Perturbations of a transonic flow with vanishing shock waves

AIAA Journal ◽  
1985 ◽  
Vol 23 (6) ◽  
pp. 965-967 ◽  
Author(s):  
David Nixon ◽  
G. David Kerlick
Keyword(s):  
Shock Waves ◽  
Transonic Flow

Perturbation Procedures for Nonlinear Viscous Flows

1983 ◽  
Vol 50 (2) ◽  
pp. 265-269
Author(s):  
D. Nixon
Keyword(s):  
Perturbation Theory ◽  
Shock Waves ◽  
Transonic Flow ◽  
Stokes Equations ◽  
Viscous Flows ◽  
Two Dimensions ◽  
Experimental Results ◽  
Navier Stokes ◽  
Navier Stokes Equations

The perturbation theory for transonic flow is further developed for solutions of the Navier-Stokes equations in two dimensions or for experimental results. The strained coordinate technique is used to treat changes in location of any shock waves or large gradients.

scholarly journals ANALYSIS OF TRANSONIC FLOW PAST CUSPED AIRFOILS

2015 ◽  
Vol 55 (3) ◽  
pp. 193-198
Author(s):  
Jiří Stodůlka ◽  
Pavel Šafařík
Keyword(s):  
Shock Waves ◽  
Transonic Flow ◽  
Flow Behavior ◽  
Flow Past ◽  
Trailing Edges ◽  
Oblique Shocks

Transonic flow past two cusped airfoils is numerically solved and achieved results are analyzed by means of flow behavior and oblique shocks formation.Regions around sharp trailing edges are studied in detail and parameters of shock waves are solved and compared using classical shock polar approach and verified by reduction parameters for symmetric configurations.

Prediction of Viscous Effects in Steady Transonic Flow Past an Aerofoil

1979 ◽  
Vol 30 (3) ◽  
pp. 485-505 ◽  
Author(s):  
M.R. Collyer ◽  
R.C. Lock
Keyword(s):  
Boundary Layer ◽  
Shock Waves ◽  
Transonic Flow ◽  
Lift Coefficient ◽  
Inviscid Flow ◽  
Viscous Effects ◽  
Flow Past ◽  
Boundary Layer Development ◽  
Transition Position ◽  
Realistic Representation

SummaryAn account is given of a numerical method for calculating transonic flow past an aerofoil with an allowance for viscous effects, providing that the boundary layer remains fully attached over the aerofoil surface. The method has been developed by combining, in an iterative manner, calculations of the inviscid flow with calculations of the compressible boundary layer and wake. The solution for the inviscid flow is obtained by an iterative scheme, originally established by Garabedian & Korn, which has been modified to give a more realistic representation of shock waves. The boundary-layer development is treated as laminar initially; at a certain transition position a turbulent boundary layer is assumed to develop, and this is determined by the lag-entrainment method of Green et al. Comparisons of the results from the numerical scheme with some experimental measurements are shown for various examples in which shock waves of moderate strength are present. The method predicts, with reasonable accuracy, both the detailed pressure distribution and the variation of drag coefficient with lift coefficient.

Linearized Transonic Flow About Slender Bodies at Zero Angle of Attack

1961 ◽  
Vol 28 (4) ◽  
pp. 481-490 ◽  
Author(s):  
P. F. Maeder ◽  
H. U. Thommen
Keyword(s):  
Shock Waves ◽  
Transonic Flow ◽  
Angle Of Attack ◽  
Flow Theory ◽  
Theoretical Investigations ◽  
Slender Bodies

The simple linearized transonic flow theory as originally proposed by Oswatitsch and Keune [1] and by the present authors [2] is improved by considering and partially correcting its error. In this manner a theory which is easy to apply and which should be valid for a great number of smooth bodies is obtained. This improved theory predicts shock waves in the lower transonic regions. It is applied to a number of significant body and airfoil shapes and its predictions are compared with experiments and results of other theoretical investigations.

Analysis of Rotor-Rotor and Stator-Stator Interferences in Multi-Stage Turbomachines

2002 ◽  
Author(s):  
L. He ◽  
T. Chen ◽  
R. G. Wells ◽  
Y. S. Li ◽  
W. Ning
Keyword(s):  
Shock Waves ◽  
Flow Field ◽  
Transonic Flow ◽  
Subsonic Flow ◽  
Present Approach ◽  
Post Processing ◽  
Transonic Compressor ◽  
Multi Stage ◽  
Performance Variation

A nonlinear harmonic methodology is adopted to analyse interactions between adjacent stages in multi-stage compressors. Of particular interest are the effects of circumferential ‘aperiodic’ distributions and the relative circumferential positioning (‘clocking’) of blades. The main feature of the present approach is that both the aperiodic and clocking effects are very efficiently included with circumferential ‘steady’ harmonic disturbances. Consequently, a single run of the nonlinear harmonic solver using a single-passage domain can produce the whole annulus unsteady and aperiodic time-averaged flow field. In addition, performance variation at any clocking position can be obtained simply by post-processing the result. A case study is presented for a two and half stage transonic compressor, and the present results show much stronger rotor-rotor interaction than stator-stator interaction. A mechanism leading to strong rotor-rotor interference seems to be the interaction between upstream rotor wakes and the downstream rotor passage shock waves. A rotor-rotor clocking study illustrates a qualitatively different loss variation with respect to clocking position in a transonic flow compared to that in a subsonic flow.

Analysis of Rotor-Rotor and Stator-Stator Interferences in Multi-Stage Turbomachines

2002 ◽  
Vol 124 (4) ◽  
pp. 564-571 ◽  
Author(s):  
L. He ◽  
T. Chen ◽  
R. G. Wells ◽  
Y. S. Li ◽  
W. Ning
Keyword(s):  
Shock Waves ◽  
Flow Field ◽  
Transonic Flow ◽  
Subsonic Flow ◽  
Present Approach ◽  
Post Processing ◽  
Transonic Compressor ◽  
Multi Stage ◽  
Performance Variation

A nonlinear harmonic methodology is adopted to analyze interactions between adjacent stages in multi-stage compressors. Of particular interest are the effects of circumferential “aperiodic” distributions and the relative circumferential positioning (‘clocking’) of blades. The main feature of the present approach is that both the aperiodic and clocking effects are very efficiently included with circumferential “steady” harmonic disturbances. Consequently, a single run of the nonlinear harmonic solver using a single-passage domain can produce the whole annulus unsteady and aperiodic time-averaged flow field. In addition, performance variation at any clocking position can be obtained simply by post-processing the result. A case study is presented for a two-and-half-stage transonic compressor, and the present results show much stronger rotor-rotor interaction than stator-stator interaction. A mechanism leading to strong rotor-rotor interference seems to be the interaction between upstream rotor wakes and the downstream rotor passage shock waves. A rotor-rotor clocking study illustrates a qualitatively different loss variation with respect to clocking position in a transonic flow compared to that in a subsonic flow.

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