Aerodynamic Characteristics of Several Flap-type Trailing-edge Controls on a Trapezoidal Wing at Mach Numbers of 1.61 and 2.01
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Lord, Douglas R↗
Engineering topics
Czarnecki, K R
Publications and source records attributed to Czarnecki, K R.
An exploratory investigation of skin friction and transition on three bodies of revolution at a Mach number of 1.61
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Hilton, John H , Jr↗
Investigation of Distributed Surface Roughness on a Body of Revolution at a Mach Number of 1.61
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Czarnecki, K R↗
Preliminary Investigation of the Effects of Heat Transfer on Boundary-layer Transition on a Parabolic Body of Revolution (NACA RM-10) at a Mach Number of 1.61
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FLOW, TURBULENT↗
An Extension of the Investigation of the Effects of Heat Transfer on Boundary-layer Transition on a Parabolic Body of Revolution (NACA RM-10) at a Mach Number of 1.61
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BODIES - SURFACE CONDITIONS↗
Aerodynamic characteristics of a full-span trailing-edge control on a 60 degree delta wing with and without a spoiler at Mach number 1.61
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Lord, Douglas R↗
Recent information on flap and tip controls
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Lord, Douglas R↗
Factors affecting transition at supersonic speeds
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Czarnecki, K R↗
Preliminary Investigation of the Effect of Fences and Balancing Tabs on the Hinge-moment Characteristics of a Tip Control on a 60 Degree Delta Wing at Mach Number 1.61
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Czarnecki, K R↗
Load distributions associated with controls at supersonic speeds
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Czarnecki, K R↗
An Extension of the Investigation of the Effects of Heat Transfer on Boundary-layer Transition on a Parabolic Body of Revolution (NACA RM-10) at a Mach Number of 1.61
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Czarnecki, K R↗
Hinge-moment Characteristics for Several Tip Controls on a 60 Degree Sweptback Delta Wing at Mach Number 1.61
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Czarnecki, K R↗
Preliminary investigation of the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA RM-10) at a Mach number of 1.61
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Czarnecki, K R↗
Skin-friction Drag and Boundary-layer Transition on a Parabolic Body of Revolution (NACA Rm-10)at a Mach Number of 1.6 in the Langley 4-by-4-foot Supersonic Pressure Tunnel
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Czarnecki, K R↗
Investigation at Supersonic Speeds of Some of the Factors Affecting the Flow over a Rectangular Wing with Symmetrical Circular-arc Section and 30-percent-chord Trailing-edge Flap
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Czarnecki, K R↗
Investigation at Mach Number 1.62 of the Pressure Distribution over a Rectangular Wing with Symmetrical Circular-arc Section and 30-percent-chord Trailing-edge Flap
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Czarnecki, K R↗
Dynamometer-stand investigation of a group of mufflers
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ENGINES - PRESSURE, BACK↗
Investigation of Interaction Effects Arising from Side-wall Boundary Layers in Supersonic Wind-tunnel Tests of Airfoils
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Czarnecki, K R↗