AICs) based on third-order piston theory with an optional correction to agree with Van Dyke's quasi-steady second-order theory. The AICs are computed assuming the airfoil to have a rigid chord with or without a (rigid chord) control surface. The influence coefficients relate the surface deflections to the aerodynamic forces through. The piston theory is limited to high Mach number (or high reduced frequency), but Van...

Topics: DTIC Archive, Rodden, William P, AEROSPACE CORP EL SEGUNDO CA, *SUPERSONIC AIRFOILS, *WINGS,...

255
255

Jul 12, 2010
07/10

by
Macdougall, J. D.; Gopalan, K.; Lugmair, G. W.; Roy, A. B

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Data from an initial set of Banded Gneiss Complex (BGC) east of the city of Udaipur are given. In this region the BGC comprises typical grey gneiss with variably abundant granitic and mafic components. Efforts to date were concentrated on the mafic components which, based on chemical data, appear to be metavolcanic. All samples examined were recrystallized under amphibolite or upper amphibolite facies conditions. Pertinent chemical data for a small number of amphibolites analyzed so far are:...

Topics: APPROXIMATION, CARTESIAN COORDINATES, EIGENVECTORS, EULER EQUATIONS OF MOTION, SHOCK WAVES,...

Through the empirical correlation of experimental data and theoretical analysis, a set of graphs has been developed which summarize the inviscid aerodynamics of delta wings at supersonic speeds. The various graphs which detail the aerodynamic performance of delta wings at both zero-lift and lifting conditions were then employed to define a preliminary wing design approach in which both the low-lift and high-lift design criteria were combined to define a feasible design space.

Topics: NASA Technical Reports Server (NTRS), AERODYNAMICS, DELTA WINGS, INVISCID FLOW, SUPERSONIC...

The input data required to execute the computer program ISCON are described. The program generates a numerical procedure for the determination of unsteady aerodynamic forces on arbitrarily interacting wings and tails in supersonic flow. A velocity potential gradient method is used. Constant Mach number is assumed throughout the flow field. Lifting surfaces are represented by trapezoidal elements which can be generated automatically by the program. The wake field is represented by rectangular...

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC FORCES, COMPUTER PROGRAMS, SUPERSONIC AIRFOILS,...

Heat transfer and pressure distributions have been obtained on a two- dimensional symmetric body designed to reduce heat transfer rates at the stagnation point. Theoretical and experimental pressure distributions indicate a large reduction in velocity gradients at the stagnation point. Experimental heat transfer results at the high angles of attack (a equals 30 degrees) indicate a 15 - 20% reduction from the two-dimensional stagnation point heat transfer. Further investigation at the higher...

Topics: DTIC Archive, SEIDMAN, MITCHELL, GENERAL APPLIED SCIENCE LABS INC HEMPSTEAD NY, *HEAT TRANSFER,...

In order to have a high level of maneuverability, supersonic delta wings should have a cross flow that is free of embedded shock waves. The conical cross flow sonic surface differs from that of plane transonic flow in many aspects. Well-known properties such as the monotone law are not true for conical cross flow sonic surfaces. By using a local analysis of the cross flow sonic line, relevant conditions for smooth cross flow are obtained. A technique to artificially construct a smooth sonic...

Topics: NASA Technical Reports Server (NTRS), CAMBER, CROSS FLOW, DELTA WINGS, POTENTIAL FLOW, SHOCK WAVES,...

A theoretical and experimental investigation was conducted to assess the effect of leading-edge load constraints on supersonic wing design and performance. In the effort to delay flow separation and the formation of leading-edge vortices, two constrained, linear-theory optimization approaches were used to limit the loadings on the leading edge of a variable-sweep planform design. Experimental force and moment tests were made on two constrained camber wings, a flat uncambered wing, and an...

Topics: NASA Technical Reports Server (NTRS), BOUNDARY LAYER SEPARATION, SUPERSONIC AIRFOILS, SUPERSONIC...

This bibliography, with abstracts, consists of 69 publications arranged in chronological order. The material may be useful to those interested in supersonic cruise fighter/penetrator/interceptor airplanes. Two pertinent conferences on military supercruise aircraft are considered as single items; one contains 37 papers and the other 29 papers. In addition, several related bibliographies are included which cover supersonic civil aircraft and military aircraft studies at the Langley Research...

Topics: NASA Technical Reports Server (NTRS), AIRCRAFT DESIGN, FIGHTER AIRCRAFT, MILITARY AVIATION,...

The use of a sensitivity equation method to computer derivatives for optimization based design algorithms are discussed. The problem of designing an optimal forebody simulator is used to motivate the algorithm and to illustrate the basic ideas. Finally, how an existing computational fluid dynamics (CFD) code can be modified to compute sensitivities and a numerical example is presented.

Topics: NASA Technical Reports Server (NTRS), COMPUTATIONAL FLUID DYNAMICS, FOREBODIES, OPTIMIZATION,...

443
443

Jul 12, 2010
07/10

by
Weaver, E. A.; Bilbro, J. W.; Dunkin, J. A.; Johnson, S. C.; Jones, W. D.; Harris, C. E.; Dimarzio, C. A

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A pulsed C02 Doppler lidar system is described and demonstration tests in ground-based and airborne flight operations are discussed. As a ground-based system, it can detect wind shears in thunderstorm gust fronts to a range of 6 km. When in the airborne configuration, the lidar can detect clear air turbulence in advance of the aircraft encountering clear air turbulence. The data provided by the lidar included turbulence location and intensity with intensity being indicated by the measured...

Topics: AERODYNAMICS, AERODYNAMIC CONFIGURATIONS, COMPRESSIBLE FLOW, CRITICAL VELOCITY, FLOW THEORY, MACH...

Past studies of reentry vehicles tested to high angles of attack (up to 90 deg) in the Mach number range from 2 to 4.8 are reviewed. Two basic planforms are considered: highly-swept deltas and circular. The delta concepts include variations in cross section (and thus volume) and in camber distribution. The effectiveness of various types of aerodynamic control devices is also included. The purpose of the paper is to examine the characteristics of the vehicles with a view toward the potential...

Topics: NASA Technical Reports Server (NTRS), ANGLE OF ATTACK, CAMBERED WINGS, CIRCULAR CONES, DELTA WINGS,...

A theoretical study was made of supersonic wing geometries at Mach 1.8, using the attainable leading-edge thrust concept. The attainable thrust method offers a powerful means to improve overall aerodynamic efficiency by identifying wing leading-edge geometries that promote attached flow and by defining a local angle-of-attack range over which attached flow may be obtained. The concept applies to flat and to cambered wings, which leads to the consideration of drooped-wing leading edges for...

Topics: NASA Technical Reports Server (NTRS), LEADING EDGE THRUST, SUCTION, SUPERSONIC AIRFOILS, THRUST...

A review is made of a method for computing the aerodynamic influence coefficients (AICs) for surfaces with supersonic leading edges. The method is based on the two-dimensional secondorder potential solution of Van Dyke. The strip oscillatory coefficients are obtained from the extension of Van Dyke's work by Rodden and Revell to include the effects of sweep and finite span in addition to the effects of thickness, leading to a method that will avoid the unconservation of linearized theory and...

Topics: DTIC Archive, Rodden, William P, AEROSPACE CORP EL SEGUNDO CA, *SUPERSONIC AIRFOILS, *WINGS,...

A body-fitted grid embedment technique applicable to inviscid transonic airfoil flow field analysis was developed and verified through a series of tests. Test cases used to verify the technique show that the accuracy of the solution was increased by grid embedding. This enhancement of the solution is especially true when small supercritical zones occur which cannot be adequately described using the main grid only. Results obtained with the SKANFP full potential program are considered with...

Topics: NASA Technical Reports Server (NTRS), AIRFOIL PROFILES, BOUNDARY LAYER FLOW, COMPUTATIONAL FLUID...

Tests were conducted on a 0.5 hub/tip ratio single-stage fan designed to produce a pressure ratio of 2.280 at an efficiency of 83.8 percent with a rotor tip speed of 548.6 m/sec (1800 ft/sec). The rotor was designed utilizing a quasi three dimensional design system and four-part, multiple-circular-arc airfoil sections. The rotor is the third in a series of single-stage fans that have included a precompression airfoil design and a multiple-circular-arc airfoil design. The stage achieved a peak...

Topics: NASA Technical Reports Server (NTRS), AIRFOIL PROFILES, BLADE TIPS, COMPRESSOR ROTORS, FAN BLADES,...

Experimental/theoretical correlations are presented which show that significant levels of leading-edge thrust are possible at supersonic speeds for certain planforms having the geometry to support the theoretical thrust-distribution potential. The new analytical process employed provides not only the level of leading-edge thrust attainable but also the spanwise distribution of both it and that component of full theoretical thrust which acts as vortex lift. Significantly improved aerodynamic...

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, LEADING EDGE SWEEP, SUPERSONIC...

An analysis of a caseless and nozzleless solid-propellant rocket motor employing the external burning concept was made. Performance was calculated for a wide range of supersonic flight conditions. The results of the analysis show that acceptable values of specific impulse and thrust are possible for propellants having sufficiently high burn rates in a base burning configuration. The effect of boattailing with combustion along the boattail was investigated and found to degrade the performance....

Topics: DTIC Archive, Willbanks, C E, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *SOLID...

Ventral fin loads, expressed as normal force coefficients, bending moment coefficients, and torque coefficients, were measured during flight tests of a YF-12A airplane. Because of the proximity of the ventral fin to the ailerons, the aerodynamic loads presented were the result of both sideslip loads and aileron crossflow loads. Aerodynamic data obtained from strain gage loads instrumentation and some flight pressure measurements are presented for several Mach numbers ranging from 0.70 to 2.00....

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC LOADS, FLIGHT TESTS, LOW ASPECT RATIO,...

Further wind tunnel tests have been carried out on the NAE 10 in. chord supercritical NLF airfoil NAE 68-060-21:1. In previous tests, this airfoil showed very low drag levels when free transition was allowed on the model. In the main part of about 7,9 and 13 million, transition was fixed at 7% and 15% on upper and lower surfaces respectively. It is observed that there is a substantial loss of lift under these conditions which appears to be associated with boundary layer thickening on the lower...

Topics: DTIC Archive, Khalid,M, NATIONAL AERONAUTICAL ESTABLISHMENT OTTAWA (ONTARIO), *SUPERCRITICAL...

Four advanced fighter configurations, which differed in wing planform and airfoil shape, were investigated in the Langley Unitary Plan Wind Tunnel at Mach numbers of 1.60, 1.80, 2.00, and 2.16. Supersonic data were obtained on the four uncambered wings, which were each attached to a single fighter fuselage. The fuselage geometry varied in cross-sectional shape and had two side-mounted, flow-through, half-axisymmetric inlets. Twin vertical tails were attached to the fuselage. The four planforms...

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CHARACTERISTICS, AIRCRAFT CONFIGURATIONS, FIGHTER...

Results of the experimental validation are presented for the three dimensional cambered wing which was designed to achieve attached supercritical cross flow for lifting conditions typical of supersonic maneuver. The design point was a lift coefficient of 0.4 at Mach 1.62 and 12 deg angle of attack. Results from the nonlinear full potential method are presented to show the validity of the design process along with results from linear theory codes. Longitudinal force and moment data and static...

Topics: NASA Technical Reports Server (NTRS), CAMBERED WINGS, REATTACHED FLOW, SUPERCRITICAL FLOW,...

The supersonic flow field over a rearward facing step was studied with a schlieren system. The effect of Mach number variation, step height variation, and total pressure variation on the expansion fan angle, lip shock angle, flow turning angle, reattachment point, and reattachment shock angle was determined. Schlieren photographs of the flow at Mach number 2.7 to 3.1, step heights of 1/4 to 3/4 in, and total pressures of 60 to 95 psia are presented. It was found that the relatively small...

Topics: DTIC Archive, Waters, Albert L, AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF...

A method is developed consistent with the assumptions of small perturbation theory, which provides a means of determining the downwash behind a wing in supersonic flow for a known load distribution. The analysis is based upon the use of supersonic doublets which are distributed over the plan form and wake of the wing in a manner determined from the wing loading. The first application of the method proves the equivalence in subsonic and supersonic flow of the downwash at infinity corresponding...

Topics: DTIC Archive, Heaslet, Max A, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES...

This Digest covers unclassified research in aeronautics performed at the United States Air Force Academy during the six months ending 15 July 1981. This report includes technical papers in the specific areas of aerodynamics, propulsion, experimental instrumentation, engineering education, and aeronautical history. Topics include: The Mass Flux Surface Boundary Condition for Linarized Potential Flow; A Numerical Investigation of the Effects of Fin Planform Parameters on the Subsonic Cruise...

Topics: DTIC Archive, Higgins,A M, AIR FORCE ACADEMY CO, *Aeronautics, Air Force research, Potential flow,...

Supersonic aircraft design is a computationally expensive optimization problem and multifidelity approaches over a significant opportunity to reduce design time and computational cost. This report presents tools developed to improve supersonic aircraft design capabilities including: aerodynamic tools for supersonic aircraft configurations; a systematic way to manage model uncertainty; and multifidelity model management concepts that incorporate uncertainty. The aerodynamic analysis tools...

Topics: NASA Technical Reports Server (NTRS), SUPERSONIC AIRCRAFT, AERODYNAMIC CHARACTERISTICS, DESIGN...

The variation of pressure distribution is calculated for a two-dimensional supersonic airfoil either experiencing a sudden angle-of- attack change or entering a sharp-edged gust. From these pressure distributions the indicial lift functions applicable to unsteady lift problems are determined for the two cases. A close similarity is shown to exist between the calculated functions for varying free-stream Mach number and the corresponding functions in three-dimensional incompressible flow for...

Topics: DTIC Archive, Heaslet, Max A, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES...

The three dimensional off design flow fields are calculated for stream Mach numbers in the range 1.3 tgo 4.0 and corresponding to attached and detached shocks at the leading edges of a reentrant pyramidal waverider geometry. The MacCormack shock capturing version of the Lax-Wendroff finite difference technique is used with grids chosen to align with surface, symmetry and approximate shock traces in the transverse plane. Separate natural grid systems are defined for the compression and expansion...

Topics: DTIC Archive, Baron,Judson R, MASSACHUSETTS INST OF TECH CAMBRIDGE FLUID DYNAMICS RESEARCH LAB,...

An exact theoretical method is developed that permits the determination of the pressure field of a wing-body combination having a circular body and a wing with supersonic leading and trailing edges. Detailed calculations have been performed for wing-body combinations composed of rectangular wings mounted at incidence on bodies at zero angle of attack for effective chord-radius ratios of 4 or less. For large effective chord-radius ratios some asymptotic results have been obtained. It was...

Topics: DTIC Archive, Nielsen, Jack N, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES...

A series of simple theoretical models are discussed, representing the essential features of flexible aircraft both of the classical and integrated varieties, in trimmed level flight. Assuming linear aerodynamics it is shown that the maximum speed for trimmed flight for the classical aircraft is determined primarily by the tail-plane flexibility. For the integrated aircraft this maximum speed occurs when both the overall aeroelastic distortion and the control forces become very large, the...

Topics: DTIC Archive, Hancock, G J, ADVISORY GROUP FOR AERONAUTICAL RESEARCH AND DEVELOPMENT PARIS...

Steady flow about curved airfoils is investigated analytically at high supersonic speeds. Assuming air behaves as an ideal diatomic gas, it is found that small pressure disturbances emanating from the surface of an airfoil are almost completely absorbed in the leading-edge shock wave (or a shock wave emanating from any other location on the surface), provided the flow deflection angles are not too close to those corresponding to shock detachment. This result is found to be essentially...

Topics: DTIC Archive, Eggers, A J , Jr, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES...

A class of conservative difference approximations for the steady full potential equation was presented. They are, in general, easier to program than the usual density biasing algorithms, and in fact, differ only slightly from them. Rigorous proof indicated that these new schemes satisfied a new discrete entropy inequality, which ruled out expansion shocks, and that they have sharp, steady, discrete shocks. A key tool in the analysis is the construction of a new entropy inequality for the full...

Topics: NASA Technical Reports Server (NTRS), APPROXIMATION, CONSERVATION EQUATIONS, ENTROPY, FLOW...

Contents: Steady Transonic Tunnel Wall Interactions and Far Fields; Unsteady Tunnel Wall Interference Effects; Studies of Transonic Slender Body Flows. (Author)

Topics: DTIC Archive, Malmuth,N D, ROCKWELL INTERNATIONAL THOUSAND OAKS CA SCIENCE CENTER, *AIR FLOW,...

The flow characteristics behind weak stationary shock waves reflected from various edges lying in the mainstream direction are determined according to linearized theory. Five different types of edges are considered, made up of various combinations of solid and free plane surfaces. An assumption regarding the singularity of one of the perturbation velocity is required in order to render the solutions unique. By superposition of such basic 'edge' solutions, the flow behind a shock wave reflected...

Topics: DTIC Archive, Sun, T. F., CORNELL UNIV ITHACA NY GRADUATE SCHOOLOF AEROSPACE ENGINEERING, *SHOCK...

This paper describes the implementation of optimization techniques based on control theory for wing and wing-body design of supersonic configurations. The work represents an extension of our earlier research in which control theory is used to devise a design procedure that significantly reduces the computational cost by employing an adjoint equation. In previous studies it was shown that control theory could be used to~eviseransonic design methods for airfoils and wings in which the shape and...

Topics: NASA Technical Reports Server (NTRS), AERODYNAMIC CONFIGURATIONS, AIRCRAFT DESIGN, BODY-WING...

Contents: Some Precise Solutions for Wings with Supersonic Edges with Arbitrary Time Dependences; Procedure of Calculation of the Aerodynamic Wing Characteristics of Arbitrary Planform; Practical Applications; Special Features of the Practical Use of Duhamel Integral in Tasks of Aerodynamics; Approximation Method; Coefficients of the Aerodynamic Derivative and of Apparent Additional Masses; Some Common Properties of Unsteady Effect of Planform, Numbers M and p* on the Aerodynamic Derivatives of...

Topics: DTIC Archive, Belotserkovskiy,S M, FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO, *AERODYNAMIC...