A Visualized Wake Hazard Assessment

Zheng, Zhong; Xu, Ying

doi:10.2514/6.2008-467

Cited by 1 publication

(3 citation statements)

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“…Once the vortex method is validated, the induced vortex is added into the wind field and the result is compared to the result calculated by the strip theory model 13 Figure 2 shows the mesh used in the vortex lattice method in Tornado. Figure 3 shows the rolling moment coefficient from two methods with different vortex center locations along the wing span-wise direction at the same level of the wing.…”

Section: Resultsmentioning

confidence: 99%

“…Since we have the wake vortex velocity field from the wake vortex model, we can calculate the induced rolling moment coefficient on an aircraft that flies through the wake 13 . Considering the aircraft with a wing span of 2s F and flying speed , and assuming that the lift slope / is approximately constant in the range of angle of attack α, we have:…”

Section: Induced Rolling Moment Coefficient On the Following Aircmentioning

confidence: 99%

“…The wake/aircraft interaction model is developed based on a vortex lattice method 4 . The induced rolling moment coefficient is also modeled following a strip theory model 13 , and is used to compare the results from the vortex lattice method. With an assumed vortex created by the leader 2 American Institute of Aeronautics and Astronautics UAV at the wingtip location 8 , the rolling moment coefficient of the follower is calculated and used as a measure for the roll hazard induced on the following UAV.…”

Section: Introductionmentioning

confidence: 99%

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Aerodynamic Simulation of Wake Encounter for Aircraft Close Formation Operations (Invited)

Zheng

2015

7th AIAA Atmospheric and Space Environments Conference

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In this study, the rolling moment coefficient of a following unmanned aerial vehicle (UAV) induced by wake vortices from a leading UAV is analyzed and studied. Numerical simulation results are compared to the results from an analytical vortex lattice method. Then a complete UAV mesh is built and used to calculate the influence by a pair of wake vortices created by the leading UAV in real flight scenario. The paper provides an estimate of the vortex roll hazard assessment for the following UAV in close formation operations. Nomenclature 0 = main wing span = rolling moment coefficient of the follower = cord length of the follower ̅ = average cord length of the follower = rolling moment of the follower = induced vortex core radius = plan form area = wing span = vertical velocity on the wing = flying speed of the follower = coordinate of the main wing of the follower 0 = vortex strength generated by the leader = vortex strength acting on the follower = circulation on the wing of the follower

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Section: Resultsmentioning

confidence: 99%

Section: Induced Rolling Moment Coefficient On the Following Aircmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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