A Fast Approach to Model the Effects of Propeller Slipstream on Wing Load Distribution

Agostinelli, Christian; Simeone, Simone; Allen, Christian B; Zhu, Feng; Rampurawala, Abdul

doi:10.2514/6.2015-0028

Cited by 4 publications

(2 citation statements)

References 12 publications

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“…Then Gerard's estimation of wing mass could be deducted into the estimation of aerial density of wing, as shown in Eq. (25). However,within a given magnitude of gross weight, S could also be recognized as constant.…”

Section: Weight Modelmentioning

confidence: 97%

“…For most of the schemes with overlarge propellers, the propellers are mounted on the wings. Thus the load distribution of wing would be influenced in a large scale, as shown in Fig.18 [25] , which would cause ununiformed additional normal velocity and enhanced 3-dimensiona flow on wing. This would make the aerodynamics more complex for prediction in preliminary design, and would lead to high induced drag and low lift-drag ratio.…”

Section: Enhanced Interactionmentioning

confidence: 98%

See 1 more Smart Citation

Research on Design Domain of Propeller-Driven Hybrid-Mode Aerial Vehicle

Wang

Hou

Zheng

et al. 2016

16th AIAA Aviation Technology, Integration, and Operations Conference

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Propeller-driven hybrid-mode aerial vehicle (PHAV) is the object of this study. Because of its vertical take-off and landing capacity and high horizontal-cruise performance, PHAV is an ideal candidate to undertake intermediate-range emergent missions, such as disaster rescue, goods delivery, emergent battle and so on. However, many designs have failed to realize the indexes due to the failure in handling the contradiction between the two flight modes: vertical flight mode and horizontal flight mode. A feasible approach to the solution of this problem is to consider the requirements of the two modes in formulation of the design domain. In this paper, the design domain of PHAV has been studied. With aerodynamic performance, propulsion efficiency and weight properties considered, a design domain of wing loading W/S and propeller-wing area ratio A/S has been built up. And a nonlinear programming aimed at maximum margin of weight fraction has been conducted. As a distinct feature, a high area ratio would probably be obtained in a design of PHAV. After the programming, the maximum attainable area ratios of different configuration techniques, such distributed powerplants, stop rotor and ducted fan, have been discussed in a more general way, and the problems brought by high area ratio have been also discussed. As a conclusion, the margin of weight fraction of a PHAV is sufficient for endurance, payload, additional weight of propulsion system, strengthened structure, equipment, maneuverability and novel configuration. NomenclatureA = gross disc area propellers AR = aspect ratio a = acceleration B = number of propeller blades  = inflow angle at blade element CL = lift coefficient Cl = roll moment coefficient yielded by torque of propeller CD = drag coefficient CT = thrust coefficient D = drag DL = disk loading d = propeller diameter E = lift-drag ratio e = correction factor f = power ratio g = gravity acceleration 2  = efficiency J = advance ratio of propeller  = margin of weight fraction L = lift Ma = Mach number N = number of propellers n = rotation speed of propeller or load factor P = power q = thrust factor of duct R = propeller radius  = density or atmospheric density S = wing area T = thrust t = time  = thrust-weight ratio V = velocity VS = sonic velocity W = weight W/S = wing loading  = general factor Subscript BE = balde element DF = ducted fan d = propeller disc Eq = equipment F = fuel system H = horizontal flight mode I = ideal N = nonideal P = propulsion system Pl = payload S = structure system V = vertical flight mode

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Section: Weight Modelmentioning

confidence: 97%

Section: Enhanced Interactionmentioning

confidence: 98%