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- 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
- Performance of as-forged, heat-treated, and overaged S-816 blades in a turbojet engine
- NACA research on slurry fuels through 1954
- Experimental study of shock-positioning method of ram-jet-engine control
- Study of some effects of structural flexibility on the longitudinal motions and loads as obtained from flight measurements of a swept-wing bomber
- Preliminary experimental investigation of a variable-area, variable-internal-contraction air inlet at Mach numbers between 1.42 and 2.44
- Preliminary discussion of fuel temperatures attained in supersonic aircraft
- Preliminary results from free-jet tests of a 48-inch-diameter ram-jet combustor with an annular can-type flame holder
- Flight-determined pressure distributions over a section of the 35 degree swept wing of the Douglas D-558-II research airplane at Mach numbers up to 2.0
- Preliminary results from free jet tests of a 48-inch-diameter ram-jet combustor with an annular-piloted baffle-type flameholder
- Preliminary investigation at Mach number 1.9 of simulated wing-root inlets
- A pressure-distribution investigation of the aerodynamic characteristics of a body of revolution in the vicinity of a reflection plane at Mach numbers of 1.41 and 2.01
- Preparation and physical properties of some trialkylboranes