Call Number (LC) Title Results
Y 3.N 21/5:6/2187 Bonding investigation of titanium carbide with various elements / 1
Y 3.N 21/5:6/2188 Experimental investigation of stiffened circular cylinders subjected to combined torsion and compression / 1
Y 3.N 21/5:6/2189 The development and performance of two small tunnels capable of intermittent operation at Mach numbers between 0.4 and 4.0 / 1
Y 3.N 21/5:6/2190 The use of an uncalibrated cone for determination of flow angles and Mach numbers at supersonic speeds / 1
Y 3.N 21/5:6/2191 Theoretical investigation and application of transonic similarity law for two dimensional flow / 1
Y 3.N 21/5:6/2192 A survey of the flow at the plane of the propeller of a twin-engine airplane / 1
Y 3.N 21/5:6/2193 Effect of heat-capacity lag on a variety of turbine-nozzle flow processes / 1
Y 3.N 21/5:6/2194 The NACA oil-damped V-G recorder / 1
Y 3.N 21/5:6/2195 A flight investigation and analysis of the lateral-oscillation characteristics of an airplane / 1
Y 3.N 21/5:6/2196 Effect of heat-capacity lag on the flow through oblique shock waves / 1
Y 3.N 21/5:6/2197 Pressure distribution and damping in steady pitch at supersonic Mach numbers of flat swept-back wings having all edges subsonic / 1
Y 3.N 21/5:6/2198 Sintering mechanism between zirconium carbide and columbium / 1
Y 3.N 21/5:6/2199 Wind-tunnel investigation at low speed of the lateral control characteristics of an unswept untapered semispan wing of aspect ratio 3.13 equipped with various 25-percent-chord plain ailerons / 1
Y 3.N 21/5:6/2200 A study of second-order supersonic-flow theory / 1
Y 3.N 21/5:6/2201 Measurement of the moments of inertia of an airplane by a simplified method / 1
Y 3.N 21/5:6/2202 Effect of heat and power extraction on turbojet-engine performance. : 3 - Analytical determination of effects of shaft-power extraction / 1
Y 3.N 21/5:6/2203 Boundary-layer measurements in 3.84- by 10-inch supersonic channel / 1
Y 3.N 21/5:6/2204 Gust-tunnel investigation of a wing model with semichord line swept back 60 degrees / 1
Y 3.N 21/5:6/2205 Theoretical supersonic characteristics of inboard trailing-edge flaps having arbitrary sweep and taper. : Mach lines behnid flap leading and trailing edges / 1
Y 3.N 21/5:6/2206 Graphical method for obtaining flow field in two-dimensional supersonic stream to which heat is added / 1