Author: Neal M. Chaderjian
Publisher:
ISBN:
Category :
Languages : en
Pages : 8
Book Description
The IAR/WL 65 deg. delta wing experimental results provide both detail pressure measurements and a wide range of flow conditions covering from simple attached flow, through fully developed vortex and vortex burst flow, up to fully-stalled flow at very high incidence. Thus, the Computational Unsteady Aerodynamics researchers can use it at different level of validating the corresponding code. In this section a range of CFD results are provided for the 65 deg. delta wing at selected flow conditions. The time-dependent, three-dimensional, Reynolds-averaged, Navier-Stokes (RANS) equations are used to numerically simulate the unsteady vortical flow. Two sting angles and two large-amplitude, high-rate, forced-roll motions and a damped free-to-roll motion are presented. The free-to-roll motion is computed by coupling the time-dependent RANS equations to the flight dynamic equation of motion. The computed results are compared with experimental pressures, forces, moments and roll angle time history. In addition, surface and off-surface flow particle streaks are also presented.
Large-Amplitude, High-Rate Roll Oscillations of a 65 Deg. Delta Wing at High Incidence
Author: Neal M. Chaderjian
Publisher:
ISBN:
Category :
Languages : en
Pages : 8
Book Description
The IAR/WL 65 deg. delta wing experimental results provide both detail pressure measurements and a wide range of flow conditions covering from simple attached flow, through fully developed vortex and vortex burst flow, up to fully-stalled flow at very high incidence. Thus, the Computational Unsteady Aerodynamics researchers can use it at different level of validating the corresponding code. In this section a range of CFD results are provided for the 65 deg. delta wing at selected flow conditions. The time-dependent, three-dimensional, Reynolds-averaged, Navier-Stokes (RANS) equations are used to numerically simulate the unsteady vortical flow. Two sting angles and two large-amplitude, high-rate, forced-roll motions and a damped free-to-roll motion are presented. The free-to-roll motion is computed by coupling the time-dependent RANS equations to the flight dynamic equation of motion. The computed results are compared with experimental pressures, forces, moments and roll angle time history. In addition, surface and off-surface flow particle streaks are also presented.
Publisher:
ISBN:
Category :
Languages : en
Pages : 8
Book Description
The IAR/WL 65 deg. delta wing experimental results provide both detail pressure measurements and a wide range of flow conditions covering from simple attached flow, through fully developed vortex and vortex burst flow, up to fully-stalled flow at very high incidence. Thus, the Computational Unsteady Aerodynamics researchers can use it at different level of validating the corresponding code. In this section a range of CFD results are provided for the 65 deg. delta wing at selected flow conditions. The time-dependent, three-dimensional, Reynolds-averaged, Navier-Stokes (RANS) equations are used to numerically simulate the unsteady vortical flow. Two sting angles and two large-amplitude, high-rate, forced-roll motions and a damped free-to-roll motion are presented. The free-to-roll motion is computed by coupling the time-dependent RANS equations to the flight dynamic equation of motion. The computed results are compared with experimental pressures, forces, moments and roll angle time history. In addition, surface and off-surface flow particle streaks are also presented.
Selected Data Set from Static and Rolling Experiments on a 65 Deg. Delta Wing at High Incidence
Author: X. Z. Huang
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
Book Description
This data set is selected from an extensive set of experimental results obtained for configurations with a 650 delta wing under static as well as large-amplitude high-rate rolling or pitching conditions at high incidence. The experiments were performed under a joint research program on "Non-Linear Aerodynamics under Dynamic Maneuvers" by the National Research Council of Canada (NRC (IAR)), the U.S. Air Force (USAF (AFOSR, AFRL)) and the Canadian Dept. for National Defence (DND). NASA Ames informally participated in the program through its substantial CFD work on specific test conditions. The experimental results provide both detail pressure measurements and a wide range of flow conditions covering from simple attached flow, through fully developed vortex and vortex burst flow, up to fully-stalled flow at very high incidence. Since this data set includes different levels of physical difficulty, the computational researchers wording in unsteady aerodynamics can use it as a staircase approach to the problem of validating their corresponding code Four schematic and representative configurations' were selected in the experiments (Fig. 1 to Fig. 3).
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
Book Description
This data set is selected from an extensive set of experimental results obtained for configurations with a 650 delta wing under static as well as large-amplitude high-rate rolling or pitching conditions at high incidence. The experiments were performed under a joint research program on "Non-Linear Aerodynamics under Dynamic Maneuvers" by the National Research Council of Canada (NRC (IAR)), the U.S. Air Force (USAF (AFOSR, AFRL)) and the Canadian Dept. for National Defence (DND). NASA Ames informally participated in the program through its substantial CFD work on specific test conditions. The experimental results provide both detail pressure measurements and a wide range of flow conditions covering from simple attached flow, through fully developed vortex and vortex burst flow, up to fully-stalled flow at very high incidence. Since this data set includes different levels of physical difficulty, the computational researchers wording in unsteady aerodynamics can use it as a staircase approach to the problem of validating their corresponding code Four schematic and representative configurations' were selected in the experiments (Fig. 1 to Fig. 3).
Experimental Determination of the Effects of Frequency and Amplitude of Oscillation on the Roll-stability Derivatives for a 60 Degree Delta-wing Airplane Model
Author: Lewis R. Fisher
Publisher:
ISBN:
Category : Vibration
Languages : en
Pages : 54
Book Description
Publisher:
ISBN:
Category : Vibration
Languages : en
Pages : 54
Book Description
Large-amplitude High-rate Roll Experiments on a Delta and Double Delta Wing
Author: E. S. Hanff
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 568
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 568
Book Description
Low-speed Investigation of the Effects of Frequency and Amplitude of Oscillation in Sideslip on the Lateral Stability Derivatives of a 60 Degree Delta Wing, a 40 Degree Sweptback Wing and an Unswept Wing
Author: Jacob H. Lichtenstein
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
Book Description
International Aerospace Abstracts
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 974
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 974
Book Description
Journal of Aircraft
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
Book Description
NASA SP.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 360
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 360
Book Description
30th Aerospace Sciences Meeting and Exhibit: 92-0670 - 92-0719
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 566
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 566
Book Description