Aerodynamic Database Development for the Hyper-X Airframe-Integrated Scramjet Propulsion Experiments

Engelund, Walter C.; Holland, Scott D.; Cockrell, Charles E.; Bittner, Robert D.

doi:10.2514/2.3768

Cited by 48 publications

(19 citation statements)

References 12 publications

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“…Next, the tools were used to calculate the inlet-open and fuel-on force and moment increments. For the Mach 7 flight condition, the predicted force and moment were experimentally verified by full-scale propulsion flowpath tests that were conducted in the nasa Langley Research Center (larc) 8-ft High Temperature Tunnel (8-ft htt; Engelund et al, 2001). The results of these validation processes are shown in Figure 2.8a and Figure 2.8b and, as is typical with most Hyper-X associated publications, the scale of the vertical axes has not been given.…”

Section: National Aeronautics and Space Administrationmentioning

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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Section: National Aeronautics and Space Administrationmentioning

confidence: 99%

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

Doherty¹

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“…Three articles, by Engelund et al (2001), Holland et al (2001), andHuebner et al (2001), presented information relating to objective 1.…”

Section: Ground-based Testsmentioning

confidence: 99%

Critical Hypersonic Aerothermodynamic Phenomena

Bertin

Cummings

2006

Annu. Rev. Fluid Mech.

245

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The challenges in understanding hypersonic flight are discussed and critical hyper sonic aerothermodynamics issues are reviewed. The ability of current analytical meth ods, numerical methods, ground testing capabilities, and flight testing approaches to predict hypersonic flow are evaluated. The areas where aerothermodynamic short comings restrict our ability to design and analyze hypersonic vehicles are discussed, and prospects for future capabilities are reviewed. Considerable work still needs to be done before our understanding of hypersonic flow will allow for the accurate pre diction of vehicle flight characteristics throughout the flight envelope from launch to orbital insertion.

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“…[15][16][17] The database provides force and moment coefficients for three different vehicle configurations (stack, HXLV and RV) in regions of free-flight and aerodynamic interference. Also included in the database are the force/moment contributions of the HXLV control surfaces (elevons and rudder), the RV control surfaces (all-moving wing and twin vertical tails with rudder) as well as pitch, roll and yaw damping derivatives for the RV.…”

Section: Aerodynamicsmentioning

confidence: 99%

Hyper-X Stage Separation Trajectory Validation Studies

Tartabini

Bose

Mcminn

et al. 2003

AIAA Modeling and Simulation Technologies Conference and Exhibit

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An independent twelve degree-of-freedom simulation of the X-43A separation trajectory was created with the Program to Optimize Simulated trajectories (POST II). This simulation modeled the multi-body dynamics of the X-43A and its booster and included the effect of two pyrotechnically actuated pistons used to push the vehicles apart as well as aerodynamic interaction forces and moments between the two vehicles. The simulation was developed to validate trajectory studies conducted with a 14 degree-offreedom simulation created early in the program using the Automatic Dynamic Analysis of Mechanics Systems (ADAMS) simulation software. The POST simulation was less detailed than the official ADAMS-based simulation used by the Project, but was simpler, more concise and ran faster, while providing similar results. The increase in speed provided by the POST simulation provided the Project with an alternate analysis tool. This tool was ideal for performing separation control logic trade studies that required the running of numerous Monte Carlo trajectories.

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Aerodynamic Database Development for the Hyper-X Airframe-Integrated Scramjet Propulsion Experiments

Abstract: This paper provides an overview of the activities associated with the aerodynamic database which is be-

Cited by 48 publications

References 12 publications

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

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

Critical Hypersonic Aerothermodynamic Phenomena

Hyper-X Stage Separation Trajectory Validation Studies

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