Call Number (LC) Title Results
Y 3.N 21/5:6/1148 Flow tests of an NACA-designed supercharger inlet elbow and the effects of various components on the flow characteristics at the elbow outlet / 1
Y 3.N 21/5:6/1149 Performance of hoods for aircraft exhaust-gas turbines / 1
Y 3.N 21/5:6/1150 A Relaxation procedure for the stress analysis of a continuous beam-column elastically restrained against deflection and rotation at the supports / 1
Y 3.N 21/5:6/1151 Summary of drag characteristics of practical-construction wing sections / 1
Y 3.N 21/5:6/1152 Flight investigation of the effect of a local change in wing contour on chordwise pressure distribution at high speeds / 1
Y 3.N 21/5:6/1153 Foaming volume and foam stability / 1
Y 3.N 21/5:6/1154 A Comparison of the lateral motion calculated for tailless and conventional airplanes / 1
Y 3.N 21/5:6/1155 A Preliminary study of a propeller powered by gas jets issuing from the blade tips / 1
Y 3.N 21/5:6/1156 Column and plate compressive strengths of aircraft structural materials. : Extruded 0-1HTA magnesium alloy / 1
Y 3.N 21/5:6/1157 Compressive strength of 24S-T aluminum-alloy flat panels with longitudinal formed hat-section stiffeners / 1
Y 3.N 21/5:6/1158 Flutter and oscillating air-force calculations for an airfoil in a two-dimensional supersonic flow / 1
Y 3.N 21/5:6/1159 Turbosupercharger-rotor temperatures in flight / 1
Y 3.N 21/5:6/1160 The Infrared spectra of spiropentane, methylenecyclobutane, and 2-methyl-1-butene / 1
Y 3.N 21/5:6/1161 Effect of catalysts and pH on strength of resin-bonded plywood / 1
Y 3.N 21/5:6/1162 Effect of brake forming in various tempers on the strength of alclad 75S-T aluminum-alloy sheet / 1
Y 3.N 21/5:6/1163 The Synthesis and purification of aromatic hydrocarbons. : 4-1,2,3-trimethylbenzene / 1
Y 3.N 21/5:6/1164 The Synthesis and purification of aromatic hydrocarbons. : 5 - 1-ethyl-3-methylbenzene / 1
Y 3.N 21/5:6/1165 Tensile properties of a sillimanite refractory at elevated temperatures / 1
Y 3.N 21/5:6/1166 Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 0 degrees and -3 degrees trim and with a 22 1/2 degree angle of dead rise / 1
Y 3.N 21/5:6/1167 Pressure distributions and force tests of an NACA 65-210 airfoil section with a 50-percent-chord flap / 1