Conversion of Wing Surface Pressures Into Normalized Lift Coefficient

A normalized lift coefficient indicator has been developed for single-engine aircraft. The system developed incorporates a low-cost capacitance type pressure transducer and an electronic circuit to calculate the wing pressure coefficient. The system eliminates the need for probes protruding from the aircraft's wing by using two flush pressure taps on the wing surface and the aircraft's static pressures. The pressure taps have been located so as to produce a normalized lift coefficient display that is nearly linear, independent of flap setting, and independent of thrust. The system gives the aircraft's proximity to a stall condition regardless of its load factor, weight, or configuration. The preceding should reduce the fatal stall/spin accidents that are one of the foremost killers in general aviation.