Call Number (LC) Title Results
Y 3.N 21/5:6/2114 Theoretical lift and damping in roll of thin wings with arbitrary sweep and taper at supersonic speeds. : Supersonic leading and trailing edges / 1
Y 3.N 21/5:6/2115 Theoretical wave drags and pressure distributions for axially symmetric open-nose bodies / 1
Y 3.N 21/5:6/2116 Linearized supersonic axially symmetric flow about open-nosed bodies obtained by use of stream function / 1
Y 3.N 21/5:6/2117 Design and applications of hot-wire anemometers for steady-state measurements at transonic and supersonic airspeeds / 1
Y 3.N 21/5:6/2118 Investigation of a NACA high-speed optical torquemeter / 1
Y 3.N 21/5:6/2119 Effect of humidity on performance of turbojet engines / 1
Y 3.N 21/5:6/2120 Development and preliminary investigation of a method of obtaining hypersonic aerodynamic data by firing models through highly cooled gases / 1
Y 3.N 21/5:6/2121 Study of effects of sweep on the flutter of cantilever wings / 1
Y 3.N 21/5:6/2122 Theoretical calculations of the lateral force and yawing moment due to rolling at supersonic speeds for sweptback tapered wings with streamwise tips. : Subsonic leading edges / 1
Y 3.N 21/5:6/2123 Investigation of turbulent flow in a two-dimensional channel / 1
Y 3.N 21/5:6/2124 Spectrums and diffusion in a round turbulent jet / 1
Y 3.N 21/5:6/2125 Prandtl-Meyer flow for a diatomic gas of variable specific heat / 1
Y 3.N 21/5:6/2126 Improvements in heat transfer for anti-icing of gas-heated airfoils with internal fins and partitions / 1
Y 3.N 21/5:6/2127 An investigation of the effect of tetraethyl lead and ethyl nitrite on the autoignition characteristics of isooctane and triptane / 1
Y 3.N 21/5:6/2128 Investigation of 75-millimeter-bore cylindrical roller bearings at high speeds. 1
Y 3.N 21/5:6/2129 Method of calculating the lateral motions of aircraft based on the Laplace transform / 1
Y 3.N 21/5:6/2130 Calculation of transonic flows past thin airfoils by an integral method / 1
Y 3.N 21/5:6/2131 Boundary-layer transition on a cooled 20° cone at Mach numbers of 1.5 and 2.0 / 1
Y 3.N 21/5:6/2132 The calculation of modes and frequencies of a modified structure from those of the unmodified structure / 1
Y 3.N 21/5:6/2133 Investigation of separation of the turbulent boundary layer / 1