Abstract: Systems and methods for determining turbine engine system stability encompass measuring or otherwise determining values of performance parameters, storing a data set of such values in memory, generating a stability indicator, and displaying the stability indicator on an operator interface. The stability indicator is generated by a processor operating in data communication with the computer memory, utilizing customized software algorithms to remove high frequency components, apply an adaptive filter to adjust selected parameters according to a target value of a selected target parameter, and apply a stochastic filters to estimate true values of the selected parameters, based on the remaining variation.

Abstract: Systems and methods for determining turbine engine system stability encompass measuring or otherwise determining values of performance parameters, storing a data set of such values in memory, generating a stability indicator, and displaying the stability indicator on an operator interface. The stability indicator is generated by a processor operating in data communication with the computer memory, utilizing customized software algorithms to remove high frequency components, apply an adaptive filter to adjust selected parameters according to a target value of a selected target parameter, and apply a stochastic filters to estimate true values of the selected parameters, based on the remaining variation.

Abstract: A matrix or array of elongated tubular members, each member being formed by spirally winding a piece or pieces of material into a generally cylindrical shape, wherein the matrix or array is mounted in an airflow to reduce the noise associated with and/or produced by the airflow.

Abstract: A matrix or array of elongated tubular members, each member being formed by spirally winding a piece or pieces of material into a generally cylindrical shape, wherein the matrix or array is mounted in an airflow to reduce the noise associated with and/or produced by the airflow.

Abstract: A free fall simulator with a flight chamber, a fan system to generate airflow in the flight chamber, and a noise attenuation housing substantially enclosing the fan system.

Abstract: An open jet wind tunnel having a test section, a nozzle exit and a collector in which the leading edge of the collector is configured with at least a portion being non-uniformly spaced from the nozzle exit.

Abstract: An open jet wind tunnel having a test section, a nozzle exit and a collector in which the leading edge of the collector is configured with at least a portion being non-uniformly spaced from the nozzle exit.

Abstract: A wind tunnel and a heat exchanger for use in the wind tunnel. The heat exchanger is a plate-fin type heat exchanger having at least one heat exchanger unit with an inflow end and an outflow end, and air flow section and a coolant flow section. The air flow section includes fins generally aligned with the air flow through the exchanger and the coolant flow section includes fins defining a coolant passageway.

Abstract: A jet engine test cell capable of dissipating infrasound. The test cell includes an engine test section, an augmentor and an exhaust stack having a structure near its open end for dissipating infrasound.

Abstract: A free piston shock tube/tunnel and a diaphragm construction for a free piston shock tube tunnel in which the diaphragm is provided with multiple rupture areas.

Abstract: A free piston shot tube tunnel having a high speed valve for releasing the piston to start the piston shot. A further feature of the present invention is a free piston shock tube/tunnel having a high speed valve for releasing pressure from the compression tube into the shock tube.