Aerodynamic characteristics of proposed assured crew return capability (ACRC) configurations

Ware, G. M.; Spencer, B.; Micol, John R.

doi:10.2514/6.1989-2172

Cited by 10 publications

(2 citation statements)

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“…Based on the results presented in Ref. [10] and [11], it can be observed that while the lack of a center fin appears to have a small effect on the results, some of the largest differences do appear to be a slight decrease in pitching moment at lower angles of attack. As the Mach 6 and 10 wind tunnel model had the center fin for all tests, this could potentially be the source of some of the discrepancy in pitching moment at lower angles of attack for these two Mach number cases.…”

Section: B Comparison Of Resultsmentioning

confidence: 81%

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Optimization of Waverider-Derived Crew Reentry Vehicles using a Rapid Aerodynamics Analysis Approach

Lobbia

2015

53rd AIAA Aerospace Sciences Meeting

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A unique implementation of commonly used engineering methods for estimating supersonic and hypersonic aerodynamics of arbitrary shapes is discussed. A validation case comparing the aerodynamic coefficients generated by this technique with both wind tunnel and published computational results for the NASA HL-20 configuration from Mach 1.2 to Mach 10 is presented. These results indicate that the method can generate aerodynamic databases where the lift and drag coefficients are within 15% of experimental data in minutes on a typical workstation. Therefore, the benefits of this rapid aerodynamic analysis approach are further investigated by integrating it into a multidisciplinary design optimization framework for waverider-derived crew reentry vehicles. A shape design code, mass estimating model, and trajectory/aeroheating analysis are linked using a genetic algorithm optimization process to generate a pareto front comparing vehicle downrange versus landed mass. The results of this analysis indicate that a higher lift-to-drag ratio (L/D) typically results in a longer range, but also correlates with a larger vehicle mass. Finally, a comparison with the HL-20 is performed to highlight how the waverider-derived design approach can produce configurations exhibiting a 20% increase in maximum L/D with only a 4% increase in vehicle length. Nomenclatureܽ = speed of sound ‫ܥ‬ = pressure coefficient ℎ = altitude ‫ܦ/ܮ‬ = Lift-to-drag ratio ‫ܯ‬ = Mach number ݊ ො = surface normal vector ‫‬ = pressure ‫ݎ‬ = radial coordinate in Taylor-Maccoll equation ܴ ௌ = waverider shock profile curve radius for cone region in base plane ܴ݁ = Length-based Reynolds number ‫ݑ‬ = radial velocity in Taylor-Maccoll equation ‫ݒ‬ = angular velocity in Taylor-Maccoll equation ‫̅ݔ‬ = axial center of gravity location from vehicle nose (non-dimensionalized to vehicle length) ‫ݕ‬ = waverider lower surface base curve control point (vertical) in base plane ‫ݖ‬ = waverider lower surface base curve control point (horizontal) in base plane ܸ ሬԦ = velocity vector ߚ = shock wave angle ߛ = ratio of specific heats 1 Senior Project Engineer, Launch Strike and Range Department, 2310 E. El Segundo Blvd., Mail Stop M1-557; AIAA Member. Downloaded by UNIVERSITY OF NEW SOUTH WALES on August 23, 2015 | http://arc.aiaa.org | 2 ߥ = Prandtl-Meyer function value ߩ = density ߠ = surface inclination angle; angular coordinate in Taylor-Maccoll equation Subscripts 02 = station number for stagnation point behind a normal shock wave ݅ = surface panel index ‫‬ = streamline segment index ∞ = freestream

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Section: B Comparison Of Resultsmentioning

confidence: 81%

“…In particular, a series of transonic and supersonic tests were performed in the NASA Langley Unitary Plan Wind Tunnel using a 7% scale model (Ref. [10] and [11]), and hypersonic tests were performed in the NASA Langley 20-inch (Mach 6) and 31-inch (Mach 10) tunnels using a 2% scale model (Ref. [12] and [13]).…”

Section: Aerodynamic Analysis -Validationmentioning

confidence: 99%

Optimization of Waverider-Derived Crew Reentry Vehicles using a Rapid Aerodynamics Analysis Approach

Lobbia

2015

53rd AIAA Aerospace Sciences Meeting

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Design and Applications of Preliminary Evaluation Platform of Aerodynamic Forces for Supersonic/Hypersonic Vehicles

2018

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Rapid evaluation of aerodynamic forces is a key technology in conceptual and preliminary performance assessment and design optimization for supersonic/hypersonic vehicles, which is expected to achieve a balance between accuracy and time. In this paper, the preliminary evaluation platform of aerodynamic forces is built based on the physical theories and engineering methods. This platform computes the local velocity vector by using the streamline tracing technology, and extracts the pressure and friction coefficients by calling methods in method database. Furthermore, an example based on HL-20 is brought out. A good agreement is obtained by comparing the calculated results via CFD with the experimental. Also, a good angle of attack compatibility of streamline tracing technology is concluded. This platform has a computation time less than that via CFD and an flight range greater than that via wind tunnel. Finally, the simple flight dynamics simulation is taken out and the synergetic process is verified.

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Integrated inertial navigation system/Global Positioning System (INS/GPS) for manned return vehicle autoland application

Braden

Browning

Gelderloos

et al.

IEEE Symposium on Position Location and Navigation. A Decade of Excellence in the Navigation Sciences

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Aerodynamic characteristics of proposed assured crew return capability (ACRC) configurations

Cited by 10 publications

References 0 publications

Optimization of Waverider-Derived Crew Reentry Vehicles using a Rapid Aerodynamics Analysis Approach

Optimization of Waverider-Derived Crew Reentry Vehicles using a Rapid Aerodynamics Analysis Approach

Design and Applications of Preliminary Evaluation Platform of Aerodynamic Forces for Supersonic/Hypersonic Vehicles

Integrated inertial navigation system/Global Positioning System (INS/GPS) for manned return vehicle autoland application

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