A First-Order Formulation of the Unsteady Supersonic Flow Problem for Finite Wings

1956 ◽  
Vol 23 (6) ◽  
pp. 578-582 ◽  
Author(s):  
JOHN W. MILES
Keyword(s):  
Supersonic Flow ◽  
Flow Problem ◽  
First Order ◽  
Unsteady Supersonic Flow

On the flow field of a rapidly oscillating airfoil in a supersonic flow

1974 ◽  
Vol 62 (4) ◽  
pp. 811-827 ◽  
Author(s):  
M. Kurosaka
Keyword(s):  
Supersonic Flow ◽  
Flow Field ◽  
Leading Edge ◽  
Flow Region ◽  
Relative Magnitude ◽  
Frequency Parameter ◽  
Unsteady Supersonic Flow ◽  
Long Time ◽  
Intimate Knowledge ◽  
Repeated Use

This paper examines the features of the flow field off the surface of an oscillating flat-plate airfoil immersed in a two-dimensional supersonic flow Although the exact linearized solution for a supersonic unsteady airfoil has been known for a long time, its expression in the form of an integral is not convenient for a physical interpretation. In the present paper, the quintessential features of the flow field are extracted from the exact solution by obtaining an asymptotic expansion in descending powers of a frequency parameter through the repeated use of the stationary-phase and steepest descent methods. It is found that the flow field consists of two dominant and competing signals: one is the acoustic ray or that component arising from Lighthill's ‘convecting slab’ and the other is the leading-edge disturbance propagating as a convecting wavelet. The flow field is found to be divided into several identifiable regions defined by the relative magnitude of the signals, and the asymptotic expansions appropriate for each flow region are derived along with their parametric restrictions. Such intimate knowledge of the flow field in unsteady, supersonic flow is of interest for interference aerodynamics and related acoustic problems.

Experimental study of unsteady supersonic flow interacting with porous cavity and jets or rods

2014 ◽  
Vol 23 (2) ◽  
pp. 153-159
Author(s):  
Nao Kuniyoshi ◽  
Minoru Yaga ◽  
Isao Teruya ◽  
Masaaki Ishikawa
Keyword(s):  
Experimental Study ◽  
Supersonic Flow ◽  
Porous Cavity ◽  
Unsteady Supersonic Flow

scholarly journals Unsteady Supersonic Flow

Nature ◽  
1960 ◽  
Vol 186 (4724) ◽  
pp. 505-506
Author(s):  
L. E. FRAENKEL
Keyword(s):  
Supersonic Flow ◽  
Unsteady Supersonic Flow

Higher-Order Solutions for Unsteady Hypersonic and Supersonic Flow

1974 ◽  
Vol 25 (1) ◽  
pp. 59-68 ◽  
Author(s):  
W H Hui ◽  
J Hamilton
Keyword(s):  
Shock Wave ◽  
Mach Number ◽  
Supersonic Flow ◽  
Power Series ◽  
Unsteady Flow ◽  
The Body ◽  
Wedge Flow ◽  
First Order ◽  
Order Solution ◽  
Method Of Solution

SummaryThe problem of unsteady hypersonic and supersonic flow with attached shock wave past wedge-like bodies is studied, using as a basis the assumption that the unsteady flow is a small perturbation from a steady uniform wedge flow. It is formulated in the most general case and applicable for any motion or deformation of the body. A method of solution to the perturbation equations is given by expanding the flow quantities in power series in M−2, M being the Mach number of the steady wedge flow. It is shown how solutions of successive orders in the series may be calculated. In particular, the second-order solution is given and shown to give improvements uniformly over the first-order solution.

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