Download or read book Transonic Pressure Force and Flow Visualization Measurements on a Pitching Straked Delta Wing at High Alpha written by and published by . This book was released on 2003 with total page 29 pages. Available in PDF, EPUB and Kindle. Book excerpt: A force and pressure test was conducted in May 1992 (at the National Aerospace Laboratory NLR, The Netherlands) on a simple straked wing with the objective to extend the understanding of flow fields at low speed and high incidence obtained in earlier tests, up to transonic speeds also at high incidences. A flow visualization test was then conducted with the same simple straked wing modes in August 1996 for the purpose of obtaining flow-visualization data to complement the pressure and force database generated in the earlier tests. These tests were conducted in order to examine the flow-field characteristics at high-alpha conditions that involve vortices, shocks, and separated flows. Laser light sheet/water vapor techniques were used to illuminate the flows, and video recording was used to obtain the data. Both low- and high-speed video cameras were used to examine spanwise and streamwise laser sheet positions. In addition, under NLR funding, some preliminary particle image velocimetry (PIV) data were obtained at M - 0.225 and 0.6, as well as some pulsed laser-flow visualization (9 nano-sec pulse) at M - 0.9. Correlation was performed between the flow visualization data from this test and the pressure/force data obtained in 1992 on the same configuration. The database described in this paper has been included in the RTO database for verification and validation data for computational unsteady aerodynamics.

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:

Download or read book Professional Measurements Obtained in Flight at Transonic Speeds for a Conically Cambered Delta Wing written by Earl R. Keener and published by . This book was released on 1959 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Unsteady Aerodynamics of Delta Wings Performing Maneuvers to High Angle of Attack written by Mohammad-Ameen M. Jarrah and published by . This book was released on 1988 with total page 352 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book High alpha Vortex Decoupling Investigations on a Chine Forebody Delta Wing Configuration at Transonic Mach Numbers written by and published by . This book was released on 1992 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Pressure Measurements Obtained in Flight at Transonic Speeds for a Conically Cambered Delta Wing written by Earl R. Keener and published by . This book was released on 1959 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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:

Download or read book A Transonic Wind tunnel Investigation of the Longitudinal Force and Moment Characteristics of Two Delta Wings and One Clipped tip Delta Wing of 4 Percent Thickness on a Slender Body written by William E. Palmer and published by . This book was released on 1955 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Steady and Unsteady Transonic Pressure Measurements on a Clipped Delta Wing for Pitching and Control surface Oscillations written by Robert W. Hess and published by . This book was released on 1986 with total page 115 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA SP written by and published by . This book was released on 1992 with total page 654 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Detailed Flow field Measurements Over a 75 swept Delta Wing written by Scott O. Kjelgaard and published by . This book was released on 1990 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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...

Download or read book Unsteady Low Speed Windtunnel Test of a Straked Delta Wing Oscillating in Pitch Part 1 General Description and Discussion of Results written by A. M Cunningham (Jr) and published by . This book was released on 1988 with total page 140 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of a wind tunnel test of an oscillating straked wing indicate unsteady airloads and pressure distributions for a range of incidences ( -8 to 50 deg.) and amplitudes (1 to 16 deg.). The wind speed was 80 meters/second, which provided reduced frequencies up to 0.50 based on root chord. The zeroth and first harmonic as well as the continuous time history of the pressure and overall loads were measured. Flow visualization was performed for flow of 30 meters/second using a pulsating laser light sheet. This part presents the description of this wind tunnel test and preliminary discussions of results obtained from the test. Details are provided on the model, instrumentation and support system as well as test program condition/run member cross-reference tables for use with the data base presented in parts II through VI of this report. Model geometry and force data processing procedures are presented in the appendices. Also presented in the appendices are updated values of force data obtained from the steady tests of the model suspended by a wire balance. (fr).

Download or read book Aerodynamic Characteristics of a Delta Wing with Leading Edge Swept Back 45 Degrees Aspect Ratio 4 and NACA 65A006 Airfoil Section written by William C. Sleeman and published by . This book was released on 1949 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of the investigation of wing-alone and wing-fuselage combination employing a delta wing having 45 degree sweepback of the leading edge, aspect ratio 4, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location also were obtained for these configurations, and are presented for a range of tail heights at one tail length. In order to expedite publishing of these data, only a brief analysis is included.

Download or read book Aeronautical Engineering written by and published by . This book was released on 1993 with total page 712 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)

Download or read book Pressure Measurements on Two 60 Swept Delta Wings with Blunt Leading Edges and Dihedral Angles of 0 and 45 at a Mach Number of 4 95 written by P. Calvin Stainback and published by . This book was released on 1962 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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...