Trailing: A Memoir was VOTED ONE OF THE BEST INDIE BOOKS OF 2013!Something unexpected occurs when Kristin Louise Duncombe moves to New Orleans to begin her adult life as a psychotherapist: She falls madly in love with a Médecins Sans Frontières doctor, abandons all of her plans, and follows him on a medical mission to East Africa. Faced with the dual culture shock of Kenya and life with the MSF team, Kristin struggles to craft a new existence in a context of mishap, witchcraft, and the life or death stakes of the MSF world. Just when she has managed to establish a life for herself in Nairobi, a violent carjacking catapults her into a state of acute post-traumatic stress, and her life thereafter devolves into a world of intense anxiety that permeates every aspect of her existence. Forced to examine questions about her relationship, career, and personal identity, she struggles to save her marriage while facing the most difficult fight of her life: saving herself. Duncombe's debut, as humorous as it is harrowing, provides an insider's view of an MSF marriage and the humanitarian crisis in East Africa. Probing deeply into her tumultuous search for identity, she captures the essence of the experience with extraordinary authenticity and honesty. An altogether life-altering journey to the core of the human soul, Trailing: A Memoir is a compulsive page-turner, as fascinating as it is life affirming.

The effects of variation of trailing-edge angle and trailing-edge thickness on the lift characteristics of a 10-percent-chord thick symmetrical NACA airfoil section with a 25-percent-chord plain flap are appraised from wind-tunnel tests at Mach numbers from 0.3 to 0.9 and Reynolds numbers varying correspondingly from 1 to 2 million. The airfoil trailing-edge angle was varied from approximately 18 to 6 degrees, and the trailing-edge thickness from zero to the thickness at the flap hinge line.

The pressres acting on the base of blunt-trailing-edge airfoils have been measured at Mach numbers of 1.25, 1.5, 2.0, and 3.1 and at Reynolds numbers from 0.2 to 3.8 million. Data are presented for 29 profiles both with laminar and with turbulent boundary layers approaching the trailing edges of the wings. The base pressure is found to be a function primarily of Mach number and the ratio of the boundary layer thickeness at the trailing edge to the trailing-edge thickness.

The experimental and analytical investigation included solid blades with five different trailing-edge thicknesses and four different trailing-edge geometries. One of the geometries was round, one was square, one was tapered from the suction surface, and the other tapered from the pressure surface. One of the trailing-edge thicknesses was sharp edged; the other four thicknesses were equivalent to about 5, 11, 16, and 20 percent of the blade throat width. The experimental results show increased efficiency loss for increased trailing-edge thickness for all trailing-edge geometries. The blade with round trailing edge, equal to about 11 percent of the blade throat width, had 60 percent more loss than the sharp-edged blade. For the same trailing-edge thickness, square trailing edges caused more loss than round trailing edges, and the tapered trailing edges caused about the same loss as the round trailing edges.