48 research outputs found
A Note on the Effect of Heat Transfer on Peak Pressure Rise Associated with Separation of Turbulent Boundary Layer on a Body of Revolution (NACA RM-10) at a Mach Number of 1.61
Get PDFAn 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
Get PDFPreliminary 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
Get PDFAn 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
Get PDFPreliminary 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
Get PDFInvestigation of Boundary-layer Transition on 10 Degree Cone in Langley 4- by 4-foot Supersonic Pressure Tunnel at Mach Numbers of 1.41, 1.61, and 2.01
Get PDFA method for the determination of the time lag in pressure measuring systems incorporating capillaries
Get PDFWind-tunnel calibration of a combined pitot-static tube and vane-type flow-angularity indicator at Mach numbers of 1.61 and 2.01
Get PDFA limited calibration of a combined pitot-static tube and vane-type flow-angularity indicator has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01. The results indicated that the angle-of-yaw indications were affected by unsymmetric shock effects at low angles of attack
A pressure-distribution investigation of a supersonic-aircraft fuselage and calibration of the Mach number 1.40 nozzle of the Langley 4- by 4-foot supersonic tunnel
Get PDFPreliminary Investigation of the Drag Characteristics of the NACA RM-10 Missile at Mach Numbers of 1.40 and 1.59 in the Langley 4- by 4-foot Tunnel
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