Abstract: Systems and methods for autonomously operating an antenna assembly. The methods comprise: obtaining, by a processor of the antenna assembly, first information comprising at least one of a value for a variable altitude of the antenna assembly, a value for a variable height of the antenna assembly above ground, a value for a variable height of the antenna assembly above sea level, a value for a variable distance of the antenna assembly from a reference object, and a first value for a variable signal frequency of a communication device; using, by the processor, the information to obtain a desired length of an antenna of the antenna assembly; and controlling, by the processor, an actuator to adjust a length of the antenna until the length reaches the desired length.

Abstract: A method includes obtaining a plurality of user accounts each including a user profile, a network strategy, and plurality of primary connections. Each primary connection defines a primary relationship between a respective user account and a different user account. The method also includes determining a target user account from the plurality of user accounts and identifying a first user account using one of the plurality of primary connections of the target user account. The method also includes determining a second user account using one of the plurality of primary connections of the first user account. Here, the second user account lacks a primary relationship with the target user account. The method also includes generating a networking recommendation based on text corresponding to the target user account and text corresponding to the second user account. The method also includes transmitting a notification including the networking recommendation to a user device.

Abstract: A turbine blade, airfoil, and rotor stage for a gas turbine engine is disclosed. The turbine blade, airfoil, and rotor stage each includes an uncoated airfoil profile in accordance with Cartesian coordinate values of X, Y, and Z disclosed herein. The resulting airfoil exhibits high flutter margins, thus enabling the gas turbine engine to be operated at an increased power output while avoiding operational limitations required in known gas turbine engines.

Abstract: A turbine blade, airfoil, and rotor stage for a gas turbine engine is disclosed. The turbine blade, airfoil, and rotor stage each includes an uncoated airfoil profile in accordance with Cartesian coordinate values of X, Y, and Z disclosed herein. The resulting airfoil exhibits high flutter margins, thus enabling the gas turbine engine to be operated at an increased power output while avoiding operational limitations required in known gas turbine engines.