Call Number (LC) Title Results
Y 3.N 21/5:6/2727 Experiments in external noise reduction of a small pusher-type amphibian airplane / 1
Y 3.N 21/5:6/2728 Experiments to determine neighborhood reactions to light airplanes with and without external noise reduction / 1
Y 3.N 21/5:6/2729 An analysis of supersonic flow in the region of the leading edge of curved airfoils, including charts for determining surface-pressure gradient and shock-wave curvature / 1
Y 3.N 21/5:6/2730 Choking of a subsonic induction tunnel by the flow from an induction nozzle / 1
Y 3.N 21/5:6/2731 Influence of structure on properites of sintered chromium carbide / 1
Y 3.N 21/5:6/2732 Theoretical investigation of velocity diagrams of a single-stage turbine for a turbojet engine at maximum thrust per square foot turbine frontal area / 1
Y 3.N 21/5:6/2733 Method for calculation of heat transfer in laminar region of air flow around cylinders of arbitrary cross section (including large temperature differences and transpiration cooling) / 1
Y 3.N 21/5:6/2734 Summary of available hail literature and the effect of hail on aircraft in flight / 1
Y 3.N 21/5:6/2735 An analysis of the normal accelerations and airspeeds of a two-engine type of transport airplane in commercial operations on routes in the central United States from 1948 to 1950 / 1
Y 3.N 21/5:6/2736 Two-dimensional shear flow in a 90 degree elbow / 1
Y 3.N 21/5:6/2737 Plastic stress-strain relations for combined tension and compression / 1
Y 3.N 21/5:6/2738 A probability analysis of the meteorological factors conductive to aircraft icing in the United States / 1
Y 3.N 21/5:6/2739 Numerical determination of indicial lift and moment functions for a two-dimensional sinking and pitching airfoil at Mach numbers 0.5 and 0.6 / 1
Y 3.N 21/5:6/2740 Experimental investigation of the local and average skin friction in the laminar boundary layer on a flat plate at a Mach number of 2.4 / 1
Y 3.N 21/5:6/2741 Investigation of the influence of fuselage and tail surfaces on low-speed static stability and rolling characteristics of a swept-wing model / 1
Y 3.N 21/5:6/2742 Boundary-layer development and skin friction at Mach number 3.05 / 1
Y 3.N 21/5:6/2743 Landing-gear impact / 1
Y 3.N 21/5:6/2744 Practical calculation of second-order supersonic flow past nonlifting bodies of revolution / 1
Y 3.N 21/5:6/2745 Influence of chemical composition on rupture test properties at 1500 degrees F of forged chromium-cobalt-nickel-iron base alloys / 1
Y 3.N 21/5:6/2746 Preview of behavior of grain boundaries in creep of aluminum bicrystals / 1