Eighteenth Symposium on Naval Hydrodynamics (1991) / Chapter Skim
Currently Skimming:
A Navier-Stokes Solution of Hull-Ring Wing-Thruster Interaction
A Navier-Stokes Solution of Hull-Ring Wing-Thruster Interaction
Pages 687-696
The Chapter Skim interface presents what we've algorithmically identified as the most significant single chunk of text within every page in the chapter.
Select key terms on the right to highlight them within pages of the chapter.
From page 687... ...
Pressure and velocity components near the stern region were obtained computationally and are shown to compare favorably with the experimental data. The method correctly predicts the existence and extent of stern flow separation for the barebody and the absence of flow separation for the three other configurations with ring wing and/or propeller.
|
From page 688... ...
The propeller plane is located at 135 cm from the nose. The water tunnel in which the experiments were conducted has a square cross-section with round corners and its dimensions are 90 cm x 90 cm.
|
From page 689... ...
The L2 norm of the residual is often used as a measure of convergence of a solution. Letting the flux Jacobians A, B arid C be defined as follow A i3E" B OF" C JIG" - Em' - Ad' - 'am' discretize the inviscid and viscous fluxes according to upwind differencing scheme and central differencing scheme respectively in (, ~ and r1 coordinate direction independently and then assemble them together.
|
From page 690... ...
depends upon the inflow at the propeller plane which in turn is influenced by the blade circulation. This mu tual dependency implies that the body forces f be and f be which are functions of G(r)
|
From page 691... ...
Computational results are presented in the form of velocity profiles and pressure contours in the stern region; they are compared with available experimental data. In addition, to facilitate the flow visualization and discussion, computed particle trace are also included.
|
From page 692... ...
The experimental data presented in this paper are of foreign origin, obtained via informal correspondence.
|
From page 693... ...
0.60 0.50 0.40 0.30 0.20 _ 0.10 _ 0.00 _ -0.10 _ _ ._ -0.20 _ -0.30 _ -0.40 -0.50 _ -0.60 _ -0.70 _ -0.80 0.60 ' l · i , , i BAREBODY | ~ Experimental data | | Computational results | 0.65 0.70 0.75 0.80 o.ss 0.90 0.95 1.00 X/L Figure 4. Pressure Distribution on Stern Surface for Case 1 HAREBODY \ v .
|
From page 694... ...
Pressure contours in Stern Region for Case 2 ~ > Experimental data BODY WITII mNG WING ~ Computational results ~ == ~ = \ Figure 10. Velocity Vectors in Stern Region for Case 3 BODY Wll'll PROPEI,LER 0 Experimental data Computational results \ \ ,?
|
From page 695... ...
p~ln l / ; '~ ~ ': ~
|
From page 696... ...
AUTHORS' REPLY The differencing scheme presented in this paper is based on hyperbolic formulation, assuming that at high Reynolds numbers the behavior of Navier-Stokes equations becomes hyperbolic-like. At present, the solver has been used to simulate flow at Reynolds number 15 X 106.
|
Key Terms
This material may be derived from roughly machine-read images, and so is provided only to facilitate research.
More
information on Chapter Skim is available.