scholarly journals Study of the coupling between real gas effects and rarefied effects on hypersonic aerodynamics

2012 ◽  
Author(s):  
Song Chen ◽  
Yuan Hu ◽  
Quanhua Sun
Keyword(s):  
Real Gas ◽  
Real Gas Effects ◽  
Hypersonic Aerodynamics

Problems of Hypersonic Aerodynamics— A Survey

1959 ◽  
Vol 63 (585) ◽  
pp. 489-492 ◽  
Author(s):  
R. J. Monaghan
Keyword(s):  
Hypersonic Flow ◽  
Three Dimensional ◽  
Separated Flow ◽  
Low Pressure ◽  
Aerodynamic Heating ◽  
Aerodynamic Efficiency ◽  
Real Gas ◽  
Pressure Drag ◽  
Real Gas Effects ◽  
Hypersonic Aerodynamics

SummaryReal gas effects are among the major complications of hypersonic flow and this is illustrated by examples of the temperatures and pressures attained when a flow is brought to rest. Once dissociation appears, these depend to a marked extent on the type of compression.In designing for the alleviation of aerodynamic heating there are two distinct cases. The first is the uncontrolled re-entry of a freely falling body, for which it is best to have a shape with a high pressure drag. The second is sustained flight, for which a shape with low pressure drag could be better, radiation giving appreciable control of surface temperature.Low pressure drag accords with design for aerodynamic efficiency and there is scope for research on three-dimensional lifting shapes. There is some discussion of this and also of the philosophy of securing maximum amounts of separated flow.Finally, there is continual emphasis on the need for experimental research, since hypersonic flow fields may differ considerably from those that would be expected by extrapolation of conventional supersonic experience.

Accuracy and Efficiency Assessments for a Weak Statement CFD Algorithm for High-Speed Aerodynamics

1992 ◽  
Author(s):  
G. S. Iannelli ◽  
A. J. Baker
Keyword(s):  
High Speed ◽  
Time Discretization ◽  
Matrix Product ◽  
Real Gas ◽  
Flow Characterization ◽  
Real Gas Effects ◽  
Arbitrary Convex ◽  
Layer Flow ◽  
Hypersonic Aerodynamics ◽  
Quasi Newton

A bilinear finite element, implicit Runge-Kutta space-time discretization has been established for an aerodynamics weak statement CFD algorithm. The algorithm admits real-gas effects simulation, for reliable hypersonic flow characterization, via an equilibrium reacting air model. The terminal algebraic system is solved using an efficient block-tridiagonal quasi-Newton linear algebra procedure that employs tensor matrix product factorizations within a lexicographic mesh-sweeping protocol. A block solution-adaptive remeshing, for totally arbitrary convex elements, is also utilized to facilitate accurate shock and/or boundary layer flow resolution. Numerical validations are presented for representative benchmark supersonic-hypersonic aerodynamics problem statements.

New Approximate Method for Calculating Real Gas Effects on Missile Configurations

1993 ◽  
Vol 30 (1) ◽  
pp. 22-31 ◽  
Author(s):  
F. G. Moore ◽  
M. J. Armistead ◽  
S. H. Rowles ◽  
F. R. DeJarnette
Keyword(s):  
Approximate Method ◽  
Real Gas ◽  
Real Gas Effects

Real Gas Effects in a Pulsed Laser Propulsion System

AIAA Journal ◽  
1978 ◽  
Vol 16 (12) ◽  
pp. 1309-1310 ◽  
Author(s):  
Sharad Chandra Purohit
Keyword(s):  
Pulsed Laser ◽  
Propulsion System ◽  
Real Gas ◽  
Laser Propulsion ◽  
Real Gas Effects

scholarly journals Sensitivity of Supersonic ORC Turbine Injector Designs to Fluctuating Operating Conditions

2015 ◽  
Author(s):  
Elio A. Bufi ◽  
Paola Cinnella ◽  
Xavier Merle
Keyword(s):  
Method Of Characteristics ◽  
Organic Rankine Cycle ◽  
Design Procedure ◽  
Rankine Cycle ◽  
Operating Conditions ◽  
Real Gas ◽  
Real Gas Effects ◽  
Nozzle Shape ◽  
Turbine Design ◽  
The Impact

The design of an efficient organic rankine cycle (ORC) expander needs to take properly into account strong real gas effects that may occur in given ranges of operating conditions, which can also be highly variable. In this work, we first design ORC turbine geometries by means of a fast 2-D design procedure based on the method of characteristics (MOC) for supersonic nozzles characterized by strong real gas effects. Thanks to a geometric post-processing procedure, the resulting nozzle shape is then adapted to generate an axial ORC blade vane geometry. Subsequently, the impact of uncertain operating conditions on turbine design is investigated by coupling the MOC algorithm with a Probabilistic Collocation Method (PCM) algorithm. Besides, the injector geometry generated at nominal operating conditions is simulated by means of an in-house CFD solver. The code is coupled to the PCM algorithm and a performance sensitivity analysis, in terms of adiabatic efficiency and power output, to variations of the operating conditions is carried out.

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