Call Number (LC) Title Results
Y 3.N 21/5:11/L688 Tank tests of a 1/8-size dynamic model of the PB2Y-3 airplane with increased power - NACA model 131 / 1
Y 3.N 21/5:11/L689 Cooling investigation of a B-24D engine-nacelle installation in the NACA full-scale tunnel / 1
Y 3.N 21/5:11/L69 Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 6 degrees and 9 degrees trim and a 22.5 degree angle of dead rise / 1
Y 3.N 21/5:11/L690 Preliminary data on buckling strength of curved sheet panels in compression / 1
Y 3.N 21/5:11/L691 Critical compressive stress for curved sheet supported along all edges and elastically restrained against rotation along the unloaded edges / 1
Y 3.N 21/5:11/L692 A preliminary theoretical study of helicopter-blade flutter involving dependence upon coning angle and pitch setting / 1
Y 3.N 21/5:11/L693 Wind-tunnel investigation of an NACA 23012 airfoil with a 30 percent chord Maxwell slate and with trailing-edge flaps / 1
Y 3.N 21/5:11/L694 Preliminary investigation in the NACA low-turbulence tunnel of low-drag airfoil sections suitable for admitting air at the leading edge / 1
Y 3.N 21/5:11/L695 Some lift and drag measurements of a representative bomber nacelle on a low-drag wing. : Part 1 / 1
Y 3.N 21/5:11/L696 Some lift and drag measurements of a representative bomber nacelle on a low-drag wing. : Part 2 / 1
Y 3.N 21/5:11/L697 Wind-tunnel investigation of a low-drag airfoil section with a double slotted flap / 1
Y 3.N 21/5:11/L698 Effects of a typical nacelle on the characteristics of a thick low-drag airfoil critically affected by leading-edge roughness / 1
Y 3.N 21/5:11/L699 Effects of mean-line loading on the aerodynamic characteristics of some low-drag airfoils / 1
Y 3.N 21/5:11/L7 Wind-tunnel investigation of an NACA 23021 airfoil with a 0.32-airfoil-chord double slotted flap / 1
Y 3.N 21/5:11/L70 Theoretical and experimental dynamic loads for a prismatic float having an angle of dead rise of 22.5 degrees / 1
Y 3.N 21/5:11/L700 Pressure-distribution measurements of two airfoil models with Fowler flaps submitted by Consolidated Aircraft Corporation as alternative wing sections of the XB-32 airplane / 1
Y 3.N 21/5:11/L701 Test of NACA 66,2-116, a = 0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane / 1
Y 3.N 21/5:11/L702 Wind-tunnel investigation of a revised horizontal tail surface for the Grumman TBF-1 airplane / 1
Y 3.N 21/5:11/L703 Lift and drag characteristics of a low-drag airfoil with slotted flap submitted by Curtiss-Wright Corporation / 1
Y 3.N 21/5:11/L704 Tests of four models representing intermediate sections of the XB-33 airplane including sections with slotted flap and ailerons / 1