Search
Search U.S. government technical reports digitized or harvested by TRAIL.
Keyword Search
19 results returnedSearch results
- Tests of Wing Machine-Gun and Cannon Installations in the NACA Full-Scale Wind Tunnel, Special Report
- Pressure-Drop Characteristics of Orifice Plates Used to Simulate Radiators
- Wind-Tunnel Investigation of Rear Underslung Fuselage Ducts
- Langley full-scale-tunnel investigation of the fuselage boundary layer on a typical fighter airplane with a single liquid-cooled engine
- Dynamometer-stand investigation of the muffler used in the demonstration of light-airplane noise reduction
- Investigation of interaction effects arising from side-wall boundary layers in supersonic wind-tunnel tests of airfoils
- An approximate method of calculating pressures in the tip region of a rectangular wing of circular-arc section at supersonic speeds
- 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
- 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
- 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
- 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
- Factors affecting transition at supersonic speeds
- Hinge-moment characteristics for several tip controls on a 60 degree sweptback delta wing at Mach number 1.61
- 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
- Investigation of distributed surface roughness on a body of revolution at a Mach number of 1.61
- Loads associated with spoilers at supersonic speeds
- An 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
- Simplified procedures for estimating flap-control loads at supersonic speeds
- Analysis of pressure distributions for a series of tip and trailing-edge controls on a 60 deg wing at Mach numbers of 1.61 and 2.01