Drop tests of an idealized wing and alighting gear were made to provide an experimental check on methods for computing the transient bending stresses in the wing produced by a symmetrical vertical landing impact. The model was dropped in a nearly strain-free condition to make contact at a point below the center of gravity. The forces in the alighting gear, acceleration at the fuselage, and bending strains in the wing were recorded as a function of time. According to the statistical theory of Biot and Bisplinghoff, the computed maximum bending stresses, using the first three flexural modes, were found to be 43 to 137 percent greater than the measured values. Using the actual forcing function reduced the difference to less than 20 percent.