Call Number (LC) Title Results
Y 3.N 21/5:6/1858 A review of analytical methods for the treatment of flows with detached shocks / 1
Y 3.N 21/5:6/1859 A method of calculating a stability boundary that defines a region of satisfactory period-damping relationship of the oscillatory mode of motion / 1
Y 3.N 21/5:6/1860 Theoretical lift and damping in roll of thin sweptback wings of arbitrary taper and sweep at supersonic speeds : Subsonic leading edges and trailing edges / 1
Y 3.N 21/5:6/1861 One-dimensional flows of an imperfect diatomic gas / 1
Y 3.N 21/5:6/1862 A Simple method of estimating the subsonic lift and damping in roll of sweptback wings / 1
Y 3.N 21/5:6/1863 Comparative strengths of some adhesive-adherend systems / 1
Y 3.N 21/5:6/1864 Extended applications of the hot-wire anemometer / 1
Y 3.N 21/5:6/1865 Further experiments on the flow and heat transfer in a heated turbulent air jet / 1
Y 3.N 21/5:6/1866 Spin-tunnel investigation to determine the effectiveness of a rocket for spin recovery / 1
Y 3.N 21/5:6/1867 A study of effects of heat treatment and hot-cold-work on properties of low-carbon N-155 alloy / 1
Y 3.N 21/5:6/1868 Correlation of pilot opinion of stall warning with flight measurements of various factors which produce the warning / 1
Y 3.N 21/5:6/1869 WInd-tunnel investigation of the opening characteristics, drag, and stability of several hemispherical parachutes / 1
Y 3.N 21/5:6/1870 Free-space oscillating pressures near the tips of rotating propellers / 1
Y 3.N 21/5:6/1871 A mathematical theory of plasticity based on the concept of slip / 1
Y 3.N 21/5:6/1872 High-lift and lateral control characteristics of an NACA 65₂-215 semispan wing equipped with plug and retractable ailerons and a full-span slotted flap / 1
Y 3.N 21/5:6/1873 Subsonic two-dimensional-flow conditions near an airfoil determined by static pressures measured at the tunnel wall / 1
Y 3.N 21/5:6/1874 Analysis of altitude compensation systems for aircraft carburetors / 1
Y 3.N 21/5:6/1875 On two-dimensional supersonic flows / 1
Y 3.N 21/5:6/1876 Calculation of the aerodynamic loading of flexible wings of arbitrary plan form and stiffness / 1
Y 3.N 21/5:6/1877 Effects of compressibility on lift and load characteristics of a tapered wing of NACA 64-210 airfoil sections up to a Mach number of 0.60 / 1