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Andrew Hay Aerospace Engineering with German

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Experimental investigations of the flow during the stage separation of a space transportation system. Andrew Hay Aerospace Engineering with German. Project Brief. The ELAC 1 and EOS configuration is a two-stage-to-orbit space transportation system

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slide1

Experimental investigations of the flow during the stage separation of a space transportation system

Andrew Hay

Aerospace Engineering with German

slide2

Project Brief

  • The ELAC 1 and EOS configuration is a two-stage-to-orbit space transportation system
  • Stage separation occurs at Mach number Ma = 6.8 and at an altitude of 31 km
  • Flow visualisation - Oil flow pattern and colour Schlieren photography
  • Static wall pressure measurement
  • Identify aerodynamic interaction effects
slide3

Experimental Set-Up

  • 40cm x 40cm “Trisonic” Wind Tunnel
  • 1:150 scale EOS upper stage model and flat plate to simulate ELAC 1 lower stage
  • Test Parameters:
  • Freestream Mach number (Ma = 2.0 to 2.2)
  • Relative angle of attack (Δα = -5° to +10 °)
slide4

Test Geometry

  • Relative separation distance also planned but not possible
slide5

Flow Visualisation

  • Oil flow pattern - to visualise the near surface flow.Emulsion of oil and pigments move along wall shear stress flow lines.
  • Colour Schlieren photography - to visualise the shock system. Density gradients are made visible, because refraction index changes with density.

Pressure Measurement

  • Pressure coefficient Cp calculated from difference between static wall pressure p and ambient pressure p0.
slide6

Oil Flow Pattern

  • EOS bow shock impingement line on flat plate is visible
  • No shock induced boundary layer separation is visible
  • Reflected shock impingement line is not visible on EOS model
slide7

Colour Schlieren

  • Observed shock system very weak
  • Shock geometry used with shock theory to calculate flow conditions
  • Disturbances from flat plate very visible
slide8

Pressure Measurement

  • Shock impingement points visible (pressure increase)
  • Overall trend is a decrease in pressure downstream
  • Reason - 3D effects of the closed wind tunnel test section
slide9

Results Discussion

  • No boundary layer separation observed - confirmed by Schlieren and comparison with experimental data.
  • Shock systems very weak - shock intensities very close to 1
  • 3D effects of test section have a stronger influence on the pressure results than the shock system
  • Comparison of testing methods:All test methods consistent in providing location of shock impingement points. Schlieren is best for visualising system.
slide10

Conclusions

  • Shock systems visible, but very weak at tested Mach numbers
  • No shock induced boundary layer separation observed
  • 3D effects of the closed test section had a significant influence on the results
  • Improved test set-up is required to enable testing at more parameter variables
slide11

Experimental investigations of the flow during the stage separation of a space transportation system

Andrew Hay

Aerospace Engineering with German

slide15

Colour Schlierem Photo

Ma = 2.0  = +5° h = 40mm

slide16

Static Wall Pressure Measurement

Ma = 2.0  = +5° h = 40mm

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