Browse TRAIL Inventories

Tank investigation of the hydrodynamic characteristics of a 1/13.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat: TED No. NACA DE 385

Minimum-drag ducted and pointed bodies of revolution based on linearized supersonic theory

Development of craze and impact resistance in glazing plastics by multiaxial stretching

Comparison of the Drag of a Fin-Stabilized Body of Revolution and of a Complete Airplane Configuration as Obtained at Transonic Speeds in a Slotted Wind Tunnel and in Free Flight

An experimental investigation of the hinge-moment characteristics of a constant-chord control surface oscillating at high frequency

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

On boattail bodies of revolution having minimum wave drag

Generalized indical forces on deforming rectangular wings in supersonic flight

Analog study of interacting and noninteracting multiple-loop control systems for turbojet engines

Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/10-Scale Model of the Grumman F9F-9 Airplane, TED No. NACA AD 3109

Temperature in a J47-25 Turbojet-Engine Combustor and Turbine Sections During Steady-State and Transient Operation in a Sea-Level Test Stand

Investigation of the compressive strength and creep lifetime of 2024-T3 aluminum-alloy plates at elevated temperatures

Charts for estimating tail-rotor contribution to helicopter directional stability and control in low-speed flight

Error in airspeed measurement due to the static-pressure field ahead of an airplane at transonic speeds

Theoretical analysis of incompressible flow through a radial-inlet centrifugal impeller at various weight flows

Flight Test of the Lateral Stability of a 0.133-Scale Model of the Convair XFY-1 Airplane with Windmilling Propellers at Mach Numbers from 0.70 to 1.12 (TED No. NACA DE 369)

A method for simulating the atmospheric entry of long-range ballistic missiles

An analysis of once-per-revolution oscillating aerodynamic thrust loads on single-rotation propellers on tractor airplanes at zero yaw

Flight experience with two high-speed airplanes having violent lateral-longitudinal coupling in aileron rolls

A flight and analog computer study of some stabilization and command networks for an automatically controlled interceptor during the final attack phase

Flight determination of minimum drag of 0.11-scale rocket-boosted model of the Chance Vought XF8U-1 airplane with modified fuselage area distribution and faired inlet at Mach number from 0.82 to 1.68 : TED No. NACA DE 392

Exploratory investigation at Mach number 4.06 of an airplane configuration having a wing of trapezoidal form : effects of various tail arrangements on wing-on and wing-off static longitudinal and lateral stability characteristics

Exploratory investigation of the flow in the separated region ahead of two blunt bodies at Mach number 2

Flight measurements of the dynamical longitudinal stability and frequency-response characteristics of the XF-92A delta-wing airplane

Flight measurements of wing loads on the Convair XF-92A delta-wing airplane

Flight experience with a delta-wing airplane having violent lateral-longitudinal coupling in aileron rolls

Flight measurements of the velocity distribution and persistence of the trailing vortices of an airplane

Free-jet performance configurations of the XRJ43-MA-3 ram-jet engine

Investigation of impulse-type supersonic compressor with hub-tip ratio of 0.6 and turning to axial direction II : stage performance with three different sets of stators

Internal performance of a series of circular auxiliary-air inlets immersed in a turbulent boundary layer : Mach number range: 1.5 to 2.0

Investigation of aerodynamic characteristics in pitch and sideslip of a 45 degree sweptback-wing airplane model with various vertical locations of wing and horizontal tail : basic-data presentation, M = 2.01

Interferometric observation of flow about an isentropic (reverse Prandtl-Meyer streamline) compression wedge at Mach 3.0

Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages V : preliminary analysis of over-all performance of modified compressor

Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages VI : over-all performance, rotating stall, and blade vibration at low and intermediate compressor speeds

Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages IV : modification of aerodynamic design and prediction of performance

Interaction of a jet and flat plate located in an airstream

Inlet-air distortion effects on stall, surge, and acceleration margin of a turbojet engine equipped with variable compressor inlet guide vanes

Investigation of the aerodynamic characteristics in pitch and sideslip of a 45 degree sweptback-wing airplane model with various vertical locations of the wing and horizontal tail : effect of wing location and geometric dihedral for the wing-body com

An investigation of the adaptation of a transonic slotted tunnel to supersonic operation by enclosing the slots with fairings

Investigation of rotating components of counterrotating two-spool engines I : analytical investigation of off-design performance of turbine component designed with and without outer-turbine stator

A method for the analysis of compounds containing boron, carbon, and hydrogen

Load distributions on wings and wing-body combinations at high angles of attack and supersonic speeds

Controls for supersonic missiles

Preliminary free-jet performance of XRJ43-MA-3 ram-jet engine at Mach number of 2.50

Preliminary investigation of a conical spike inlet in combination with a vertical-wedge auxiliary inlet at Mach number 1.9

Preliminary investigation of effect on performance of dividing conical-spike nose inlets into halves at Mach numbers 1.5 to 2.0

Results of initial wind-tunnel flutter experiments at low speed with a towed airplane model having a 40 degree sweptback wing of aspect ratio 3.62 equipped with pylon-mounted stores

Effect of ejector performance of varying diameter ratio by simulated iris flaps

Pressure distributions on triangular and rectangular wings to high angles of attack Mach numbers 2.46 and 3.36

The origin and distribution of supersonic store interference from measurement of individual forces on several wing-fuselage-store configurations III : swept-wing fighter-bomber configuration with large and small stores. Mach number 1.61


Published Year

Subject

Author

‹‹ previous 1 2 ... 215 216 217 218 219 220 221 ... 280 281 next ››