Aerodynamic Cruise Design of a Joined Wing SensorCraft

LeDoux, Stephen T.; Vassberg, John C.; Fatta, Gasper; DeHaan, Mark A.

doi:10.2514/6.2008-7190

Cited by 5 publications

(5 citation statements)

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“…Wolkovitch [1] discussed the effect of airfoil camber and found that a small airfoil camber of the rear wing benefits drag reduction. LeDoux et al [13] have done similar work, and the optimization supported the conclusions of Wolkovitch. Moschetta and Thipyopas [14] performed wind tunnel tests to investigate the aerodynamic performance of tandem wings at a low Reynolds number.…”

Section: Introductionsupporting

confidence: 53%

Data Mining-Based Design Space Exploration and Optimization for Tandem Airfoils

Shi

Lan

Wang

et al. 2023

International Journal of Aerospace Engineering

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The joined-wing configuration has great technical appeal for the development of next-generation SensorCraft. Research based on the simplified tandem airfoil system can improve understanding of the joined-wing configuration’s aerodynamic characteristics. We combine the adjoint-based aerodynamic shape optimization and self-organizing map- (SOM-) based data mining technology to reveal the flow interactions of tandem airfoils and aerodynamic characteristics from the perspective of the entire aerodynamic design space. The SOM is used to explore the correlation between relative position parameters and aerodynamic force coefficients of tandem airfoil systems. Results show that the drag coefficient at the defined range of lift coefficients has obviously positive linear correlation and greatly dependents on the value of decalage. The tandem airfoils with negative decalage around -2.7° have the smallest drag coefficients. Due to variations in the aerodynamic interaction strength, the drag coefficient of each airfoil changes from a linear law to a nonlinear law as airfoils approach each other. We then perform single-point aerodynamic shape optimization based on two sets of relative position parameters with different aerodynamic interaction strengths, and 1.8% and 1.28% drag reductions are obtained, respectively. Based on optimized airfoils, the SOM is used to reveal the distribution of drag variation in the design space constructed by relative position parameters. Results illustrate that the aerodynamic interference strength between the front and rear airfoils significantly affects the drag reduction mechanism, which results in the different distribution patterns of drag variation in design space.

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Section: Introductionsupporting

confidence: 53%

Data Mining-Based Design Space Exploration and Optimization for Tandem Airfoils

Shi

Lan

Wang

et al. 2023

International Journal of Aerospace Engineering

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“…Following the contract FA8650-05-C-3500 granted by AFRL, called Aerodynamic Efficiency Improvements (see also section 3.3.3), in reference [199] transonic cruise design and optimization were investigated with the constraints required for antenna thickness and fixed planform. A "point of departure" configuration was chosen and analyzed.…”

Section: The Aerodynamic Efficiency Improvements Program: Aerodynamic Optimizationmentioning

confidence: 99%

“…It was verified that the optimal configuration for the specific design point was carrying its advantages also in off-design conditions. It needs to be noted that calculations were done assuming a fully turbulent [199].…”

Section: The Aerodynamic Efficiency Improvements Program: Aerodynamic Optimizationmentioning

confidence: 99%

Challenges, Ideas, and Innovations of Joined-Wing Configurations: A Concept from the Past, an Opportunity for the Future

Cavallaro

Demasi

2016

Progress in Aerospace Sciences

120

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“…The completed tests are depicted in figure 1 along with two planned AEI tests of the Boeing joined-wing 2, 3 SensorCraft vehicle concept where a full span model will be considered. The first two wind-tunnel tests were conducted as part of the HiLDA program.…”

Section: Introductionmentioning

confidence: 99%

Aeroservoelastic Testing of a Sidewall Mounted Free Flying Wind-Tunnel Model

Scott

Vetter

Penning

et al. 2008

26th AIAA Applied Aerodynamics Conference

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A team comprised of the Air Force Research Laboratory (AFRL), Northrop Grumman, Lockheed Martin, and the NASA Langley Research Center conducted three aeroservoelastic wind-tunnel tests in the Transonic Dynamics Tunnel to demonstrate active control technologies relevant to large, flexible vehicles. In the first of these three tests, a semispan, aeroelastically scaled, wind-tunnel model of a flying wing SensorCraft vehicle was mounted to a force balance to demonstrate gust load alleviation. In the second and third tests, the same wing was mated to a new, multi-degree-of-freedom, sidewall mount. This mount allowed the half-span model to translate vertically and pitch at the wing root, allowing better simulation of the full span vehicle's rigid-body modes. Gust Load Alleviation (GLA) and Body Freedom Flutter (BFF) suppression were successfully demonstrated. The rigid body degrees-of-freedom required that the model be flown in the wind tunnel using an active control system. This risky mode of testing necessitated that a model arrestment system be integrated into the new mount. The safe and successful completion of these free-flying tests required the development and integration of custom hardware and software. This paper describes the many systems, software, and procedures that were developed as part of this effort.

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Aerodynamic Cruise Design of a Joined Wing SensorCraft

Cited by 5 publications

References 0 publications

Data Mining-Based Design Space Exploration and Optimization for Tandem Airfoils

Data Mining-Based Design Space Exploration and Optimization for Tandem Airfoils

Challenges, Ideas, and Innovations of Joined-Wing Configurations: A Concept from the Past, an Opportunity for the Future

Aeroservoelastic Testing of a Sidewall Mounted Free Flying Wind-Tunnel Model

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