Response of state of Washington in opposition to Colville Indian Tribe\u27s motion for partial summary judgement

Response of State of Wash. In Opposition to Court\u27s Motion for Partial Summary Judgmen

Supplemental written closing argument - State of Washington

Wash. Supplemental Written Closing Argumen

Proposed Findings of fact and conclusions of law (pretrial submission of state of Washington)

State of Wash. Proposed Findings of Fact and Conclusions of La

Written closing argument - State of Washington

Wash. Written Closing Argumen

Consumers' willingness to pay for an animal welfare food label

Consumers increasingly rate the ethical dimensions of food production, including animal welfare, as important to them but how these concerns influence their food choices remains unclear. To address this, a Discrete Choice Experiment assesses consumers' willingness to pay for chicken meat. The study aims to understand the effects of food labels (RSPCA Assured and Red Tractor), cause-related marketing campaigns, and price on consumers' willingness to pay. Drawing on a representative sample of 401 British consumers, we estimate a mixed logit model using the hierarchical Bayesian estimation method. The results for the full sample reveal a substantial price premium associated with the animal welfare label (RSPCA Assured); however, this is less pronounced than one of the cause-related marketing campaigns. A latent class analysis identifies two distinct market segments, price sensitive and concerned consumers, which differ on socio-economic and behavioural characteristics. Amongst price sensitive consumers, willingness to pay extra for an animal welfare label is negligible. Complementary, qualitative interviews reveal consumers' difficulties in comparing the varying standards that underpin quality assurance schemes

Numerical Modeling of Flow Control in a Boundary-Layer-Ingesting Offset Inlet Diffuser at Transonic Mach Numbers

This paper will investigate the validation of the NASA developed, Reynolds-averaged Navier-Stokes (RANS) flow solver, OVERFLOW, for a boundary-layer-ingesting (BLI) offset (S-shaped) inlet in transonic flow with passive and active flow control devices as well as a baseline case. Numerical simulations are compared to wind tunnel results of a BLI inlet experiment conducted at the NASA Langley 0.3-Meter Transonic Cryogenic Tunnel. Comparisons of inlet flow distortion, pressure recovery, and inlet wall pressures are performed. The numerical simulations are compared to the BLI inlet data at a free-stream Mach number of 0.85 and a Reynolds number of approximately 2 million based on the fanface diameter. The numerical simulations with and without tunnel walls are performed, quantifying tunnel wall effects on the BLI inlet flow. A comparison is made between the numerical simulations and the BLI inlet experiment for the baseline and VG vane cases at various inlet mass flow rates. A comparison is also made to a BLI inlet jet configuration for varying actuator mass flow rates at a fixed inlet mass flow rate. Overall, the numerical simulations were able to predict the baseline circumferential flow distortion, DPCP avg, very well within the designed operating range of the BLI inlet. A comparison of the average total pressure recovery showed that the simulations were able to predict the trends but had a negative 0.01 offset when compared to the experimental levels. Numerical simulations of the baseline inlet flow also showed good agreement with the experimental inlet centerline surface pressures. The vane case showed that the CFD predicted the correct trends in the circumferential distortion levels for varying inlet mass flow but had a distortion level that was nearly twice as large as the experiment. Comparison to circumferential distortion measurements for a 15 deg clocked 40 probe rake indicated that the circumferential distortion levels are very sensitive to the symmetry of the flow and that a misalignment of the vanes in the experiment could have resulted in this difference. The numerical simulations of the BLI inlet with jets showed good agreement with the circumferential inlet distortion levels for a range of jet actuator mass flow ratios at a fixed inlet mass flow rate. The CFD simulations for the jet case also predicted an average total pressure recovery offset that was 0.01 lower than the experiment as was seen in the baseline. Comparisons of the flow features for the jet cases revealed that the CFD predicted a much larger vortex at the engine fan-face when compare to the experiment