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
01 Feb 1957-
TL;DR: In this article, the aerodynamic characteristics of a wing equipped with a 50-percent-chord sliding flap and a 30-percentchord slotted flap operating in the slipstreams of two large-diameter propellers in the 300 mph 7- by 10-foot tunnel were investigated.
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.
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01 Jan 1959
TL;DR: In this article, the authors discuss 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.
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.
13 citations
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01 Jan 1956
TL;DR: In this paper, the results of an investigation conducted in the Langley 300 mph 7- by 10-foot wind tunnel for the purpose of determining the aerodynamic characteristics of a model wing-propeller combination, and of the wing and propeller separately at angles of attack up to 90 degrees.
Abstract: This report presents the results of an investigation conducted in the Langley 300 mph 7- by 10-foot wind tunnel for the purpose of determining the aerodynamic characteristics of a model wing-propeller combination, and of the wing and propeller separately at angles of attack up to 90 degrees. The tests covered thrust coefficients corresponding to free-stream velocities from zero forward speed to the normal range of cruising speeds. The results indicate that increasing the thrust coefficient increases the angle of attack for maximum lift and greatly diminishes the usual reduction in lift above the angle of attack for maximum lift.
32 citations
01 Jan 1957
TL;DR: In this article, an investigation of the effectiveness of a wing equipped with a 50-percent-chord sliding flap and a 30-percentchord slotted flap in deflecting a propeller slipstream downward for vertical take-off is presented.
Abstract: Results are presented of an investigation of the effectiveness of a wing equipped with a 50-percent-chord sliding flap and a 30-percent-chord slotted flap in deflecting a propeller slipstream downward for vertical take-off. Tests were conducted at zero forward speed in a large room and included the effects of flap deflection, proximity to the ground, a leading-edge slat, and end plates. A turning angle of about 70 degrees and a resultant force of about 100 percent of the thrust were achieved near the ground. Out of the ground-effect region, the turning angle was also about 70 degrees but the resultant force was reduced to about 86 percent of the thrust.
5 citations