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Aerodynamic assessment of icing effects on swept wings is an important component of a larger effort to improve three-dimensional icing simulation capabilities. An understanding of ice-shape geometric fidelity and Reynolds and Mach number effects on iced-wing aerodynamics is needed to guide the development and validation of ice-accretion simulation tools. To this end, wind-tunnel testing was carried out for 8.9% and 13.3% scale semispan wing models based upon the Common Research Model airplane configuration. Various levels of geometric fidelity of an artificial ice shape representing a realistic glaze-ice accretion on a swept wing were investigated. The highest fidelity artificial ice shape reproduced all of the three-dimensional features associated with the glaze ice accretion. The lowest fidelity artificial ice shapes were simple, spanwise-varying horn ice geometries intended to represent the maximum ice thickness on the wing upper surface.

Understanding the aerodynamic impact of swept-wing ice accretions is a crucial component of the design of modern aircraft. Computer-simulation tools are commonly used to approximate ice shapes, so the necessary level of detail or fidelity of those simulated ice shapes must be understood relative to high-fidelity representations of the ice. Previous tests were performed in the NASA Icing Research Tunnel to acquire high-fidelity ice shapes. From this database, full-span artificial ice shapes were designed and manufactured for both an 8.9%-scale and 13.3%-scale semispan wing model of the CRM65 which has been established as the full-scale baseline for this swept-wing project. These models were tested in the Walter H. Beech wind tunnel at Wichita State University and at the ONERA F1 facility, respectively. The data collected in the Wichita St.

Previous studies have shown that occupant kinematics in lateral impacts are different for near- and far-side occupants. Additionally, injuries to far-side occupants in high-speed lateral impacts have been better documented in the scientific literature; few studies have looked at low-speed far-side occupants. The purpose of this study was to determine the risk of lumbar spine injury for restrained and unrestrained far-side occupants in low- to moderate- speed lateral impacts. The NASS/CDS database was queried for far-side occupants in lateral impacts for different levels of impact severity (categorized by Delta-V): 0 to 8 km/h, 8 to 16 km/h, 16 to 24 km/h and 24 to 32 km/h. To further understand the lumbar spine injuries sustained by occupants in real-world impacts, far-side lateral impact tests with ATDs from the NHTSA Biomechanics Test Database were used to estimate lumbar loads in generic far-side sled tests.