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Y 3.N 21/5:6/4223
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Relation of journal bearing performance to minimum oil-film thickness / |
1 |
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Y 3.N 21/5:6/4224
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Effect of overheating on creep-rupture properties of M-252 alloy / |
1 |
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Y 3.N 21/5:6/4225
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Internal-friction study of aluminum alloy containing 4 weight percent copper / |
1 |
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Y 3.N 21/5:6/4226
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Analysis of harmonic forces produced at hub by imbalances in helicopter rotor blades / |
1 |
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Y 3.N 21/5:6/4227
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Drag minimization for wings in supersonic flow, with various constraints / |
1 |
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Y 3.N 21/5:6/4228
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Effects of fixing boundary-layer transition for an unswept-wing model and an evaluation of porous tunnel-wall interference for Mach numbers from 0.60 to 1.40 / |
1 |
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Y 3.N 21/5:6/4229
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Stagnation-point heat transfer to blunt shapes in hypersonic flight, including effects of yaw / |
1 |
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Y 3.N 21/5:6/4230
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Prandtl-Meyer expansion of chemically reacting gases in local chemical and thermodynamic equilibrium / |
1 |
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Y 3.N 21/5:6/4231
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Skin-friction measurements in incompressible flow / |
1 |
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Y 3.N 21/5:6/4232
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A method for the calculation of wave drag on supersonic-edged wings and biplanes / |
1 |
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Y 3.N 21/5:6/4233
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Experimental study of the equivalence of transonic flow about slender cone-cylinders of circular and elliptic cross section / |
1 |
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Y 3.N 21/5:6/4234
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Pressure distributions at transonic speeds for parabolic-arc bodies of revolution having fineness ratios of 10, 12, and 14 / |
1 |
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Y 3.N 21/5:6/4235
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Observations of turbulent-burst geometry and growth in supersonic flow / |
1 |
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Y 3.N 21/5:6/4236
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Effects of Mach number and wall-temperature ratio on turbulent heat transfer at Mach numbers from 3 to 5 / |
1 |
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Y 3.N 21/5:6/4237
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General instability of stiffened cylinders / |
1 |
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Y 3.N 21/5:6/4238
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Normal component of induced velocity for entire field of a uniformly loaded lifting rotor with highly swept wake as determined by electromagnetic analog / |
1 |
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Y 3.N 21/5:6/4239
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Experimental investigation of the drag of flat plates and cylinders in the slipstream of a hovering rotor / |
1 |
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Y 3.N 21/5:6/4240
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Some measurements of aerodynamic forces and moments at subsonic speeds on a rectangular wing of aspect ratio 2 oscillating about the midchord / |
1 |
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Y 3.N 21/5:6/4241
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An approximate method for design or analysis of two-dimensional subsonic-flow passages / |
1 |
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Y 3.N 21/5:6/4242
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General solutions for flow past slender cambered wings with swept trailing edges and calculation of additional loading due to control surfaces / |
1 |
