Experimentally determined influence coefficients are presented for the deflection of two solid delta wings - one wing of constant thickness and the other of constant thickness ratio - having a carry-through-bay chord smaller than the wing root chord. A theoretical method of analysis is demonstrated for the constant-thickness wing under tip load, and the theoretical results are compared with the experimental results. The theoretical tip-load deflection for a constant-thickness delta wing elastically supported by a carry-through bay of width 35 percent of the wing root chord is twice as large at the tip as the theoretical tip-load deflection for a similar wing clamped 100 percent of the chord at the root.
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