The experiment was intended to assist in assessing the validity of the simple sweepback concepts currently in use, particularly for predicting the flow about infinite sweptback wings from two-dimensional data. The three-dimensional effects present are reduced to some extent by the type of section used, especially at transonic speeds, and the measured pressure distributions at a particular spanwise station, and the associated pressure forces (normal and chordwise) correlate quite well on the basis of the simple theory. In addition it is shown that the general flow development, including the initial growth of the leading-edge separation, and the transonic flow-attachment about the leading edge also correlate satisfactorily, as do the pressures measured on the base of the single-wedge wing.
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