Laminar Stall Prediction and Estimation of CL(max)

Goradia, S. H.; Lyman, V.

doi:10.2514/3.60382

Cited by 10 publications

(2 citation statements)

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“…These include 1) the thin-airfoil stall, where there is a gradual loss of lift at low lift coefficients as the turbulent reattachment point moves rearward; 2) the leading-edge stall, where there is an abrupt loss of lift, as the angle of attack for maximum lift is exceeded, with little to no rounding over the lift curves; and 3) the trailing-edge stall, where there is a gradual loss of lift at high C L as the turbulent separation point moves forward from the trailing edge. Figure 1, adopted from [11], shows a typical pressure distribution for a single-component airfoil exhibiting either laminar stall (short and long bubble stall) or turbulent stall (trailing-edge stall) on the left, and the typical lift curves for the airfoils exhibiting laminar short bubble stall, laminar long bubble stall, and turbulent or trailing-edge stall for single-element airfoils on the right [11]. In Fig.…”

Section: Types Of Stallmentioning

confidence: 99%

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Autonomous Sensing and Control of Wing Stall Using a Smart Plasma Slat

Patel¹,

Sowle²,

Corke³

et al. 2007

Journal of Aircraft

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The concept of a self-governing smart plasma slat for active sense and control of flow separation and incipient wing stall is presented. The smart plasma slat design involves the use of an aerodynamic plasma actuator on the leading edge of a two-dimensional NACA 0015 airfoil in a manner that mimics the effect of a movable leading-edge slat of a conventional high-lift system. The self-governing system uses a single high-bandwidth pressure sensor and a feedback controller to operate the actuator in an autonomous mode with a primary function to sense and control incipient flow separation at the wing leading edge and to delay incipient stall. Two feedback control techniques are investigated. Wind tunnel experiments demonstrate that the aerodynamic effects of a smart actuator are consistent with the previously tested open-loop actuator, in that stall hysteresis is eliminated, stall angle is delayed by 7 deg, and a significant improvement in the lift-to-drag ratio is achieved over a wide range of angles of attack. These feedback control approaches provide a means to further reduce power requirements for an unsteady plasma actuator for practical air vehicle applications. The smart plasma slat concept is well suited for the design of low-drag, quiet, highlift systems for fixed-wing aircraft and rotorcraft.

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Section: Types Of Stallmentioning

confidence: 99%

“…Figure 1a shows the laminar short bubble at S 1 Fig. 1 Shape of the pressure distribution and typical airfoil stall patterns for single-element airfoil [11].…”

Section: Types Of Stallmentioning

confidence: 99%