EBookClubs

Read Books & Download eBooks Full Online

EBookClubs

Read Books & Download eBooks Full Online

Book Wind Tunnel Application of a Pressure Sensitive Paint Technique to a Double Delta Wing Model at Subsonic and Transonic Speeds

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 Pressure and Temperature Sensitive Paints

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.

Book NASA Technical Memorandum

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 Scientific and Technical Aerospace Reports

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1972 with total page 1056 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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

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 43rd AIAA Aerospace Sciences Meeting Exhibit

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 Unsteady Aerodynamic Pressures in Transonic Flow

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 International Aerospace Abstracts

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:

Book Flow Field Over the Wing of a Delta Wing Fighter Model with Vortex Control Devices at Mach 0 6 To 1 2

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 Applied Mechanics Reviews

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 Research and Technology Highlights 1993

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:

Book Aeronautical Engineering

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 Unsteady Transonic Wind Tunnel Test on a Semispan Straked Delta Wing Model Oscillating in Pitch Part 3 Selected Data Points for Simulated Maneuvers

Download or read book Unsteady Transonic Wind Tunnel Test on a Semispan Straked Delta Wing Model Oscillating in Pitch Part 3 Selected Data Points for Simulated Maneuvers written by and published by . This book was released on 1995 with total page 205 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel investigation was conducted in 1992 to investigate the unsteady aerodynamic aspects of transonic high incidence flows over a simple straked wing model. This test was designed to show how low speed vortex type flows evolve into complicated shock vortex interacting flows at transonic speeds. Requirements for this test were based on a low speed test conducted in 1986 on a full span model in the NLR Low Speed Tunnel. The transonic model was a semispan version of the low speed model with some modifications. It was equipped with a three-component semispan balance to measure total wing loads, seven rows of high response pressure transducers to measure unsteady pressures and 15 vertical accelerometers to measure model motion and vibrations. The model was oscillated sinusoidally in pitch at various amplitudes and frequencies for mean model incidences varying from 40 to 480. In addition, maneuver type transient motions of the model were tested with amplitudes of 160 and 300 total rotation at various starting angles. The test was conducted in the NLR HST in the Mach range of 0.225 to 0.90 with some preliminary vapor screen flow visualIzation data taken at M=O.6 and 0.9. This part of the report presents selected data points for simulated maneuvers.