TY - GEN
T1 - Ethylene flame dynamics in an arc-heated hypersonic wind tunnel
AU - Do, H.
AU - Passaro, A.
AU - Liu, Q.
AU - Lee, T.
AU - Baccarella, D.
PY - 2013
Y1 - 2013
N2 - Ethylene flame dynamics in a model scramjet is investigated using a pulsed-arc-heated hypersonic wind tunnel simulating supersonic/hypersonic flight conditions (Mach 4.5, 6 and 9 flows of up to 3,500K stagnation temperature). A partially-premixed ethylene flame is auto-ignited with Mach 4.5, 6 and 9 freestream flows in a region downstream of a fuel jet where the high enthalpy flow is compressed and decelerated by incident/reflected shockwaves and development of boundary layers. This flame propagates upstream and anchores at a location depending on flow conditions. In the case of Mach 4.5 freestream flows, inlet unstart phenomenon is observed by excessive heat release from ethylene combustion reactions over a range of fuel concentration (overall equivalence ratio = 1.5 - 2.3). Flame evolution during a test time of hundreds milliseconds is optically resolved by a fast framing camera simultaneously with surface temperature/pressure measurement in the model scramjet. The pressure/temperature traces along with time-sequential flame images (300 Hz) describe the flame dynamics, e.g., flame propagation and flame holding near a wall cavity.
AB - Ethylene flame dynamics in a model scramjet is investigated using a pulsed-arc-heated hypersonic wind tunnel simulating supersonic/hypersonic flight conditions (Mach 4.5, 6 and 9 flows of up to 3,500K stagnation temperature). A partially-premixed ethylene flame is auto-ignited with Mach 4.5, 6 and 9 freestream flows in a region downstream of a fuel jet where the high enthalpy flow is compressed and decelerated by incident/reflected shockwaves and development of boundary layers. This flame propagates upstream and anchores at a location depending on flow conditions. In the case of Mach 4.5 freestream flows, inlet unstart phenomenon is observed by excessive heat release from ethylene combustion reactions over a range of fuel concentration (overall equivalence ratio = 1.5 - 2.3). Flame evolution during a test time of hundreds milliseconds is optically resolved by a fast framing camera simultaneously with surface temperature/pressure measurement in the model scramjet. The pressure/temperature traces along with time-sequential flame images (300 Hz) describe the flame dynamics, e.g., flame propagation and flame holding near a wall cavity.
UR - http://www.scopus.com/inward/record.url?scp=84881472804&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=84881472804&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:84881472804
SN - 9781624101816
T3 - 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013
BT - 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013
T2 - 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013
Y2 - 7 January 2013 through 10 January 2013
ER -