Scramjet lift, thrust and pitching-moment characteristics measured in a shock tunnel

Robinson, M. J., Mee, D. J. and Paull, A. (2006) Scramjet lift, thrust and pitching-moment characteristics measured in a shock tunnel. Journal Of Propulsion And Power, 22 1: 85-95. doi:10.2514/1.15978


Author Robinson, M. J.
Mee, D. J.
Paull, A.
Title Scramjet lift, thrust and pitching-moment characteristics measured in a shock tunnel
Journal name Journal Of Propulsion And Power   Check publisher's open access policy
ISSN 0748-4658
Publication date 2006-01-01
Sub-type Article (original research)
DOI 10.2514/1.15978
Volume 22
Issue 1
Start page 85
End page 95
Total pages 11
Place of publication Reston
Publisher Amer Inst Aeronaut Astronaut
Language eng
Subject C1
290501 Mechanical Engineering
690302 Space transport
Abstract Lift, pitching moment, and thrust/drag on a supersonic combustion ramjet were measured in the T4 free-piston shock tunnel using a three-component stress-wave force balance. The scramjet model was 0.567 m long and weighed approximately 6 kg. Combustion occurred at a nozzle-supply enthalpy of 3.3 MJ/kg and nozzle-supply pressure of 32 MPa at Mach 6.6 for equivalence ratios up to 1.4. The force coefficients varied approximately linearly with equivalence ratio. The location of the center of pressure changed by 10% of the chord of the model over the range of equivalence ratios tested. Lift and pitching-moment coefficients remained constant when the nozzle-supply enthalpy was increased to 4.9 MJ/kg at an equivalence ratio of 0.8, but the thrust coefficient decreased rapidly. When the nozzle-supply pressure was reduced at a nozzle-supply enthalpy of 3.3 MJ/kg and an equivalence ratio of 0.8, the combustion-generated increment of lift and thrust was maintained at 26 MPa, but disappeared at 16 MPa. Measured lift and thrust forces agreed well with calculations made using a simplified force prediction model, but the measured pitching moment substantially exceeded predictions. Choking occurred at nozzle-supply enthalpies of less than 3.0 MJ/kg with an equivalence ratio of 0.8. The tests failed to yield a positive thrust because of the skin-friction drag that accounted for up to 50% of the fuel-off drag.
Keyword Engineering, Aerospace
3-component Force Balance
Boundary-layer
Flat-plate
Impulse Facilities
Heat Transfer
Engine
Combustion
Model
Transition
Q-Index Code C1

 
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Created: Wed, 15 Aug 2007, 19:12:34 EST