The boundary layer transition behavior on flat plate delta wings, marked by an outward shift of the secondary separation line, has been investigated for a series of sweep angles. The effects of Reynolds number and angle of attack have been examined using surface visualization and five hole probe flow-field measurements. The Reynolds number scaled by the local span provides a method to correlate transition location across different planforms. The transition location moved forward on the wing with increases in freestream velocity, angle of attack, or apex angle. An increase in any of these variables also resulted in an increase of the cross-flow circulation above the wing. The onset of transition was found to be directly correlated of the vortex strength based on the cross-flow circulation.
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