William C Hayes

Bio: William C Hayes is an academic researcher. The author has contributed to research in topics: Wind tunnel & Deflection (engineering). The author has an hindex of 1, co-authored 2 publications receiving 2 citations.

Wind-tunnel Investigation of Effect of Propeller Slipstreams on Aerodynamic Characteristics of a Wing Equipped with a 50-percent-chord Sliding Flap and a 30-percent-chord Slotted Flap

Abstract: Report presenting an investigation of the aerodynamic characteristics of a wing equipped with a 50-percent-chord sliding flap and a 30-percent-chord slotted flap operating in the slipstreams of two large-diameter propellers in the 300 mph 7- by 10-foot tunnel. Large tunnel-wall effects for which there are no known correction methods were encountered in the tests. Stalling was found to occur in conditions approaching steady level flight at high-power conditions,but a leading-edge slat effectively delayed the stall.

Research on vtol and stol aircraft in the united states

Abstract: Publisher Summary This chapter discusses about the rapidly increasing interest in the United States in VTOL and STOL aircraft, that is aircraft capable of performing either vertical or short take-off and landing. The chapter presents all those VTOL aircraft, falling in between that are propelled by rotors, propellers, ducted fans, or turbojets. STOL aircraft include only those in which all or most of the power available is used for producing high lift. For example, the jet flap but will not cover boundary-layer control applications that make use of only a small portion of the power available. A significant feature of VTOL–STOL research programs undertaken recently in the United States has been the use of flying test-bed aircraft that are simple and relatively inexpensive research machines.

Wing and propeller aerodynamic interaction through nonlinear lifting line theory and blade element momentum theory

Abstract: In this paper a computational methodology of aerodynamic interaction between propeller and wing is described. Presented work is focused on development of quick and accurate tool. Lifting line theory (LLT) with nonlinear airfoil characteristic is used to solve a finite span wing aerodynamic to predict downwash and lift distribution respectively. Blade element momentum theory (BEM) is used as a computational tool for estimating total thrust, torque, axial and tangential velocity distributions. Model of slipstream development is considered. Influence of propeller model to wing is simulated as contribution of higher dynamic pressure and change of angle of attack behind the propeller.