Experimental Verification of the Aerodynamics of Stream Thrust Probes

Hiers, Robert S.; Sirbaugh, J. R.; McCann, Capt Barrett T.; Cummings, Russell M.; Luft, Cadet Laura S.; Grillos, Cadet Dimitrios P.

doi:10.2514/6.2005-1215

Cited by 2 publications

(2 citation statements)

References 2 publications

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“…When testing the probe model discussed in Hiers et al 1,2,3 in CFD simulations, a consistent difference of around one percent was noticed between inviscid-flow predictions and the experimental data. To explain this difference, two main factors were examined.…”

Section: Second-order Boundary Layer Theorymentioning

confidence: 99%

The Influence of Viscosity and Surface Curvature on the Pressure Distribution of a Stream Thrust Probe

Pasman

Cummings

2006

44th AIAA Aerospace Sciences Meeting and Exhibit

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Determining the local stream thrust (a vector quantity) from a measured pitot pressure (a scalar quantity) requires either knowledge of the flow direction, or a probe shape that compensates for flow direction. This compensation would ideally make the measured pressure directly proportional to the component of momentum along the probe axis. The flow angle sensitivity required to resolve this component of momentum was determined theoretically previously. A proposed probe nose shape was analyzed using CFD and found to produce flow angle sensitivity close to the required sensitivity. The proposed nose shape was also tested in a wind tunnel at Mach 1.67, 2.45, and 3.48 at angles of attack from 0 to 15 degrees. The test results indicate that the flow angle sensitivity of the proposed nose shape agrees with the required sensitivity to within 1% up to a flow angle of 15°. The current work extends the original theoretical development for the optimum nose shape to include viscous affects and surface curvature. The new second-order theory agrees well with experimental results for both the stream thrust probe as well as other, independent data. Further work can be done to refine the theory.

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Section: Second-order Boundary Layer Theorymentioning

confidence: 99%

The Influence of Viscosity and Surface Curvature on the Pressure Distribution of a Stream Thrust Probe

Pasman

Cummings

2006

44th AIAA Aerospace Sciences Meeting and Exhibit

Self Cite

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“…Demarcation of internal and external performance of the engine for a single experiment would be useful and possible through the measurement of stream-thrust at the engine nozzle exit (in addition to the force balance). This methodology has previously been proposed by Voland (1990) and more recently Hiers et al (2005) have investigated the development of a suitable probe. Since it provides an independent method for the estimation of internal thrust, the measurement of the nozzle exit stream-thrust would also be of use during complete engine tests which do not use a force balance.…”

Section: Sr3mentioning

confidence: 99%

An experimental investigation of an airframe integrated three-dimensional scramjet engine at a Mach 10 flight condition

Doherty¹

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The University of Queensland in 2014 school of mechanical and mining engineering centre for hypersonics abstract Realisation of the dream of airbreathing access-to-space requires the development of a scramjet engine that produces sufficient net thrust to enable acceleration over a wide Mach number range. With engines that are highly integrated with the airframe, the net performance of a scramjet powered vehicle is closely coupled with the vehicle attitude and is difficult to determine only from component level studies. This work investigates the influence of airframe integration on the performance of an airframe integrated scramjet through the measurement of internal pressure distribution and the direct measurement of the net lift, thrust and pitching moment using a three-component stress wave force balance. The engine chosen as the basis for this study was the Mach 12 rectangularto-elliptical shape-transition (m12rest) scramjet that was developed by Suraweera and Smart (2009) as a research engine for access-to-space applications. The inlet and combustor flowpath were integrated with a slender 6°wedge forebody, streamlined external geometry and three dimensional thrust nozzle. The scale of the engine was chosen so that the entire engine would fit within the core-flow diamond (bi-conic) produced by a Mach 10 facility nozzle. The Mach 10b facility nozzle was chosen because it is the largest nozzle current in use with the t4 Stalker Tube and because the offdesign performance of a scramjet engine is of interest for access-to-space vehicles that must accelerate over a range of Mach numbers.Freejet experiments were conducted within the t4 Stalker Tube. Two trueflight Mach 10 test conditions were used: a high pressure test condition that replicated flight at a dynamic pressure of 48 kPa and a low pressure test condition that replicated flight at a dynamic pressure of 28 kPa. Scaling of the test conditions according to the established binary scaling law was not completed due to facility operational limits.The engine featured two fuel injection stations from which gaseous hydrogen was injected. The first injection station was partway along the length of the inlet while the second injection station was at the start of the combustor behind a rearward facing circumferential step. In addition to investigating inlet-only and step-only injection, a combined scheme where 68 % of the fuel was injected from the step station and 32 % from the inlet station was also investigated.To support the analysis of the experimental results, numerical simulations of the engine with no fuel injection were conducted using the nasa code vulcan. Analysis of the simulations show that the mass capture ratio with respect to the projected inlet area is approximately 60 % at each test condition. The simulations also show that spillage of flow from the slender forebody accounts for just 12 % of the flow through the projected iii inlet area, a small but non-negligible fraction. By integrating the engine surface forces, the drag coefficient with respect ...

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Experimental Verification of the Aerodynamics of Stream Thrust Probes

Cited by 2 publications

References 2 publications

The Influence of Viscosity and Surface Curvature on the Pressure Distribution of a Stream Thrust Probe

The Influence of Viscosity and Surface Curvature on the Pressure Distribution of a Stream Thrust Probe

An experimental investigation of an airframe integrated three-dimensional scramjet engine at a Mach 10 flight condition

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