A system comprising: a first laser air data sensor (12, 25A) configured to emit first directional light into airflow about an aircraft exterior and to generate first air data parameter outputs for the aircraft based on returns of the emitted first directional light; and an acoustic air data sensor (14, 26) configured to: emit acoustic signals into the airflow about the aircraft exterior; sense the acoustic signals; and generate second air data parameter outputs for the aircraft based on the sensed acoustic signals, wherein the first laser air data sensor is a molecular-based laser air data sensor configured to: receive the returns of the emitted first directional light scattered by air molecules within the airflow about the aircraft exterior; and determine, based on the returns of the emitted first directional light scattered by the air molecules within the airflow, first static pressure of the airflow, first static air temperature of the airflow, first true airspeed of the airflow, and a first relative wind angle of the first laser air data sensor with respect to the airflow, and characterized in that the acoustic air data sensor is electrically coupled to receive the first static pressure of the airflow from the first laser air data sensor; and wherein the acoustic air data sensor includes a static pressure port or wherein the system comprises a first static pressure sensor electrically connected to the acoustic air data sensor, wherein the static pressure port or the first static pressure sensor is configured to sense second static pressure of the airflow about the aircraft exterior; and wherein the acoustic air data sensor is configured to determine the altitude of the aircraft based on the first static pressure of the airflow received from the first laser air data sensor and the second static pressure of the airflow sensed by the static pressure sensor; wherein the acoustic air data sensor is configured to generate the second air data parameter outputs as including the determined altitude. a first laser air data sensor (12, 25A) configured to emit first directional light into airflow about an aircraft exterior and to generate first air data parameter outputs for the aircraft based on returns of the emitted first directional light; and an acoustic air data sensor (14, 26) configured to: emit acoustic signals into the airflow about the aircraft exterior; sense the acoustic signals; and emit acoustic signals into the airflow about the aircraft exterior; sense the acoustic signals; and generate second air data parameter outputs for the aircraft based on the sensed acoustic signals, wherein the first laser air data sensor is a molecular-based laser air data sensor configured to: receive the returns of the emitted first directional light scattered by air molecules within the airflow about the aircraft exterior; and determine, based on the returns of the emitted first directional light scattered by the air molecules within the airflow, first static pressure of the airflow, first static air temperature of the airflow, first true airspeed of the airflow, and a first relative wind angle of the first laser air data sensor with respect to the airflow, and characterized in that the acoustic air data sensor is electrically coupled to receive the first static pressure of the airflow from the first laser air data sensor; and receive the returns of the emitted first directional light scattered by air molecules within the airflow about the aircraft exterior; and determine, based on the returns of the emitted first directional light scattered by the air molecules within the airflow, first static pressure of the airflow, first static air temperature of the airflow, first true airspeed of the airflow, and a first relative wind angle of the first laser air data sensor with respect to the airflow, and characterized in that the acoustic air data sensor is electrically coupled to receive the first static pressure of the airflow from the first laser air data sensor; and wherein the acoustic air data sensor includes a static pressure port or wherein the system comprises a first static pressure sensor electrically connected to the acoustic air data sensor, wherein the static pressure port or the first static pressure sensor is configured to sense second static pressure of the airflow about the aircraft exterior; and wherein the acoustic air data sensor is configured to determine the altitude of the aircraft based on the first static pressure of the airflow received from the first laser air data sensor and the second static pressure of the airflow sensed by the static pressure sensor; wherein the acoustic air data sensor is configured to generate the second air data parameter outputs as including the determined altitude.