Search
Search U.S. government technical reports digitized or harvested by TRAIL.
Keyword Search
14045 results returnedSearch results
- Preliminary flight investigation of the wing-dropping tendency and lateral-control characteristics of a 35 degree swept-wing airplane at transonic Mach numbers
- Measurements of the effect of trailing-edge thickness on the zero-lift drag of thin low-aspect-ratio wings
- Effects of sweep on the damping-in-roll characteristics of three sweptback wings having an aspect ratio of 4 at transonic speeds
- An NACA transonic test section with tapered slots tested at Mach numbers to 1.26
- Performance of high-pressure-ratio axial-flow compressor using highly cambered NACA 65-series blower blades at high Mach numbers
- NACA research on combustors for aircraft gas turbines I : effects of operating variables on steady-state performance
- Large-scale flight measurements of zero-lift drag at Mach numbers form 0.86 to 1.5 of a wing-body combination having a 60 degree triangular wing with NACA 65A003 sections
- Preliminary correlation of efficiency of aircraft gas-turbine combustors for different operating conditions
- Preliminary analysis of effects of air cooling turbine blades on turbojet-engine performance
- Preliminary investigation of constant-geometry, variable Mach number, supersonic tunnel with porous walls
- Preliminary flight investigation of the dynamic longitudinal-stability characteristics of a 35 degree swept-wing airplane
- Preliminary analysis of three cycles for nuclear propulsion of aircraft
- Lift and moment characteristics at subsonic Mach numbers of four 10-percent-thick airfoil sections of varying trailing-edge thickness
- Lateral-control investigation of flap-type and spoiler-type controls on a wing with quarter-chord-line sweepback of 60 degrees, aspect ratio 2, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method
- Lateral-control investigation of flap-type controls on a wing with upswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method
- Lateral-control investigation of flap-type controls on a wing with quarter-chord line swept back 60 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic bump method
- Longitudinal-stability characteristics of the Northrop X-4 airplane (USAF No. 46-677)
- Low-speed investigation of leading-edge and trailing-edge flaps on a 47.5 degree sweptback wing of aspect ratio 3.4 at a Reynolds number of 4.4 x 10(exp 6)
- Measurement of uniform flame movement in carbon monoxide - air mixtures containing either added D2O or H2O
- Measurements of the drag and pressure distribution on a body of revolution throughout transition from subsonic to supersonic speeds
- Temperature survey of the wake of two closely located parallel jets
- Free-spinning tunnel tests of a 1/20-scale model of the McDonnell XF3H-1 airplane : TED No. NACA DE 343
- Free-jet investigation of a 16-inch ram jet at Mach numbers of 1.35, 1.50, and 1.73
- Free-jet performance of 16-inch ram-jet engine with several fuels
- Heat-transfer and operating characteristics of aluminum forced-convection and stainless-steel natural-convection water-cooled single-stage turbines
- Note on some observed effects of rocket motor operation on the base pressures of bodies in free light
- Free-flight performance of 16-inch-diameter supersonic ram-jet units 2: five units designed for combustion-chamber-inlet Mach number of 0.16 at free-stream Mach number of 1.60 (units B-1, B-2, B-3, B-4, and B-5)
- Flight measurements with the Douglas D-558-II (BuAero No. 37974) research airplane : determination of the aerodynamic center and zero-lift pitching-moment coefficient of the wing-fuselage combination by means of tail-load measurements in the Mach num
- Effect of fuel volatility on altitude starting limits of a turbojet engine
- Correlation of forced-convection heat-transfer data for air flowing in smooth platinum tube with long-approach entrance at high surface and inlet-air temperatures
- Correlation of laboratory smoke test with carbon deposition in turbojet combustors
- Aerodynamic characteristics of NACA RM 10 missile in 8 by 6 foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98. 3: analysis of force distribution at angle of attack (stabilizing fins removed)
- Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 1: presentation and analysis of pressure measurements (stabilizing fins removed)
- Interpretation of boundary-layer pressure-rake data in flow with a detached shock
- Analytical investigation of turbines with adjustable stator blades and effect of these turbines on jet-engine performance
- Analytical determination of local surface heat-transfer coefficients for cooled turbine blades from measured metal temperatures
- Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 2, taper ratio 0.78, and NACA 65A004 airfoil section : transonic-bump method
- Combustion efficiencies in hydrocarbon-air systems at reduced pressures
- Analytical Investigation of Propeller Efficiency at High Subsonic Flight Speeds near Mach Number Unity
- Wind-tunnel investigation at Mach numbers from 0.50 to 1.29 of an unswept tapered wing of aspect ratio 2.67 with leading- and trailing-edge flaps - trailing-edge flaps deflected
- Analytical investigation of flow and heat transfer in coolant passages of free-convection liquid-cooled turbines
- Antiknock evaluation of hydrocarbons and ethers as aviation fuel components
- Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 2, taper ratio 0.6, and NACA 65A006 airfoil section : transonic bump method
- Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A004 airfoil section : transonic-bump method
- Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 2: presentation and analysis of force measurements
- Aerodynamic characteristics with fixed and free transition of a modified delta wing in combination with fuselage at high subsonic speeds
- Comparison of large scale flight measurements of zero lift drag at Mach numbers from 0.9 to 1.7 of two wing-body combinations having similar 60 degree triangular wings with NACA 65A003 sections
- An investigation of three transonic fuselage air inlets at Mach numbers from 0.4 to 0.94 and at a Mach number of 1.19
- Characteristics of perforated diffusers at free-stream Mach number 1.90
- The effect of tip tanks on the rolling characteristics at high subsonic Mach numbers of a wing having an aspect ratio of 3 with quarter-chord line swept back 35 degrees