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The prospect of atmospheric flight at five times the speed of sound, or greater, has captivated researchers for many years. One type of hypersonic propulsion engine capable of providing such astounding flight-speeds is the Dual-mode scramjet (DMSJ). This engine is especially attractive because a single flowpath is used over a wide range of flight Mach numbers. However, the complex combustion process in a DMSJ is not well understood. The flowfield of a DMSJ combustor is highly turbulent and highly threedimensional due to fuel injection schemes and massive flow separation. These characteristics, along with temperatures in excess of 1200K, make experimental measurements extremely challenging. Therefore, three-component velocity measurements for the combusting flow of a scramjet are currently lacking in the literature. Velocity measurements in a Dual-Mode Scramjet combustor would further understanding of this complicated flow by providing quantitative in-stream information and a benchmark data set that is needed to facilitate computational model validation. Classic probe-based measurement techniques are unacceptable for measuring the three-component velocity field of a DMSJ because these techniques alter the flowfield. However, a non-intrusive optical-based technique, such as Stereoscopic Particle Image Velocimetry (SPIV), is a candidate for velocity measurements in scramjet combustors. SPIV experiments have been undertaken at the University of Virginia’s Aerospace Research Laboratory in order to measure the flow inside a DMSJ for the case of fuel-air mixing prior to ignition and also for the case of fuel-air combustion. These experiments were conducted at several different measurement locations in two DMSJ combustors with different flowpath geometries, each containing a ramp fuel injector. Because of opposing

Stereoscopic Particle Image Velocimetry Measurements in Scramjet Combustors