Secondary Gas Injection into a Supersonic Conical Nozzle

Masuya, Goro; Chinzei, Nobuo; Ishii, Shinichi

doi:10.2514/3.63234

Cited by 23 publications

(11 citation statements)

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“…The circular injection with inclination from the nozzle axis has been investigated experimentally by Nielson et al [19] and also by Masuya et al [18]. Nielson et al [19] performed the experiments on series of the circular sonic injections of f m ∼ 0.06 under di¨erent angles.…”

Section: Numerical Results Of the Truncated-ideal-contour Nozzle Testmentioning

confidence: 99%

“…In the presented experimental procedure, two conical nozzles with identical divergent sections and the two di¨erent second injection positions are investigated in the experiments; x j /x t = 0.7 similar to the experimental case of Masuya et al [18] and second one with injection at x j /x t = 0.9. With the aim to test system without additional pumps and with low-moderate mass- §ow ratio, secondary pressure ratio (SPR) is ranging up to unity value, while the secondary to primary mass- §ow ratio is varying around 5%.…”

Section: Geometry Of the Secondary Injectionmentioning

confidence: 99%

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Thrust vectoring effects of a transverse gas injection into a supersonic cross flow of an axisymmetric convergent-divergent nozzle

Zmijanović

Lago

Léger

et al. 2013

Progress in Propulsion Physics

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The transverse gas injection into the main supersonic §ow of an axisymmetric convergent-divergent (C-D) propulsive nozzle is investigated for the §uidic thrust vectoring (FTV) possibilities as the segment part of the CNES ¤Perseus¥ project. Truncated ideal contour and conical C-D nozzles with di¨erent position and angle of the secondary circular injection port are selected as test models in the current numerical and experimental study. Analytical approach revealed parameters which a¨ect the FTV e©ciency, these criterions are further numerically explored and results data of the conical nozzle test cases are compared and coupled with the ones from experiments. It is found that upstream inclined injection has positive e¨ect on vectoring capabilities and that with moderate secondary to primary mass- §ow ratios, ranging around 5%, pertinent vector side force is possible to be achieved. NOMENCLATURE AND ABBREVIATIONS2D two-dimensional 3D three-dimensional C d discharge coe©cient

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Section: Numerical Results Of the Truncated-ideal-contour Nozzle Testmentioning

confidence: 99%

Section: Geometry Of the Secondary Injectionmentioning

confidence: 99%

Thrust vectoring effects of a transverse gas injection into a supersonic cross flow of an axisymmetric convergent-divergent nozzle

Zmijanović

Lago

Léger

et al. 2013

Progress in Propulsion Physics

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“…Experimentally obtained results by Masuya 16 and numerical results are compared. Figure 1 shows a cutaway view of the convergent-divergent nozzle experimented on.…”

Section: Code Validationmentioning

confidence: 97%

“…Possible sources of this disagreement are the turbulence models incapable of re ning the ne-scale turbulence on the ow properties and a bias in the experimental values. 16 As was noted in the Ref. 15, no detailed measurement adjacent to the injection port was conducted.…”

Section: Code Validationmentioning

confidence: 99%

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Performance Analysis of Secondary Gas Injection into a Conical Rocket Nozzle

Yoon

2002

Journal of Propulsion and Power

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The effects of injection location of secondary jet and nozzle divergent cone angle on the performance of secondary gas injection for thrust vector control (SITVC) were numerically investigated.Three-dimensionalReynoldsaveraged Navier-Stokes equations with an algebraic turbulence model solved the complex three-dimensional nozzle ows perturbed by the secondary gas jet. The numerical code was properly validated by experiment. The results showed that downstream secondary jet injection and smaller nozzle divergent cone angles lead to higher ef ciencies over a wide range of pressure ratios. The occurrence of re ected shock waves severely lowers SITVC propulsion performance. Upstream jet injection is more effective in a narrow range of de ection. Nomenclature A = cross-sectional area C f = thrust coef cient E = total energy per unit volume F = thrust K = speci c impulse ratio M = Mach number m = mass ow rate p = pressure q i = heat ux Re = Reynolds number r = radius, radial coordinate T = temperature v i = velocity x = axial distance (axial coordinate) from the primary nozzle throat x J = axial distance of secondary injection ori ce x L = length of divergent section of primary nozzle Z = axial coordinate ® = divergent cone half-angle ± = Kronecker delta µ = circumferential coordinate ½ = density ¿ i j = stress tensor Subscripts a = ambient state e = exit condition i = inlet condition n = normal direction p = primary ow s = secondary jet t = primary nozzle throat w = wall 0 = reference (total) state Superscript T = transpose

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