Analytical shock jump formulae for cryogenic homogeneous two-phase nozzle flow

Download

index.pdf

Date

2000-08-01

Author

Akmandor, IS
Nagashima, T

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

164
views

0
downloads

Choked flux rates and shock jump relations were calculated both analytically and computationally for a converging-diverging nozzle. High inlet stagnation pressure with a maximum of 6.45 MPa was applied to the cryogenic vapor-liquid nitrogen flow. The total inlet-to-static exit pressure ratio range was between 3.5 and 15.3. The analytical shock jump expressions, which were derived, are exact extensions of the Rankine-Hugoniot single-phase gas dynamic relations. Accordingly, a consistent agreement was obtained between analytical and computational pressure, Mach number and void fraction shock jumps. The numerical mass flux values were also successfully compared with experimental data and two separate analytical results, both obtained from a modified Henry-Fauske model and a homogeneous mass flux equation.

Subject Keywords

Space and Planetary Science, Aerospace Engineering

URI

https://hdl.handle.net/11511/65052

Journal

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

DOI

https://doi.org/10.2322/tjsass.43.67

Collections

Department of Aerospace Engineering, Article

Suggestions

OpenMETU
Core

Computational study of subsonic flow over a delta canard-wing-body configuration Tuncer, İsmail Hakkı (American Institute of Aeronautics and Astronautics (AIAA), 1998-07-01) Subsonic flowfields over a close-coupled, delta canard-wing-body configuration at angles of attack of 20, 24,2, and 30 deg are computed using the OVERFLOW Navier-Stokes solver Computed flowfields are presented in terms of particle traces, surface streamlines, and leeward-side surface pressure distributions for the canard-on and -off configurations. The interaction between the canard and the wing vortices, wing vortex breakdown, and the influence of the canard on vortex breakdown are identified, The comparis...
Potential flow solutions with wakes over an ogive cylinder Tuncer, İsmail Hakkı (American Institute of Aeronautics and Astronautics (AIAA), 1998-05-01) An incompressible panel code is employed to compute the flow over an ogive cylinder body with an overall length of 7.5 diameter. Flow separation is modeled by vortex wakes attached to the base region and the leeward sides of the cylinder body. The computed surface pressures and integrated normal force and pitching-moment coefficients are found to be in good agreement with the experimental data up to 20-deg incidence. This favorable agreement suggests that the panel codes may be a computationally efficient t...
Non-parametric regional VTEC modeling with Multivariate Adaptive Regression B-Splines Durmaz, Murat; Karslıoğlu, Mahmut Onur (Elsevier BV, 2011-11-01) In this work Multivariate Adaptive Regression B-Splines (BMARS) is applied to regional spatio-temporal mapping of the Vertical Total Electron Content (VTEC) using ground based Global Positioning System (GPS) observations. BMARS is a non-parametric regression technique that utilizes compactly supported tensor product B-splines as basis functions, which are automatically obtained from the observations. The algorithm uses a scale-by-scale model building strategy that searches for B-splines at each scale fittin...
Short term variations of total electron content (TEC) fitting to a regional GPS network over the Kingdom of Saudi Arabia (KSA) Alothman, A. O.; Alsubaie, M. A.; Ayhan, M. E. (Elsevier BV, 2011-09-01) The ionosphere is a dispersive medium for radio waves with the refractive index which is a function of frequency and total electron content (TEC). TEC has a strong diurnal variation in addition to monthly, seasonal and solar cycle variations and small and large scale irregularities. Dual frequency GPS observations can be utilized to obtain TEC and investigate its spatial and temporal variations. We here studied short term TEC variations over the Kingdom of Saudi Arabia (KSA). A regional GPS network is forme...
Analysis of stability and trasitionin flat plate compressible boundary layers using linear stability theory Atalayer, H. Senem; Özge, Serkan; Department of Aerospace Engineering (2004) In this study, numerical investigations of stability and transition problems were performed for 2D compressible boundary layers over a flat plate in adiabatic wall condition. Emphasis was placed on linear stability theory. The mathematical formulation for 3D boundary layers with oblique waves including detailed theoretical information was followed by use of the numerical techniques for the solution of resulting differential system of the instability problem, consequently an eigenvalue problem. First, two-di...

Citation Formats

I. Akmandor and T. Nagashima, “Analytical shock jump formulae for cryogenic homogeneous two-phase nozzle flow,” TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, pp. 67–76, 2000, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/65052.