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Wind Tunnel Application Of A Pressure Sensitive Paint Technique To A Double Delta Wing Model At Subsonic And Transonic Speeds
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Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721985562 Total Pages :322 pages Book Rating :4.9/5 (855 download)
Book Synopsis Wind Tunnel Application of a Pressure-Sensitive Paint Technique to a Double Delta Wing Model at Subsonic and Transonic Speeds by : National Aeronautics and Space Administration (NASA)
Download or read book Wind Tunnel Application of a Pressure-Sensitive Paint Technique to a Double Delta Wing Model at Subsonic and Transonic Speeds written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-27 with total page 322 pages. Available in PDF, EPUB and Kindle. Book excerpt: A pressure-sensitive paint (PSP) technique was applied in a wind tunnel experiment in the NASA Langley Research Center 8-Foot Transonic Pressure Tunnel to study the effect of wing fillets on the global vortex induced surface static pressure field about a sharp leading-edge 76 deg./40 deg. double delta wing, or strake-wing, model at subsonic and transonic speeds. Global calibrations of the PSP were obtained at M(sub infinity) = 0.50, 0.70, 0.85, 0.95, and 1.20, a Reynolds number per unit length of 2.0 million, and angles of attack from 10 degrees to 20 degrees using an insitu method featuring the simultaneous acquisition of electronically scanned pressures (ESP) at discrete locations on the model. The mean error in the PSP measurements relative to the ESP data was approximately 2 percent or less at M(sub infinity) = 0.50 to 0.85 but increased to several percent at M(sub infinity) =0.95 and 1.20. The PSP pressure distributions and pseudo-colored, planform-view pressure maps clearly revealed the vortex-induced pressure signatures at all Mach numbers and angles of attack. Small fillets having parabolic or diamond planforms situated at the strake-wing intersection were respectively designed to manipulate the vortical flows by removing the leading-edge discontinuity or introducing additional discontinuities. The fillets caused global changes in the vortex-dominated surface pressure field that were effectively captured in the PSP measurements. The vortex surface pressure signatures were compared to available off-surface vortex cross-flow structures obtained using a laser vapor screen (LVS) flow visualization technique. The fillet effects on the PSP pressure distributions and the observed leading-edge vortex flow characteristics were consistent with the trends in the measured lift, drag, and pitching moment coefficients. Erickson, Gary E. and Gonzalez, Hugo A. Langley Research Center WBS 23-721-10-66...
Book Synopsis Pressure and Temperature Sensitive Paints by : Tianshu Liu
Download or read book Pressure and Temperature Sensitive Paints written by Tianshu Liu and published by Springer Nature. This book was released on 2021-07-31 with total page 552 pages. Available in PDF, EPUB and Kindle. Book excerpt: This new edition describes pressure and temperature sensitive paints (PSP and TSP) in global surface pressure and temperature measurements in aerodynamics and fluid mechanics. The book includes the latest progress in paint formulations, instrumentation, and steady and unsteady aerodynamic measurements in various facilities including low-speed, transonic, supersonic and hypersonic wind tunnels. The updated technical aspects of PSP and TSP in the book will be useful for students and researchers in experimental aerodynamics and fluid mechanics.
Download or read book NASA Technical Memorandum written by and published by . This book was released on 1963 with total page 276 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 43rd AIAA Aerospace Sciences Meeting & Exhibit by :
Download or read book 43rd AIAA Aerospace Sciences Meeting & Exhibit written by and published by . This book was released on 2005 with total page 624 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Application of the Pressure Sensitive Paint Technique to Steady and Unsteady Flow by : Yuichi Shimbo
Download or read book Application of the Pressure Sensitive Paint Technique to Steady and Unsteady Flow written by Yuichi Shimbo and published by . This book was released on 1996 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Application of Pressure Sensitive Paint to Measurement of Global Surface Pressure for a Convergent-divergent Nozzle and an Isolated Double Delta Wing at Transonic Speeds by : Amair Jalali Jagharghi
Download or read book Application of Pressure Sensitive Paint to Measurement of Global Surface Pressure for a Convergent-divergent Nozzle and an Isolated Double Delta Wing at Transonic Speeds written by Amair Jalali Jagharghi and published by . This book was released on 1995 with total page 13 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Unsteady Aerodynamic Pressures in Transonic Flow by : L. V. Andrew
Download or read book Unsteady Aerodynamic Pressures in Transonic Flow written by L. V. Andrew and published by . This book was released on 1971 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt: Oscillatory pressures as well as total loads were obtained on a 70-degree delta-wing model undergoing sinusoidal pitch rotation in transonic flow. The mach number range was from 0.8 to 1.2, and the maximum reduced frequency (based on centerline half chord) achieved was 0.172. Corresponding pressures were computer using the kernel function method and the doublet/vortex lattice method at subsonic speeds, the sonic box method, and the supersonic mach box method. Both box methods produce point values of potentials that are fitted by surfaces tyo yeld pressures. Comparisomns of the measured and computer pressures show that, in general (and as expected), the computed pressures are higher than the measured values near the leading edge. Also, in general (but unexpected), the computed phase lags between motion of the surface and the pressures generated by the motion are lower than the measure values.
Book Synopsis Wind Tunnel Tests of a Half-model Delta Wing-body Configuration at Subsonic, Transonic and Supersonic Speeds by : Jan A. van der Bliek
Download or read book Wind Tunnel Tests of a Half-model Delta Wing-body Configuration at Subsonic, Transonic and Supersonic Speeds written by Jan A. van der Bliek and published by . This book was released on 1957 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781723082115 Total Pages :130 pages Book Rating :4.0/5 (821 download)
Book Synopsis Flow Field Over the Wing of a Delta-Wing Fighter Model with Vortex Control Devices at Mach 0. 6 To 1. 2 by : National Aeronautics and Space Administration (NASA)
Download or read book Flow Field Over the Wing of a Delta-Wing Fighter Model with Vortex Control Devices at Mach 0. 6 To 1. 2 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt: As part of a cooperative research program between NASA, McDonnell Douglas Corporation, and Wright Research and Development Center, a flow field investigation was conducted on a 7.52 percent scale windtunnel model of an advanced fighter aircraft design. The investigation was conducted in the Langley 16 ft Transonic Tunnel at Mach numbers of 0.6, 0.9, and 1.2. Angle of attack was varied from -4 degrees to 30 degrees and the model was tested at angles of sideslip of 0, 5, and -5 degrees. Data for the over the wing flow field were obtained at four axial survey stations by the use of six 5 hole conical probes mounted on a survey mechanism. The wing leading edge primary vortex exerted the greatest influence in terms of total pressure loss on the over the wing flow field in the area surveyed. A number of vortex control devices were also investigated. They included two different apex flaps, wing leading edge vortex flaps, and small large wing fences. The vortex flap and both apex flaps were beneficial in controlling the wing leading edge primary vortex. Bare, E. Ann and Reubush, David E. and Haddad, Raymond C. Langley Research Center DELTA WINGS; FIGHTER AIRCRAFT; FLOW DISTRIBUTION; SUBSONIC SPEED; TRANSONIC SPEED; VORTEX FLAPS; WIND TUNNEL MODELS; WIND TUNNEL TESTS; ANGLE OF ATTACK; FLOW VISUALIZATION; MACH NUMBER; PRESSURE DISTRIBUTION; SIDESLIP; TRANSONIC WIND TUNNELS...
Book Synopsis Demonstration Test of Pressure Sensitive Paint in the AEDC 16-ft Transonic Wind Tunnel Using the TST Model by : M. E. Sellers
Download or read book Demonstration Test of Pressure Sensitive Paint in the AEDC 16-ft Transonic Wind Tunnel Using the TST Model written by M. E. Sellers and published by . This book was released on 1994 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis International Aerospace Abstracts by :
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1999 with total page 1016 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1993 with total page 354 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Research and Technology Highlights, 1993 by :
Download or read book Research and Technology Highlights, 1993 written by and published by . This book was released on 1994 with total page 272 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering written by and published by . This book was released on 1991 with total page 538 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Surface Pressure Data Obtained on 65 ̊delta Wing Across Reynolds Number and Mach Number Ranges by : Julio Chu
Download or read book Experimental Surface Pressure Data Obtained on 65 ̊delta Wing Across Reynolds Number and Mach Number Ranges written by Julio Chu and published by . This book was released on 1996 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aeronautical Engineering: A Cumulative Index to a Continuing Bibliography (supplement 325) by :
Download or read book Aeronautical Engineering: A Cumulative Index to a Continuing Bibliography (supplement 325) written by and published by . This book was released on 1995 with total page 470 pages. Available in PDF, EPUB and Kindle. Book excerpt:
