Call Number (LC) Title Results
Y 3.N 21/5:6/3485 An approximate solution for axially symmetric flow over a cone with an attached shock wave / 1
Y 3.N 21/5:6/3486 Measurements of turbulent skin friction on a flat plate at transonic speeds / 1
Y 3.N 21/5:6/3487 Acoustic radiation from two-dimensional rectangular cutouts in aerodynamic surfaces / 2
Y 3.N 21/5:6/3488 Some measurements of flow in a rectangular cutout / 1
Y 3.N 21/5:6/3490 Experimental and calculated temperature and mass histories of vaporizing fuel drops / 1
Y 3.N 21/5:6/3491 Experimental investigation of eccentricity ratio, friction, and oil flow of long and short journal bearings with load-number charts / 1
Y 3.N 21/5:6/3492 Determination of inflow distributions from experimental aerodynamic loading and blade-motion data on a model helicopter rotor in hovering and forward flight / 1
Y 3.N 21/5:6/3493 Development of equipment and of experimental techniques for column creep tests / 1
Y 3.N 21/5:6/3494 Sound propagation into the shadow zone in a temperature-stratified atmosphere above a plane boundary / 1
Y 3.N 21/5:6/3495 Failure of materials under combined repeated stresses with superimposed static stresses / 1
Y 3.N 21/5:6/3496 Flight testing by radio remote control - flight evaluation of a beep-control system / 1
Y 3.N 21/5:6/3497 Summary of results of a wind-tunnel investigation of nine related horizontal tails / 1
Y 3.N 21/5:6/3498 Exploratory investigation of an airfoil with area suction applied to a porous, round trailing edge fitted with a lift-control vane / 1
Y 3.N 21/5:6/3499 Calculation of the supersonic pressure distribution on a single-curved tapered wing in regions not influenced by the root or tip / 1
Y 3.N 21/5:6/3500 Correction of additional span loadings computed by the Weissinger seven-point method for moderately tapered wings of high aspect ratio / 1
Y 3.N 21/5:6/3501 The transonic characteristics of 22 rectangular, symmetrical wing models of varying aspect ratio and thickness / 1
Y 3.N 21/5:6/3502 The transonic characteristics of 38 cambered rectangular wings as varying aspect ratio and thickness as determined by the transonic-bump technique / 1
Y 3.N 21/5:6/3503 Reduction of profile drag at supersonic velocities by the use of airfoil sections having a blunt trailing edge / 1
Y 3.N 21/5:6/3504 Effect of trailing-edge thickness on lift at supersonic velocities / 1
Y 3.N 21/5:6/3505 An experimental investigation of regions of separated laminar flow / 1