Transonic Investigation of Internal-flow Characteristics of a Square-shaped Scoop Inlet Mounted at Three Chordwise Positions Above a High 45 Degree Sweptback Wing and Body Combination
Author: Arvid L. Keith
Publisher:
Published: 1957
Total Pages: 35
ISBN-13:
DOWNLOAD EBOOKAn investigation has been made in the Langley transonic blowdown tunnel at Mach numbers of 1.04, 1.28, and 1.42 to determine the internal-flow characteristics of three top-mounted scoop inlets with rounded lips. The inlets, which were of square cross section, were mounted at the leading edge, midchord, or trailing edge of the high 45 degree sweptback 6-percent-thick wing. The rearmost position without the wing installed was also studied. The test results showed that the inlet located at the wing leading edge achieved normal-shock total-pressure ratios without boundary-layer control for all Mach numbers and angles of attack. Rearward movement of the inlet over the wing effected losses of as much as 9 percent of the free-stream total pressure, compared with the leading-edge position, and increases in flow distortion up to 42 percent of the average inlet total pressure. The presence of the wing apparently had little effect on the internal-flow characteristics of the rearmost inlet for the Mach number and angle-of-attack ranges investigated.