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 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 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 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 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 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 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 Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 548 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 Presentation and Analysis of Results of an Unsteady Transonic Wind Tunnel Test on a Semi span Delta Wing Model Oscillating in Pitch written by E. G. M. Geurts and published by . This book was released on 1996 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Government Reports Announcements Index written by and published by . This book was released on 1996 with total page 740 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 Unsteady Low Speed Windtunnel Test of a Straked Delta Wing Oscillating in Pitch Part 4 Plots of Time Histories of Pressures and Overall Loads written by A. M Cunningham (Jr) and published by . This book was released on 1988 with total page 274 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of a wind tunnel test of an oscillating straked wing. The report provides 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. In part IV, the plots of time history data for both pressures and overall air loads for continuous oscillating model are presented for conditions in which non-linearities and higher harmonics are expected. Appendix A includes the pressure plots in a 'carpet' format which shows the distributions at every 45 deg of phase angle in a manner similar to the unsteady flow visualization photos. The distributions are shown similarly for all four pressure sections. A survey of the test conditions and their runnumbers is given in table 10 of part I. Appendix B includes plots of overall air loads vs. incidence for continuous oscillating model. A survey of the runnumbers of these plots is given in table 11 of part I. Keywords: Unsteady flow; Vortex flow; Wind tunnel test. (JHD).

Download or read book Unsteady Low Speed Windtunnel Test of a Straked Delta Wing Oscillating in Pitch Part 5 Power Spectral Density Plots of the Overall Loads for Harmonic Oscillation and the Response of Overall Loads to 1 COS Inputs written by and published by . This book was released on 1988 with total page 293 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of a wind tunnel test of an oscillating straked wing. The report provides 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. The power spectral densities for various conditions present the relative frequency content of selected overall loads at continuous oscillating model conditions ranging from nearly linear (first harmonic dominant) to highly nonlinear (many higher harmonics) characteristics. A survey of the selected runs and their test conditions is given including the components of the balance and the corresponding plotnumbers of the spectra presented. The time history plots are given of incidence and all air loads for (1-cos) pitch pulses that simulate transient aircraft maneuvers. Included are half pulse data which represent a pitch-up and hold at a higher angle of attack as well as a pitch-down and hold at a lower angle of attack. To give an idea of the reproducibility plots for all three runs of the balance components vs. incidence for two test conditions are also enclosed at the end. Keywords: Unsteady flow; Vortex flow; Wind tunnel test.

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:

Download or read book Unsteady Low Speed Wind Tunnel Test of a Straked Delta Wing Oscillating in Pitch Part 2 Plots of Steady and Zeroth and First Harmonic Unsteady Pressure Distributions written by and published by . This book was released on 1988 with total page 309 pages. Available in PDF, EPUB and Kindle. Book excerpt: Result of a wind tunnel test of an oscillating straked wing. The report provides 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. The plots of the pressure distributions included in this part are presented in the order of the run numbers. Tables 4 and 5 in part I provide a convenient cross reference of conditions and run numbers. All steady test cases which were covered in table 4 of part I are presented in appendix B for runs up to no. 674. All runs presented in this part relate to the test conditions of 80 m/s windspeed and zero sideslip. Keywords: Unsteady flow; Vortex flow; Wind tunnel test.

Download or read book Unsteady Low Speed Windtunnel Test of a Straked Delta Wing Oscillating in Pitch Part 6 Presentation of the Visualization Program written by A. M Cunningham (Jr) and published by . This book was released on 1988 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of a wind tunnel test of an oscillating straked wing. The report provides unsteady airloads and pressure distributions for a range of incidence ( -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. In part VI results of the flow visualization investigation are presented in the appendix in the form of tables and plots of vortex core positions, both as a function of phase angle during one cycle of oscillation. Table 13a through c in part I provides a convenient cross-reference of test conditions and the table numbers in this part. The phase angles are varied in steps on 45 deg so that a time history is developed during one cycle. When it was impossible to measure vortex core positions, due to either vortex burst or overexposure, no values are given in the tables and plots. Results are presented for the three laser light screen positions. The entries in the table for the aft position near the wing trailing edge are limited because very few core position measurements were possible due to vortex bursting. Keywords: Unsteady flow; Vortex flow; Wind tunnel test. (JHD).