Download or read book Transonic Simple Straked Delta Wing written by Evert G. Geurts and published by . This book was released on 2000 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: The unsteady transonic flow during manoeuvres of fighters is not very well understood. For instance, large time delays and severe dynamic overshoots in normal force may occur, which cannot be predicted accurately by numerical methods. As a consequence to be conservative structures must be over-designed or flight envelopes must be unnecessarily restricted There fore, a better understanding of the unsteady transonic flows, which occur during maneuvers, is of interest for the development and operation of fighters. This data set relates to an unsteady transonic wind tunnel test, on a highly instrumented semi-span simple straked delta wing model. Harmonic pitch as well as manoeuvre simulations were performed.

Download or read book Fresno State College New Campus Dedication May 4th Through May 10th written by and published by . This book was released on 1958 with total page 47 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Unsteady Transonic Wind Tunnel Test on a Semispan Straked Delta Wing Oscillating in Pitch Part 1 Description of the Model Test Setup Data Acquisition and Data Processing written by and published by . This book was released on 1994 with total page 93 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=0.6 and 0.9. This part of the report presents a description of the model, test setup, data acquisition, and data processing. (AN).

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 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.

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 Overview of Unsteady Transonic Wind Tunnel Test on a Semispan Straked Delta Wing Oscillating in Pitch written by and published by . This book was released on 1994 with total page 56 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 4 deg to 48 deg. In addition, maneuver type transient motions of the model were tested with amplitudes of 16 deg and 30 deg 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=0.6 and 0.9. Unsteady aerodynamics, Aeroelasticity, Pressure data, Transonic, High incidence flow, Shock vortex interaction, Force data.

Download or read book Unsteady Transonic Wind Tunnel Test on a Semispan Straked Delta Wing Model Oscillating in Pitch written by Atlee M. Cunningham and published by . This book was released on 1994 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Unsteady Transonic Wind Tunnel Test on a Semispan Straked Delta Wing Model Oscillating in Pitch written by Atlee M. Cunningham and published by . This book was released on 1995 with total page 199 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Unsteady Transonic Wind Tunnel Test on a Semispan Straked Delta Wing Model Oscillating in Pitch written by Atlee M. Cunningham and published by . This book was released on 1995 with total page 119 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Transonic Loads Characteristics of a 3 percent thick 60 Delta wing body Combination written by John M. Swihart and published by . This book was released on 1961 with total page 132 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Swept and Delta Wing Sense written by and published by . This book was released on 1955 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Some Section Modifications and Protuberances on the Zero lift Drag of Delta Wings at Transonic and Supersonic Speeds written by Carl A. Sandahl and published by . This book was released on 1954 with total page 48 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 Pressure Measurements at Transonic and Low Supersonic Speeds on a Thin Conical Cambered Low aspect ratio Delta Wing in Combination with Basic and Indented Bodies written by John P. Mugler and published by . This book was released on 1957 with total page 79 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure distributions on a thin conical cambered low-aspect-ratio delta wing have been obtained in the Langley 8-foot transonic tunnel over a Mach number range from 0.60 to 1.12 and at a Mach number of 1.43. Data were obtained for the wing in combination with a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2. The angle-of-attack range was from -4 to 20 degrees in most instances.

Download or read book Prediction of Transonic Vortex Flows Using Linear and Nonlinear Turbulent Eddy Viscosity Models written by Robert E. Bartels and published by . This book was released on 2000 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Threee-dimensional transonic flow over a delta wing is investigated with a focus on the effect of transition and influence of turbulence stress anisotropies. The performance of linear eddy viscosity models and an explicit algebraic stress model is assessed at the start of the vortex flow, and the results compared with experimental data. To assess the effect of transition location, computations that either fix transition or are fully turbulent are performed. To assess the effect of the turbulent stress ansiotropy, comparisons are made between predictions from the algebraic stress model and the linear eddy viscosity models. Both transition location and turbulent stress anisotropy significantly affect the 3D flow field. The most significant effect is found to be the modeling of transition location. At a Mach number of 0.90, the computed solution changes character from steady to unsteady depending on transition onset. Accounting for the anisotropies in the turbulent stresses also considerably impacts the flow, most notably in the outboard region of flow separation.

Download or read book Transonic and Supersonic Flow Past a 65 Degree Delta Wing with Rounded Leading Edges Analysis of Experimental Data written by Krishnaswami Yegna Narayan and published by . This book was released on 1988 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: