Thermodynamic performance analysis of the rotating detonative airbreathing combined cycle engine

Computational study on reducing flow asymmetry in over-expanded planar nozzle by incorporating double divergence

Inverse design method on scramjet nozzles based on maximum thrust theory

Optimization and analysis of inverse design method of maximum thrust scramjet nozzles

Over-expanded separation transitions of single expansion ramp nozzle in the accelerating and decelerating processes

Inverse design methodology on a single expansion ramp nozzle for scramjets

Experimental and numerical investigations of a scramjet nozzle at various operations

Experimental and numerical investigations on the mode transition process of an exhaust system for an over-under turbine based combined cycle

Design and performance analysis of an exhaust system for an over-under turbine based combined cycle operating at Mach 0–6

A high-temperature effect is crucial in cold-to-hot correlation for thrust nozzles to employ experimental data of cold flow to predict the real flight performance of hot gas. The high-temperature nozzle flow behaves beyond the classical gas dynamics and restricts the feasibility of cold-flow experiments, and it becomes more severe due to the species transformation from cold air to hot gas when safety and cost are considered. For an in-depth awareness, this work refines three fundamental issues regarding the high-temperature variable specific heat effect on nozzle flow characteristics. A comprehensive analysis is performed from theory to applications. First, the flow properties of calorically perfect gas (CPG) and thermally perfect gas (TPG) are distinguished and connected via the basic flow equations. One-dimensional flow theory is extended by the generalized stagnation–static gas functions for TPG. The unanticipated intersections within pressure are discovered, which could produce substantial perplexities in nozzle performance determinations. Second, the pros and cons of two homologous nozzle thrust coefficients are clarified on application objects, definition methods, and solution manners. It is proved that temperature has no influence on thrust coefficients for CPG, while the variable specific heat effect might induce three types of false-positive thrust coefficients, to make flow state unidentified, and further shake the baseline of nozzle performance. Third, for the aggravated variable specific heat effect in cold-to-hot correlation from air to hot gas, two methods are proposed with reliable verifications to solve this issue through introducing a novel concept of relative nozzle operating conditions.

Three issues on nozzle thrust performance in cold-to-hot correlation considering variable specific heat effect

Guangtao Song

Papers

Inverse design methodology on a single expansion ramp nozzle for scramjets

Experimental and numerical investigations of a scramjet nozzle at various operations

Experimental and numerical investigations on the mode transition process of an exhaust system for an over-under turbine based combined cycle

Design and performance analysis of an exhaust system for an over-under turbine based combined cycle operating at Mach 0–6

Three issues on nozzle thrust performance in cold-to-hot correlation considering variable specific heat effect