Call Number (LC) Title Results
Y 3.N 21/5:6/4226 Analysis of harmonic forces produced at hub by imbalances in helicopter rotor blades / 1
Y 3.N 21/5:6/4227 Drag minimization for wings in supersonic flow, with various constraints / 1
Y 3.N 21/5:6/4228 Effects of fixing boundary-layer transition for an unswept-wing model and an evaluation of porous tunnel-wall interference for Mach numbers from 0.60 to 1.40 / 1
Y 3.N 21/5:6/4229 Stagnation-point heat transfer to blunt shapes in hypersonic flight, including effects of yaw / 1
Y 3.N 21/5:6/4230 Prandtl-Meyer expansion of chemically reacting gases in local chemical and thermodynamic equilibrium / 1
Y 3.N 21/5:6/4231 Skin-friction measurements in incompressible flow / 1
Y 3.N 21/5:6/4232 A method for the calculation of wave drag on supersonic-edged wings and biplanes / 1
Y 3.N 21/5:6/4233 Experimental study of the equivalence of transonic flow about slender cone-cylinders of circular and elliptic cross section / 1
Y 3.N 21/5:6/4234 Pressure distributions at transonic speeds for parabolic-arc bodies of revolution having fineness ratios of 10, 12, and 14 / 1
Y 3.N 21/5:6/4235 Observations of turbulent-burst geometry and growth in supersonic flow / 1
Y 3.N 21/5:6/4236 Effects of Mach number and wall-temperature ratio on turbulent heat transfer at Mach numbers from 3 to 5 / 1
Y 3.N 21/5:6/4237 General instability of stiffened cylinders / 1
Y 3.N 21/5:6/4238 Normal component of induced velocity for entire field of a uniformly loaded lifting rotor with highly swept wake as determined by electromagnetic analog / 1
Y 3.N 21/5:6/4239 Experimental investigation of the drag of flat plates and cylinders in the slipstream of a hovering rotor / 1
Y 3.N 21/5:6/4240 Some measurements of aerodynamic forces and moments at subsonic speeds on a rectangular wing of aspect ratio 2 oscillating about the midchord / 1
Y 3.N 21/5:6/4241 An approximate method for design or analysis of two-dimensional subsonic-flow passages / 1
Y 3.N 21/5:6/4242 General solutions for flow past slender cambered wings with swept trailing edges and calculation of additional loading due to control surfaces / 1
Y 3.N 21/5:6/4243 An experimental study of the turbulent boundary layer on a shock-tube wall / 1
Y 3.N 21/5:6/4244 On solutions for the transient response of beams / 1
Y 3.N 21/5:6/4245 Flutter analysis of rectangular wings of very low aspect ratio / 1