Approximate Methods for Center of Pressure Prediction of Multi-Segment Wings

摘要

Approximate methods for predicting the center of pressure of multi- segment wings are presented. Only wings with breaks in the leading edge sweep are considered. The methods transform a multi-segment planform into an equivalent straight tapered planform. Comparisons are made with predictions from a vortex lattice code and experimental data at subsonic speeds and with predictions from a vortex lattice and an Euler code at supersonic speeds. The most accurate method studied had an average error in predicted center of pressure location of approximately 2 percent of the root chord.