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Characterization of the supersonic wake of a generic space launcher

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Abstract

The wake flow of a generic axisymmetric space-launcher model is investigated experimentally for flow cases with and without propulsive jet to gain insight into the wake-flow phenomena at a supersonic stage of the flight trajectory which is especially critical with respect to dynamic loads on the structure. Measurements are performed at Mach 2.9 and a Reynolds number Re D  = 1.3 × 106 based on model diameter D. The nozzle exit velocity of the jet is at Mach 2.5, and the flow is moderately underexpanded (p e/p ∞ = 5.7). The flow topology is described based on velocity measurements in the wake by means of particle image velocimetry and schlieren visualizations. Mean and fluctuating mass-flux profiles are obtained from hot-wire measurements, and unsteady wall-pressure measurements on the main-body base are performed simultaneously. This way, the evolution of the wake flow and its spectral content can be observed along with the footprint of this highly dynamic flow on the launcher main-body base. For the case without propulsive jet, a large separated zone is forming downstream of the main body shoulder, and the flow is reattaching further downstream on the afterbody. The afterexpanding propulsive jet (air) causes a displacement of the shear layer away from the wall, preventing the reattachment of the flow. In the spectral analysis of the baseline case, a dominant frequency around St D  = 0.25 is found in the pressure-fluctuation signal at the main-body base of the launcher. This frequency is related to the shedding of the separation bubble and is less pronounced in the presence of the propulsive jet. In the shear layer itself, the spectra obtained from the hot-wire signal have a more broadband low-frequency content, which also reflects the characteristic frequency of turbulent structures convected in the shear layer, a swinging motion (St D  = 0.6), as well as the radial flapping motion of the shear layer (St D  = 0.85), respectively. Moving downstream along the shear layer, spectral content at slightly higher frequencies (St D  < 4) gets more pronounced and can be related to the shear layer instability process and the signature of smaller turbulent structures that appear in the wake.

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Fig. 1

Figure from Statnikov et al. [20]

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Abbreviations

D :

Model main-body diameter

d :

Diameter

f :

Frequency

M :

Mach number

p :

Pressure

r :

Radius

Re :

Reynolds number

St :

Strouhal number

T :

Temperature

U :

Mean velocity in the axial direction

V :

Mean velocity in the vertical direction

x :

Axial direction

y :

Radial direction

κ :

Specific heat ratio

ℜ :

Gas constant

δ :

Boundary-layer thickness

φ :

Radial angle in plain of main-body base

τ :

Hot-wire overheat ratio

ρu :

Mass flux

e:

Value at nozzle exit

max:

Maximum value

mean:

Mean value

Mol:

Molar mass

p :

Value in rocket plume

RK:

Value in HLB settling chamber

SC:

Value in TSA settling chamber

SP:

Value in HLB storage tube

t :

Absolute pressure/temperature

∞:

Value in free stream

AoI:

Area of interest

CCD:

Charge-coupled device

CTA:

Constant temperature anemometer

HLB:

Hypersonic Ludwieg tube Braunschweig

ISM:

Institute of Fluid Mechanics, TU Braunschweig

LES:

Large-eddy simulations

PIV:

Particle image velocimetry

PSD:

Power spectral density

RANS:

Reynolds-averaged Navier–Stokes eq

rms:

Root mean square

TIC:

Truncated ideal contour

TSA:

Jet-simulation facility

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Acknowledgments

The German Research Foundation DFG is gratefully acknowledged for funding this research in the framework of the Transregional Collaborative Research Center SFB-TR40 “Technological foundations for the design of thermally and mechanically highly loaded components of future space transportation systems”.

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Authors and Affiliations

  1. Institute of Fluid Mechanics, Technische Universität Braunschweig, Braunschweig, Germany

    A.-M. Schreyer, S. Stephan & R. Radespiel

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  1. A.-M. Schreyer
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  2. S. Stephan
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  3. R. Radespiel
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Correspondence to A.-M. Schreyer.

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Schreyer, AM., Stephan, S. & Radespiel, R. Characterization of the supersonic wake of a generic space launcher. CEAS Space J 9, 97–110 (2017). https://doi.org/10.1007/s12567-016-0134-4

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  • DOI: https://doi.org/10.1007/s12567-016-0134-4

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