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At least 919 records · Page 51
All sourcesNASA NTRSDOE OSTI
NASA NTRS1986

The computation of steady 3-D separated flows over aerodynamic bodies at incidence and yaw

This paper describes the implementation of a general purpose 3-D NS code and its application to simulated 3-D separated vortical flows over aerodynamic bodies. The thin-layer Reynolds-averaged NS equations are solved by an implicit approximate factorization scheme. The pencil data structure enables the code to run on very fine grids using only limited incore memories. Solutions of a low subsonic flow over an inclined ellipsoid are compared with experimental data to validate the code. Transonic flows over a yawed elliptical wing at incidence are computed and separations occurred at different yaw angles are discussed.

Pulliam, T. H.↗
NASA NTRS1986

A direct-inverse method for the prediction of transonic and separated flows about airfoils at high angles of attack

A direct-inverse technique and computer program called TAMSEP that can be used for the analysis of the flow about airfoils at subsonic and low transonic freestream velocities is presented. The method is based upon a direct-inverse nonconservative full potential inviscid method, a Thwaites laminar boundary layer technique, and the Barnwell turbulent momentum integral scheme; and it is formulated using Cartesian coordinates. Since the method utilizes inverse boundary conditions in regions of separated flow, it is suitable for predicting the flowfield about airfoils having trailing edge separated flow under high lift conditions. Comparisons with experimental data indicate that the method should be a useful tool for applied aerodynamic analyses.

Carlson, L. A.↗
NASA NTRS1986

Computation of separated flow on a ramp using the space marching conservative supra-characteristics method

Steady, hypersonic viscous flows over compression corners with streamwise separation have been computed using the space marching Conservative Supra-Characteristics Method (CSCM-S) of Lombard. The CSCM-S method permits stable space marching of the parabolized Navier-Stokes (PNS) equations through large separated flow regions. The present method has been used to compute surface pressure, heat transfer, and skin friction coefficients for two compression corner cases studied experimentally by Holden and Moselle. The computed results compare favorably with previous Navier-Stokes results and the experimental data. The present method has also been compared with the conventional Beam-Warming scheme for solving the PNS equations. Comparison are made for accuracy, computer time, and computer storage.

Stookesberry, D. C.↗
NASA NTRS1986

Numerical simulation of transonic separated flows over low-aspect ratio wings

Transonic flow fields about a low-aspect-ratio advanced technology wing have been computed using a viscous/inviscid zonal approach. The flow field near the wing where viscous effects are important was solved using the 'Reynolds-Averaged Navier-Stokes Equations' in 'thin-layer' form. The Euler equations were used to determine the flow field in regions away from the wing where viscous effects are insignificant. A zonal grid using an H-H topology was generated around the wing by first solving a set of Poisson's equations for the global grid. This grid was then subdivided into separate zones of viscous or inviscid flow as suggested by the flow physics. A series of flow cases were computed and compared with corresponding sets of experimental data. All cases showed good agreement with experiment in terms of the pressure field. Also, a good correlation between computed separated surface flow and experimental oil flow was obtained.

Kaynak, U.↗
NASA NTRS1986

Transonic, turbulent boundary-layer separation generated on an axisymmetric flow model

Experimental data describing the transonic, turbulent, separated flow generated by an axisymmetric flow model are presented. The model consisted of a circular-arc bump affixed to a straight, circular cylinder aligned with the flow direction. Measurements of the mean velocity, turbulence intensity, and Reynolds shear-stress profiles were made in the separated flow. These data revealed dramatic changes in the shear-stress levels as the flow passed through the interaction to reattachment. Behavior of the turbulence reaction to the imposed pressure gradients was examined in terms of the mixing length and the excursions of the turbulence from equilibrium.

Bachalo, W. D.↗
NASA NTRS1986

Numerical solution of the separating flow due to an obstruction

The steady separated flow due to an obstruction in a two-dimensional channel is studied through the numerical solution of the Navier-Stokes equations using finite difference techniques. The characteristics of the separated flow behind the obstruction are obtained up to a Reynolds number of 1500. The flow patterns, vorticity contours and total pressure contours are presented. The effects of Reynolds number, height of obstruction, thickness of obstruction and the inlet velocity profile are investigated.

Nallasamy, M.↗
NASA NTRS1986

Unsteady separated boundary layer in a transonic diffuser flow with self-excited oscillations

A numerical investigation of two-dimensional unsteady boundary layer in a transonic diffuser flow with self-excited oscillations and strong flow separation by solving the compressible, Reynolds-averaged, thin-layer Navier-Stokes equations with two-equations turbulence model is described. Three different meshes with constant streamwise mesh distribution and varying vertical mesh distribution were used. Results obtained indicate that a refinement of mesh studied here has minimal effect on the mean boundary layer flow but significantly increases the amplitude of oscillation of all flow variables. Comparisons of unsteady wall pressure, velocity profile, terminal shock, and separation pocket among computations and with experiment are presented.

Hsieh, T.↗
NASA NTRS1986

Aerospace nickel-cadmium cell separator qualifications program

The present space qualified nylon separator, Pellon 2505 ML, is no longer available for aerospace nickel-cadmium (NiCd) cells. As a result of this anticipated unavailability, a joint Government program between the Air Force Space Division and the Naval Research Laboratory was established. Four cell types were procured with both the old qualified and the new unqualified separators. Acceptance, characterization, and life cycling tests are to be performed at the Naval Weapons Support Center, Crane, Ind. (NWSC/Crane). The scheduling and current status of this program are discussed and the progress of testing and available results are projected.

Francis, R. W.↗
NASA NTRS1987

An experimental study of surface pressure fluctuations in a separating turbulent boundary layer

Measurements of streamwise velocity fluctuation and surface pressure fluctuation spectra and wavespeeds are reported for a well-documented separating turbulent boundary layer. Because a portion of the acoustic pressure fluctuations is the same across the nominally two-dimensional turbulent flow, it is possible to decompose two microphone signals and obtain directly the turbulent flow contributions to the surface pressure spectra. The rms surface pressure fluctuation p' and spectra phi(omega) increase through the adverse pressure gradient attached flow region and the detached flow zone and scale on the maximum turbulent shearing stress tau(M); p'/tau(M) increases to the detachment location and decreases downstream due to the rapid movement of the pressure-fluctuation-producing motions away from the wall after the beginning of intermittent backflow. At lower frequencies for the attached flow phi(omega) is approximately omega to the -0.7 while phi(omega) is approximately omega to the -3 at higher frequencies. After the beginning of intermittent backflow, phi(omega) varies with omega at low frequencies and omega to the -3 at high frequencies; farther downstream the lower frequency range varies with omega to the 2.4. The surface pressure fluctuation celerity for the attached flow increases with frequency and agrees with the semi-logarithmic overlap equation of Panton and Linebarger. After the beginning of the separation process, the wavespeed decreases because of the oscillation of the instantaneous wavespeed direction and the streamwise coherence decreases drastically.

Simpson, Roger L.↗
NASA NTRS1987

Electro-expulsive separation system

An electro-expulsive system has one or more overlapped conductors, each comprising a flexible ribbon conductor, which is folded back on itself. The conductors are embedded in an elastomeric material. Large current pulses are fed to the conductors from power storage units. As a result of the antiparallel currents, the opposed segments of a conductor are forcefully separated and the elastomeric material is distended. Voids in the elastomer aid the separation of the conductor segments. The distention is almost instantaneous when a current pulse reaches the conductor and the distention tends to remove any solid body on the surface of the elastomeric material.

Haslim, Leonard A.↗
NASA NTRS1987

Unsteady separated flows - Novel experimental approach

A novel experimental technique, commonly referred to as laser speckle velocimetry or particle image displacement velocimetry (PIDV), is developed for the measurement of instantaneous velocity fields in unsteady and steady flows. The main advantage of this technique is the fact that the velocity field is measured with sufficient accuracy so that the distribution of vorticity can be calculated with accuracy. The PIDV technique, which is ideally suited for the study of unsteady separated flows, has been utilized to measure the development of the separated flow field generated by a high angle-of-attack (alpha = 30 deg) NACA 0012 airfoil, started impulsively from rest.

Krothapalli, A.↗
NASA NTRS1986

A full CI treatment of the 1A1-3B1 separation in methylene

The accuracy of recent theoretical computations of the total energies and the adiabatic separation of the 1A1 and 3B1 states of CH2 is investigated on the basis of complete CI calculations using the double-zeta basis sets of Dunning (1970). The results are presented in a table and characterized in detail. The errors in the separation values are found to range from less than 0.01 kcal/mol for a CASSCF/MRSDCI calculation, to 0.38 kcal/mol for a Davidson-corrected SCF/SDCI calculation, to 14.17 kcal/mol for an uncorrected SCF calculation.

Bauschlicher, Charles W., Jr.↗
NASA NTRS1986

Separable two-dimensional discrete Hartley transform

Bracewell has proposed the Discrete Hartley Transform (DHT) as a substitute for the Discrete Fourier Transform (DFT), particularly as a means of convolution. Here, it is shown that the most natural extension of the DHT to two dimensions fails to be separate in the two dimensions, and is therefore inefficient. An alternative separable form is considered, corresponding convolution theorem is derived. That the DHT is unlikely to provide faster convolution than the DFT is also discussed.

Watson, Andrew B.↗
NASA NTRS1987

Transition from laminar to turbulent flow in separated shear layers

The location of boundary layer separation may be predicted by either semiempirical criteria or by various computer codes written for such calculations; attention is presently given to the streamwide length from separation to transition, denoted by Re(sL). It is demonstrated that the unit Reynolds number, a feature of the transition phenomenon implicit in the data of Schmidt et al. (1985) and overlooked in previous investigations, must be considered in future work.

Potter, J. Leith↗
NASA NTRS1987

Surface pressure fluctuations in a separating turbulent boundary layer

A novel, microphone-employing technique for the measurement of pressure fluctuations through pinhole apertures in the flow surface is used in the present study of separating boundary layer pressure fluctuation spectra and wavespeeds. The rms of the surface pressure fluctuation increases monotonically through the adverse-pressure gradient attached flow region and the detached flow zone. A correlation of the detached flow data is given which is derived from velocity and length scales of the separated flow. The celerity of the surface pressure fluctuations for the attached flow increases with frequency to a maximum, and the streamwise coherence decreases drastically after the begining of flow reversal.

Simpson, Roger L.↗
NASA NTRS1987

Advances in the computation of transonic separated flows over finite wings

The transonic flow around a low-aspect-ratio infinite wing in a wind tunnel is investigated by means of numerical simulations, with a focus on shock-induced separated flows. A coarse global grid with far-field boundaries matching those of the test section is subdivided into zones: the flow in the clustered zones near the wing is analyzed by solving the Reynolds-averaged Navier-Stokes equations, while that farther from the wing is modeled with the Euler equations. The results are presented graphically, and it is shown that a mushroomlike separated flow with two counterrotating vortices can be simulated when the correct shock strength is imposed (by careful selection of the artificial dissipation, the boundary conditions, the grid refinement, the algebraic turbulence model, and the geometry representation).

Kaynak, Unver↗
NASA NTRS1987

A numerical study of three-dimensional separated flow past a hemisphere cylinder

Separated and vortical flow about a hemisphere-cylinder body has been investigated. An algorithm featuring two implicit factors, and partial flux splitting has been used to solve the thin-layer Navier-Stokes equations. In analyzing the complex flow patterns, experimental data and topological concepts are used to complement the numerical results in interpreting the surface-flow patterns as well as the flowfield structures. Basic issues concerning the three-dimensional separation characteristics and the leeward vortical structures are examined.

Ying, Susan X.↗
NASA NTRS1987

On the 1A1 - 3B1 separation in CH2 and SiH2

The 1A1 - 3B1 separation in CH2 and SiH2 has been computed using extended basis sets and CASSCF/SOCI wave functions. Using theoretical estimates for the effects of zero-point vibration yields T(0) values of 8.9 and -20.9 kcal/mol respectively, in excellent agreement with the experimental values of 9.02 and -21.0 kcal/mol. A corollary to the small zero-point vibrational contribution to the separation is that the symmetric stretching fundamental in CH2(3B1) must be near 3100/cm, much less than a recently suggested value of around 3400/cm. An accurate Te value for SiH2 establishes the ionization potential of the 1A1 state as 9.15 eV, the higher of two recent experimental values.

Bauschlicher, Charles W., Jr.↗