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Telionis, D. P.

Publications and source records attributed to Telionis, D. P..

15 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1993

The hemisphere-cylinder in dynamic pitch-up motions

Laser-Doppler velocimetry and seven-hole probes were employed to map out the velocity and vorticity field along a plane downstream of a hemisphere-cylinder. Steady flow data were obtained over a fixed model at a range of angles of attack, as well as over a model pitching through ramp motions to a final angle of attack. Attention was focused on the dynamic development of induced vortex asymmetry. It was found that the wake develops first in a symmetric fashion and asymmetry is generated with some time delay.

Panzer, E. C.↗
NASA NTRS1991

The dynamic character of the wake of an axisymmetric body at an angle of attack

The flow around a hemisphere-cylinder was studied at angles of attack alpha = 0-90 deg. The work was carried out in two wind tunnels, using hot wire anemometers and seven-hole probes at Reynolds number of 2.7 x 10 exp 4. Five distinct states of vortex unsteadiness were detected. For angles of attack less than 14 deg, the flow is rather stable. For alpha between 15 and 23 deg, meandering occurs at a reduced frequency of 0.065. For alpha between 24 and 32 deg, three frequencies were recorded at 0.11, 0.21, and 0.31. At even higher angles of attack, alpha between 33 and 41 deg, two frequencies were seen at 0.11 and 0.19. The onset of alternate shedding is at alpha = 42 deg, above which, alternate shedding occurred at 0.065. However, above 55 deg, shedding occurred at 0.15. Asymmetric wake structures over the hemisphere-cylinder were also investigated. It was found that asymmetric structures too are not steady but engage in periodic organized motions.

Hoang, N. T.↗
NASA NTRS1990

The hemisphere-cylinder at an angle of attack

The investigation of the flow over a cylinder with a hemispherical nose at an angle of attack is presented. Experiments were conducted in a 6 ft x 6 ft low-turbulence tunnel. The focus of this research is the separated region as well as the evaluation and testing of a new diagnostic tool, a fiber-optic laser-Doppler probe. A two-fold contribution is offered. On one hand, pressure distributions are provided along a fine grid over the body. On the other hand, a feasibility study is presented on the use of a fiber-optic LDV probe which can obtain data from inside the model.

Telionis, D. P.↗
NASA NTRS1986

The response of airfoils to periodic disturbances - The unsteady Kutta condition

Two cases of unsteady flowfields over a NACA 0012 airfoil at an angle of attack are examined. The first is the classical pitching motion about the airfoil's quarter chord. The second is the flow over a fixed airfoil immersed in the wake of the pitching airfoil. Large reduced frequencies are examined. Measurements were obtained in a water tunnel by laser Doppler velocimetry. Ensemble-averaged velocity measurements were obtained in the vicinity of the trailing edges of both the pitching and the fixed airfoil. The results indicate that the classical unsteady Kutta condition is clearly not valid. An extension of this condition earlier proposed by Giesing and Maskell is examined and some evidence is provided for its support.

Poling, D. R.↗
NASA NTRS1981

Unsteady boundary-layer injection

The boundary-layer equations for two-dimensional incompressible flow are integrated numerically for the flow over a flat plate and a Howarth body. Injection is introduced either impulsively or periodically along a narrow strip. Results indicate that injection perpendicular to the wall is transmitted instantly across the boundary layer and has little effect on the velocity profile parallel to the wall. The effect is a little more noticeable for flows with adverse pressure gradients. Injection parallel to the wall results in fuller velocity profiles. Parallel and oscillatory injection appears to influence the mean. The amplitude of oscillation decreases with distance from the injection strip but further downstream it increases again in a manner reminiscent of an unstable process.

Telionis, D. P.↗
NASA NTRS1974

Transmission of sound through annular ducts of varying cross sections and sheared mean flow

An asymptotic solution is presented for the transmission and attenuation of acoustic waves in an annular duct of slowly varying cross section which carries a sheared mean flow. The analysis also takes into account the growth of the boundary layer as well as any slow variations in the acoustic liner properties. The problem is reduced to the solution of a first-order ordinary differential equation for the amplitude. The analysis is used to estimate the effects of the variations of the duct cross section and boundary layer growth on the different acoustic modes.

Nayfeh, A. H.↗
NASA NTRS1974

Algebraically growing waves in ducts with sheared mean flow

Analysis of the behavior of standing and traveling acoustic waves in a smooth duct with a fluid flow having a sheared mean velocity profile, when the waves grow algebraically as they travel along the duct axis. It is shown that standing waves growing algebraically with the axial distance cannot exist in a smooth duct when the duct wall have a finite resistance. The existence of traveling waves subject to the same law of growth is also dismissed under realistic flow conditions.

Nayfeh, A. H.↗
NASA NTRS1973

Acoustic propagation in ducts with varying cross sections

The method of multiple scales is used to derive the equations that describe the spatial and temporal variation of the amplitudes and phases of a wave packet propagating in slowly varying hard-walled or lined ducts. The analysis is carried out for rectangular as well as circular ducts. These equations are statements of the conservation of energy. For large admittance or high-frequency modes, an approximate expression is obtained for the attenuation. This expression shows that all possible acoustic modes are attenuating. The results also show that decreasing the cross sectional area can lead to elimination of some of the acoustic modes.

Nayfeh, A. H.↗
NASA NTRS1973

Acoustic propagation in ducts with varying cross sections and sheared mean flow.

An analysis is presented of the wave propagation and attenuation in two-dimensional ducts with slowly varying cross sections which carry sheared mean flow. A uniformly valid asymptotic expansion of the acoustic waves is obtained in terms of the maximum slope of the wall by using the method of multiple scales. The result is a first-order differential equation describing the amplitude variation with the axial distance. This equation is used to evaluate the effects of variations of the duct cross section and growing boundary layers on the different acoustic modes.

Nayfeh, A. H.↗
NASA NTRS1973

The acoustics of aircraft engine-duct systems

Noise generated in aircraft engines is usually suppressed by acoustically treating the engine ducts. The optimization of this treatment requires an understanding of the transmission and attenuation of the acoustic waves. A critical review is presented of the state of the art regarding methods of determining the transmission and attenuation parameters and the effect on these parameters of (1) acoustic properties of liners, (2) the mean velocity, including uniform and shear profiles and nonparallel flow, (3) axial and transverse temperature gradients, (4) slowly and abruptly varying cross sections, and (5) finite-amplitude waves and nonlinear duct liners.

Nayfeh, A. H.↗
NASA NTRS1973

Algebraically growing waves in ducts with sheared mean flow

Standing or traveling waves which vary algebraically with the axial distance in uniform ducts with sheared mean velocity profiles are investigated. The results show that such waves are not possible for ducts with uniform cross sections and fully developed mean flows.

Nayfeh, A. H.↗
NASA NTRS1972

Heat transfer at reattachment of a compressible flow over a backward facing step with a suction slot.

A simplified model is suggested for engineering estimates of heat transfer in the vicinity of reattachment for the case of supersonic flow over a backward facing step with a suction slot. The presented approach gives a closed-form approximate solution which is shown to be in satisfactory agreement with experimental results for the case of no mass transfer, and is expected to predict the effect of mass transfer in the case of suction.

Telionis, D. P.↗