Comparison of Experimental and Numerical Results for the Interaction of a Scale Model Aircraft with a Simulated Lightning Channel

Abstract

Results are given which compare measured and computed responses for a scale model aircraft in a simulated attached lightning channel. A scale model of the NASA Langley FI06 lightning research aircraft was suspended by a wire simulating the channel. A pulse was injected on the wire and subsequently inter­ acted with the aircraft model. Sensors on the model recorded surface magnetic and electric field deriva­ tives. Numerical simulations of this configuration were made with a three dimensional fin ite difference code for four entry/exit point configurations. Good agreement was obtained.