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Force And Moment Wind Tunnel Measurements At Mach Numbers From 06 To 20 Of The Control Characteristics Of A Body Tail Control Configuration By Ggbrebner Wkosborne And Doreen Ebrown
Download Force And Moment Wind Tunnel Measurements At Mach Numbers From 06 To 20 Of The Control Characteristics Of A Body Tail Control Configuration By Ggbrebner Wkosborne And Doreen Ebrown full books in PDF, epub, and Kindle. Read online Force And Moment Wind Tunnel Measurements At Mach Numbers From 06 To 20 Of The Control Characteristics Of A Body Tail Control Configuration By Ggbrebner Wkosborne And Doreen Ebrown ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Wind-tunnel Investigation at Mach Numbers from 0.40 to 1.20 of the Static Aerodynamic and Control Characteristics of a Model of a Nonlifting Reeintry Capsule in Combination with a Rocket Booster by : Albin O. Pearson
Download or read book Wind-tunnel Investigation at Mach Numbers from 0.40 to 1.20 of the Static Aerodynamic and Control Characteristics of a Model of a Nonlifting Reeintry Capsule in Combination with a Rocket Booster written by Albin O. Pearson and published by . This book was released on 1960 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Investigation at Mach Numbers from 3.0 to 6.8 of the Static Aerodynamic Characteristics of Modified Mercury Exit and Escape Capsule Configurations by : Albin O. Pearson
Download or read book Wind-tunnel Investigation at Mach Numbers from 3.0 to 6.8 of the Static Aerodynamic Characteristics of Modified Mercury Exit and Escape Capsule Configurations written by Albin O. Pearson and published by . This book was released on 1960 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Tests of Rectangular Finned Variable Gap Tangent Ogive-cylinder Model at Mach Numbers 1.75 to 4.50 by : Neil Arthur Zarin
Download or read book Wind Tunnel Tests of Rectangular Finned Variable Gap Tangent Ogive-cylinder Model at Mach Numbers 1.75 to 4.50 written by Neil Arthur Zarin and published by . This book was released on 1964 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Investigation at Mach Numbers from 0.60 to 1.20 of the Static Aerodynamic Characteristics of a Model of a Possible Nonlifting Reentry Capsule in Combination with a Rocket Booster by : Albin O. Pearson
Download or read book Wind-tunnel Investigation at Mach Numbers from 0.60 to 1.20 of the Static Aerodynamic Characteristics of a Model of a Possible Nonlifting Reentry Capsule in Combination with a Rocket Booster written by Albin O. Pearson and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722322021 Total Pages :92 pages Book Rating :4.3/5 (22 download)
Book Synopsis Control Effectiveness and Tip-Fin Dihedral Effects for the Hl-20 Lifting-Body Configuration at Mach Numbers from 1.6 to 4.5 by : National Aeronautics and Space Administration (NASA)
Download or read book Control Effectiveness and Tip-Fin Dihedral Effects for the Hl-20 Lifting-Body Configuration at Mach Numbers from 1.6 to 4.5 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-10 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind tunnel tests were made with a scale model of the HL-20 in the Langley Unitary Plan Wind Tunnel. Pitch control was investigated by deflecting the elevon surfaces on the outboard fins and body flaps on the fuselage. Yaw control tests were made with the all movable center fin deflected 5 deg. Almost full negative body flap deflection (-30 deg) was required to trim the HL-20 (moment reference center at 0.54-percent body length from nose) to positive values of life in the Mach number range from 1.6 to 2.5. Elevons were twice as effective as body flaps as a longitudinal trim device. The elevons were effective as a roll control, but because of tip-fin dihedral angle, produced about as much adverse yawing moment as rolling moment. The body flaps were less effective in producing rolling moment, but produced little adverse yawing moment. The yaw effectiveness of the all movable center fin was essentially constant over the angle-of-attack range at each Mach number. The value of yawing moment, however, was small. Center-fin deflection produced almost no rolling moments. The model was directionally unstable over most of the Mach number range with tip-fin dihedral angles less than the baseline value of 50 deg. Cruz, Christopher I. and Ware, George M. Langley Research Center...
Book Synopsis Wind-tunnel Force Measurements on a 1/20 Scale Model of Black Arrow at Mach Numbers of 1.2, 1.5 and 2.0 by : J. R. Hall
Download or read book Wind-tunnel Force Measurements on a 1/20 Scale Model of Black Arrow at Mach Numbers of 1.2, 1.5 and 2.0 written by J. R. Hall and published by . This book was released on 1972 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics and Control Effectiveness of the Hl-20 Lifting Body Configuration at Mach 10 in Air by : National Aeronautics and Space Administration
Download or read book Aerodynamic Characteristics and Control Effectiveness of the Hl-20 Lifting Body Configuration at Mach 10 in Air written by National Aeronautics and Space Administration and published by . This book was released on 2018-08-27 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: A 0.0196-scale model of the HL-20 lifting-body, one of several configurations proposed for future crewed spacecraft, was tested in the Langley 31-Inch Mach 10 Tunnel. The purpose of the tests was to determine the effectiveness of fin-mounted elevons, a lower surface flush-mounted body flap, and a flush-mounted yaw controller at hypersonic speeds. The nominal angle-of-attack range, representative of hypersonic entry, was 2 deg to 41 deg, the sideslip angles were 0 deg, 2 deg, and -2 deg, and the test Reynolds number was 1.06 x 10 E6 based on model reference length. The aerodynamic, longitudinal, and lateral control effectiveness along with surface oil flow visualizations are presented and discussed. The configuration was longitudinally and laterally stable at the nominal center of gravity. The primary longitudinal control, the fin-mounted elevons, could not trim the model to the desired entry angle of attack of 30 deg. The lower surface body flaps were effective for roll control and the associated adverse yawing moment was eliminated by skewing the body flap hinge lines. A yaw controller, flush-mounted on the lower surface, was also effective, and the associated small rolling moment was favorable.Scallion, William I.Langley Research CenterAERODYNAMIC CHARACTERISTICS; CONTROLLABILITY; EFFECTIVENESS; LIFTING BODIES; SCALE MODELS; WIND TUNNEL TESTS; ELEVONS; FINS; YAWING MOMENTS; STABILITY; SIDESLIP; REYNOLDS NUMBER; LONGITUDINAL CONTROL; LATERAL CONTROL; HYPERSONIC SPEED; FLOW VISUALIZATION; FLAPPING; ANGLE OF ATTACK...