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Y 3.N 21/5:6/3119
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Static properties and resistance characteristics of a family of seaplane hulls having varying length-beam ratio / |
1 |
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Y 3.N 21/5:6/3120
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Span load distributions resulting from constant vertical acceleration for thin sweptback tapered wings with streamwise tips. : Supersonic leading and trailing edges / |
1 |
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Y 3.N 21/5:6/3121
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Some effects of aspect ratio and tail length on the contribution of a vertical tail to unsteady lateral damping and directional stability of a model oscillating continuously in yaw / |
1 |
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Y 3.N 21/5:6/3122
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Experimental investigation at a Mach number of 2.41 of average skin-friction coefficients and velocity profiles for laminar and turbulent boundary layers and an assessment of probe effects / |
1 |
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Y 3.N 21/5:6/3123
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Effect of various arrangements of triangular ledges on the performance of a 23 degree conical diffuser at subsonic Mach numbers / |
1 |
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Y 3.N 21/5:6/3124
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A method for estimating the effect of turbulent velocity fluctuations in the boundary layer on diffuser total-pressure-loss measurements / |
1 |
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Y 3.N 21/5:6/3125
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A simple mechanical analogue for studying the dynamic stability of aircraft having nonlinear moment characteristics / |
1 |
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Y 3.N 21/5:6/3126
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A design study of leading-edge inlets for unswept wings / |
1 |
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Y 3.N 21/5:6/3127
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The effectiveness at high subsonic Mach numbers of a 20-percent-chord plain traiiling-edge flap on the NACA 65-210 airfoil section / |
1 |
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Y 3.N 21/5:6/3128
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Comparison between theory and experiment for interference pressure field between wing and body at supersonic speeds / |
1 |
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Y 3.N 21/5:6/3129
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Investigation of a slat in several different positions on an NACA 64A010 airfoil for a wide range of subsonic Mach numbers / |
1 |
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Y 3.N 21/5:6/3130
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A procedure for the design of air-heated ice-prevention systems / |
1 |
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Y 3.N 21/5:6/3131
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On the kernel function of the integral equation relating the lift and downwash distributions of oscillating finite wings in subsonic flow / |
1 |
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Y 3.N 21/5:6/3132
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Fatigue tests at stresses producing failure in 2 to 10,000 cycles. : 24S-T3 and 75S-T6 aluminum-alloy sheet specimens with a theoretical stress-concentration factor of 4.0 subjected to completely reversed axial load / |
1 |
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Y 3.N 21/5:6/3133
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The free-stream boundaries of turbulent flows / |
1 |
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Y 3.N 21/5:6/3134
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A method for estimating variations in the roots of the lateral-stability quartic due to changes in mass and aerodynamic parameters of an airplane / |
1 |
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Y 3.N 21/5:6/3135
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Investigation of mutual interference effects of several vertical-tail-fuselage configurations in sideslip / |
1 |
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Y 3.N 21/5:6/3136
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Creep bending and buckling of linearly viscoelastic columns / |
1 |
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Y 3.N 21/5:6/3137
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Creep bending and buckling of nonlinearly viscoelastic columns / |
1 |
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Y 3.N 21/5:6/3138
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Creep buckling of columns / |
1 |
