National Advisory Committee for Aeronautics (NACA) - 13,806 Matching Results

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Altitude performance of a 20-inch-diameter ram-jet engine investigated in a free-jet facility at Mach number 3.0
No Description Available.
Comparison and evaluation of two model techniques used in predicting bomb-release motions
No Description Available.
Pressure Distributions and Aerodynamic Characteristics of Several Spoiler-type Controls on a Trapezoidal Wing at Mach Numbers of 1.61 and 2.01
Pressure distributions and aerodynamic characteristics of spoiler-type controls on trapezoidal wing at supersonic speed.
Aerodynamic characteristics of a 0.04956-scale model of the Convair F-102A airplane at Mach numbers of 1.41, 1.61, and 2.01
Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 of various arrangements of a 0.04956-scale model of the Convair F-102A airplane with faired inlets. Tests made of the model equipped with a plain wing, a wing with 6.4 percent conical camber, and a wing with 15 percent conical camber. Body modifications including an extended nose, a modified canopy, and extended afterbody fillets were evaluated. In addition, the effects of a revised vertical tail and two different ventral fins were determined. The results indicated that the use of cambered wings resulted in lower drag in the lift-coefficient range above 0.2. This range, however, is above that which would generally be required for level flight; hence, the usefulness of camber might be confined to increased maneuverability at the higher lifts while its use may be detrimental to the high-speed (low-lift) capabilities.
Transonic flight evaluation of the effects of fuselage extension and indentation on the drag of a 60 deg delta wing interceptor airplane
No Description Available.
Analysis of flight-determined and predicted effects of flexibility on the steady-state wing loads of the B-52 airplane
Flight-determined and predicted effects of flexibility on steady-state wing loads of B-52 airplane.
Induction system characteristics and engine surge occurrence for two fighter-type airplanes
No Description Available.
In-flight Gains Realized by Modifying a Twin Side-inlet Induction System
Modification of twin side-inlet induction system and in-flight gains.
Power-off tests of the Northrop N9M-2 tailless airplane in the 40- by 80-foot wind tunnel
No Description Available.
Heat Transfer Measured in Free Flight on a Slightly Blunted 25 deg Cone-Cylinder-Flare Configuration at Mach Numbers up to 9.89
Skin temperature and surface pressure of blunted cone-cylinder-flare configuration free flight test vehicle to hypersonic speeds.
Model ditching investigations of three airplanes equipped with hydro-skis
No Description Available.
A note on the ability to predict transonic drag-rise changes due to model modifications
Wind tunnel test to establish validity of Fourier analysis results for transonic drag rise changes due to model modifications.
The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselage-store Configurations. Ii - Swept-wing Heavy-bomber Configuration With Large Store Nacelle . Lateral Forces and Pitching Moments, Mach Number, 1.61
Effect of large store /nacelle/ on a swept-wing heavy bomber - lateral force and pitching moments.
The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. 1.-swept-wing Heavy-bomber Configuration With Large Store Nacelle . Lift and Drag, Mach Number, 1.61
Supersonic store interference - 1, swept-wing heavy bomber with large stores - lift & drag at mach 1.61.
The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselagestore Configurations. Iii - Swept-wing Fighter-bomber Configuration With Large and Small Stores. Mach Number, 1.61
Origin of supersonic store interference from measurements of individual forces - swept-wing fighter-bomber with large & small stores.
Aerodynamics of Oscillating Control Surfaces at Transonic Speeds
Aerodynamic forces and moments of oscillating control surfaces at transonic speeds.
Aerodynamic loads on an external store adjacent to a 60 deg delta wing at mach numbers from 0.75 to 1.96
Aerodynamic loads on external store adjacent to 60 deg delta wing at Mach numbers 0.75 to 1.96.
Aerodynamic Loads on an External Store Adjacent to an Unswept Wing at Mach Numbers Between 0.75 and 1.96
Aerodynamic loads on high-speed aircraft external store adjacent to an unswept wing at mach 0.75 to 1.96.
Aeronautical Lab. Examination of Recent Lateral-stability-derivative Data
Stability derivatives affecting lateral behavior of aircraft and missiles.
Analytical studies of the response to longitudinal control of three airplane configurations in landing approaches
Analytical studies of response to longitudinal control of three aircraft configurations in carrier landing approaches.
Buffet Tests of an Attack-airplane Model With Emphasis on Analysis of Data From Wind-tunnel Tests
Buffeting tests of attack aircraft model at transonic speeds.
Calculation of External-store Loads and Correlation With Experiment
Calculation of external-store loads and correlation with experiment.
Canard Hinge Moments and Longitudinal Stability of a 1/7-Scale Model of the Convair B-58 External Store in a Free-Flight Investigation at Mach Numbers from 0.94 to 2.58
No Description Available.
Comparison of free-flight measurements of the zero-lift drag rise of six airplane configurations and their equivalent bodies of revolution at transonic speeds
No Description Available.
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
Supersonic pressure distributions for tip and trailing edge controls on 60 deg delta wing.
Comparison of wind-tunnel, rocket, and flight drag measurements for eight airplane configurations at Mach numbers between 0.7 and 1.6
No Description Available.
The Design and Cascade Tests of Free-streamline and Full-contour 160 Deg Turning Supersonic-turbine-blade Sections
Supersonic flow of two turbine blade sections with turning angle of 160-degrees.
Drag and static stability at low lift of rocket-powered models of the convair mx-1626 airplane at mach numbers from 0.7 to 1.5
No Description Available.
Drag at model trim lift of a 1/15-scale Convair B-58 supersonic bomber
No Description Available.
Drag measurements at low lift of a four- nacelle airplane configuration having a longitudinal distribution of cross-sectional area conductive to low transonic drag rise
Drag measurements at low lift of four-nacelle aircraft configuration with longitudinal distribution of cross-sectional area conducive to low transonic drag rise.
Dynamic Lateral Behavior of High-performance Aircraft
Dynamic lateral stability and control of high performance hypersonic aircraft.
Dynamic stability investigation of two right circular cylinders in axial free flight at Mach numbers from 0.4 to 1.7 fineness-ratio- 2.56 cylinder and fineness-ratio-4.0 cylinder with flared afterbody
Dynamic longitudinal stability of right circular cylinders in axial free flight.
Measurement of static forces on internally carried bombs of three fineness ratios in flow field of a swept-wing fighter-bomber configuration at a Mach number of 1.61 with illustrative drop path calculations
No Description Available.
A Feasibility Study of the Flare-Cylinder Configuration as a Reentry Body Shape for an Intermediate Range Ballistic Missile
A study has been made of a flare-cylinder configuration to investigate its feasibility as a reentry body of an intermediate range ballistic missile. Factors considered were heating, weight, stability, and impact velocity. A series of trajectories covering the possible range of weight-drag ratios were computed for simple truncated nose shapes of varying pointedness, and hence varying weight-drag ratios. Four trajectories were chosen for detailed temperature computation from among those trajectories estimated to be possible. Temperature calculations were made for both "conventional" (for example, copper, Inconel, and stainless steel) and "unconventional" (for example, beryllium and graphite) materials. Results of the computations showed that an impact Mach number of 0.5 was readily obtainable for a body constructed from conventional materials. A substantial increase in subsonic impact velocity above a Mach number of 0.5 was possible without exceeding material temperature limits. A weight saving of up to 134 pounds out of 822 was possible with unconventional materials. This saving represents 78 percent of the structural weight. Supersonic impact would require construction of the body from unconventional materials but appeared to be well within the range of attainability.
Free Spinning and Recovery Characteristics of 1/36-Scale Model of the Republic F-105B Airplane
No Description Available.
Experimental and Theoretical Determination of Forces and Moments on a Store and on a Store- Pylon Combination Mounted on a 45 Deg Swept- Wing-Fuselage Configuration at a Mach Number of 1.61
Forces and moments of store-pylon combination mounting on swept wing-fuselage configuration in supersonic pressure tunnel.
Wind-Tunnel Flutter Tests at Mach Numbers up to 3.0 of Boeing Wing Models for Weapons System 110A
No Description Available.
Boundary-Layer-Transition and Heat-Transfer Measurements from Flight Tests of Blunt and Sharp 50 Degree Cones at Mach Numbers from 1.7 to 4.7
Boundary-layer-transition and heat-transfer measurements were obtained from flight tests of blunt and sharp cones having apex angles of 50 deg. The test Mach number range was from 1.7 to 4.7, corresponding to free-stream Reynolds numbers, based on cone base diameter, of 18. 3 x 10(exp 6) and 32.1 x 10(exp 6), respectively. Transition on both models occurred at a local Reynolds number of 1 x 10(exp 6) to 2 X 10(exp 6) based on distance from the stagnation point. Transition Reynolds numbers based on momentum thickness were between 320 and 380 for the blunt cone. The model surface roughness was 25 rms microinches or greater. Turbulent heat transfer to the conical surface of the blunt cone at a Mach number of 4 was 30 percent less than that to the surface of the sharp cone. Available theories predicted heat-transfer coefficients reasonably well for the fully laminar or turbulent flow conditions.
Transonic aerodynamic and trim characteristics of 1/15-scale models of the convair mx-1964 airplane with indented fuselage
No Description Available.
Transonic aerodynamic and trim characteristics of a multi-engine delta-wing airplane model
Wind tunnel testing of two and four engine models of delta wing aircraft for transonic drag rise increment and maximum lift-drag ratio comparison.
Transonic Aerodynamic Characteristics of a 1/15-Scale Model of the Convair B-58 Airplane
No Description Available.
Transonic flutter characteristics of a cambered A-plan-form wing with and without simulated nacelles
No Description Available.
Transonic Flutter Investigation of an All-movable Horizontal Tail for a Fighter Airplane
Transonic flutter of all-movable horizontal tail - bending & pitching moments.
Transonic flutter investigation of models of the all-movable horizontal tail of a fighter airplane
Horizontal tail flutter in fighter aircraft at transonic speeds.
Transonic flutter investigation of models of the sweptback wing of a fighter airplane
Transonic flutter characteristics of sweptback fighter airplane wing models.
Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail
Results are presented of a free-flight investigation between Mach numbers of 0.7 to 1.3 and Reynolds numbers of 3.1 x 10(exp 6) to 7.0 x 10(exp 6) to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. This missile has a weng, body, and vertical tail, but has no horizontal tail. The basic wing plan form has an aspect ratio of 5.5, 45 deg of sweepback of the 0.406 streamwise chord line, and a taper ratio of 0.4. A 1/10-scale steel-wing model of the missile was flown with modifications to the basic wing plan form consisting of leading-edge chord-extensions deflected 7 deg downward together with the forward 15 percent of the wing chord, and inboard trailing-edge flaps deflected 5 deg downward. In addition, the model had a static-pressure tube mounted at the tip of the vertical tail for position-error measurements and had a speed brake also mounted on the vertical tail to trim the model to positive lift coefficients and to permit determination of the trim and drag effectiveness of the brake. The data are uncorrected for the effects of wing elasticity, but experimental wing influence coefficients are presented.
Transonic wind-tunnel investigation of static- pressure fluctuations in duct of a scale inlet model of a supersonic fighter-bomber airplane
No Description Available.
Experimental investigation of the transonic and supersonic flutter characteristics of the upper and lower vertical tails of an air-to-ground missile
Wind tunnel investigation of transonic and supersonic flutter of air to surface missile vertical tail surfaces.
Experimental static aerodynamic forces and moments at high subsonic speeds on a canard missile during simulated launching from the midsemispan location of a 45 deg sweptback wing-fuselage-pylon combination at zero sideslip
No Description Available.
First landing of Bell X-2 research airplane
No Description Available.