National Advisory Committee for Aeronautics (NACA) - 5,157 Matching Results

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Aerodynamic Performance and Static Stability and Control of Flat-Top Hypersonic Gliders at Mach Numbers From 0.6 to 18

Description: Memorandum presenting a study of aerodynamic performance and static stability and control at hypersonic speeds. In the first part of the study, the effect of interference lift is investigated by tests of asymmetric models with conical fuselages and arrow plan-form wings. In the second part, the aerodynamic performance and static stability and control characteristics of a hypersonic glider are investigated in somewhat greater detail.
Date: September 17, 1958
Creator: Syvertson, Clarence A.; Gloria, Hermilo R. & Sarabia, Michael F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Wingless Missile Configurations with Folding Controls and Low-Aspect-Ratio Stabilizing Surfaces

Description: Results regarding a wind-tunnel investigation of wingless missile configurations with cylindrical bodies and conical or hemispherical noses, extensible control surfaces aft of the nose, and tails consisting of eight low-aspect-ratio triangular or rectangular fins. Normal-force, axial-force, and pitching-moment coefficients were obtained for several control deflections for Mach numbers 1.2 and 1.9.
Date: September 17, 1958
Creator: Lazzeroni, Frank A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measurements of the Buffeting Loads on the Wing and Horizontal Tail of a 1/4-Scale Model of the X-1E Airplane

Description: "The buffeting loads acting on the wing and horizontal tail of a 1/4-scale model of the X-1E airplane have been measured in the Langley 16-foot transonic tunnel in the Mach number range from 0.40 to 0.90. When the buffeting loads were reduced to a nondimensional aerodynamic coefficient of buffeting intensity, it was found that the maximum buffeting intensity of the horizontal tail was about twice as large as that of the wing. Comparison of power spectra of buffeting loads acting on the horizont… more
Date: September 17, 1958
Creator: Rainey, A. Gerald & Igoe, William B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Stability Investigation of a Blunt Cone and a Blunt Cylinder With a Square Base at Mach Numbers From 0.64 to 2.14

Description: Memorandum presenting a discussion of a fineness-ratio-2.6 bluff shape with an x(exp 1/10) nose and a 5 degree flare extending the entire body length and a fineness-ratio-2.5 bluff shape with an x(exp 1/10) nose and a square base with sides equal to the diameter of the cylindrical forebody tested in free flight over a range of Mach and Reynolds numbers. Time histories, cross plots of force and moment coefficients, and plots of the longitudinal-force coefficient, rolling velocity, aerodynamic ce… more
Date: September 17, 1958
Creator: Coltrane, Lucille C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Design and Experimental Investigation of a Single-Stage Turbine With a Rotor Entering Relative Mach Number of 2

Description: Memorandum presenting a design and experimental investigation of a single-stage supersonic turbine. The turbine was designed for a rotor entering relative Mach number of 2. Results regarding the overall turbine performance, outer-wall static-pressure variation, momentum-loss considerations, effect of rotor modifications, and supersonic starting are provided.
Date: September 15, 1958
Creator: Moffitt, Thomas P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of an Isentropic, All-Internal-Contraction, Axisymmetric Inlet Designed for Mach 2.50

Description: Memorandum presenting an experimental investigation of an internal-contraction, axially symmetric inlet with isentropic compression surfaces on both the cowl and centerbody conducted over a range of Mach numbers from 2.0 to 2.7 at angles of attack from 0 to 6 degrees. The study was made to determine the optimum bleed system, together with a method of controlling the inlet.
Date: September 15, 1958
Creator: Bowditch, David N. & Anderson, Bernhard H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The static and dynamic-rotary stability derivatives at subsonic speeds of a model of the X-15 research airplane

Description: Report presenting measurements in a wind tunnel of the subsonic static and dynamic-rotary stability derivatives of a model of an airplane designed to fly at high supersonic speeds and high altitudes. The effects of flaps and landing gear, speed brakes, and several model components are included in the results as well as the stability characteristics of the model.
Date: September 15, 1958
Creator: Lopez, Armando E. & Tinling, Bruce E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of the low-speed aerodynamic characteristics of a hypersonic glider configuration

Description: Report presenting a wind-tunnel investigation of the low-speed aerodynamic characteristics of an airplane configuration designed to obtain high lift-drag ratios at hypersonic speeds. The power-off landing of this aircraft would be difficult due to the high sinking speeds inherent in the design. Results regarding the longitudinal characteristics, lateral characteristics, and landing considerations are provided.
Date: September 15, 1958
Creator: Kelly, Mark W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic Characteristics at Mach Numbers From 2.5 to 3.5 of a Canard Bomber Configuration Designed for Supersonic Cruise Flight

Description: Report presenting an investigation of a canard-type configuration designed for supersonic cruise flight in the Unitary Plan wind tunnel. Tests were conducted over a range of angles of attack and angles of sideslip. Results regarding the effect of forebody configuration, effects of Reynolds number and transition, effect of canard and elevon deflection, and effect of vertical surfaces are provided.
Date: September 10, 1958
Creator: Carmel, Melvin M.; Kelly, Thomas C. & Gregory, Donald T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Flight Study of the Effects of Noise Filtering in the Attack Display on the Pilot's Tracking Performance

Description: Memorandum presenting flight tests conducted with a director-type radar fire-control system, with scope presentation of the steering information, to determine the effects of attack-display smoothing on the pilot's tracking and steering effectiveness in tail-chase and lead-collision beam attacks. Results regarding tail-chase attacks and lead-collision beam attacks are provided.
Date: September 10, 1958
Creator: Turner, Howard L. & Heinle, Donovan R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated Glide-Rocket Shape at Mach Numbers up to 10

Description: "Heat-transfer measurements were made on a simulated glide-rocket shape in free flight at Mach numbers up to 10 and free-stream Reynolds numbers of 2 x 10 based on distance along surface from apex and 3 x 10 based on nominal leading-edge diameter. The model simulated the bottom of a 75 deg delta wing at 80 deg angle of attack. The data indicated that for the test conditions a modified three-dimensional stagnation-point theory will predict to reasonable engineering accuracy the heating on a high… more
Date: September 10, 1958
Creator: Swanson, Andrew G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation at Mach Numbers From 0.6 to 1.4 of Several Ejected Pilot-Seat Models

Description: "The results are presented of an experimental investigation conducted to determine the static longitudinal and lateral-direction aerodynamic characteristics of basic and modified versions of a conventional upward ejected pilot-seat combination, a sled-type upward ejected pilot-seat combination, and a downward ejected pilot-seat combination" (p. 1). The drag coefficient, lift coefficient, rolling-moment coefficient, pitching-moment coefficient, yawing-moment coefficient, and side-force coefficie… more
Date: September 10, 1958
Creator: Summers, James L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane

Description: Memorandum presenting an investigation conducted in the full-scale tunnel to determine the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane over a range of test velocities from minimum stall speed up to speeds giving load factors for wing buckling. The airplane was developed as a potential way to rescue downed pilots in enemy territory. An exploration of the stability, stalling characteristics, buckling, and chosen configuration is provided.
Date: September 10, 1958
Creator: Cocke, Bennie W., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Hovering and Transition Flight Tests of a 1/5-Scale Model of the Ryan X-13 VTOL Airplane

Description: Report discussing an investigation of the dynamic stability and control characteristics of a model of the Ryan X-13 jet VTOL airplane in hovering and transition flight. Flight control was smooth and easy without the gyroscopic effects of the engine represented, but adding a simulation of the gyroscopic effects caused the plane to become uncontrollable in hovering flight without artificial stabilization. The transition was found to be easy to perform with and without gyroscopic effects, but the … more
Date: September 9, 1958
Creator: Smith, Charles C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of Calculated and Experimental Temperatures and Coolant Pressure Losses for a Cascade of Small Air-Cooled Turbine Rotor Blades

Description: From Summary: "Average spanwise blade temperatures and cooling-air pressure losses through a small (1.4-in, span, 0.7-in, chord) air-cooled turbine blade were calculated and are compared with experimental nonrotating cascade data. Two methods of calculating the blade spanwise metal temperature distributions are presented. The method which considered the effect of the length-to-diameter ratio of the coolant passage on the blade-to-coolant heat-transfer coefficient and assumed constant coolant pr… more
Date: September 4, 1958
Creator: Stepka, Francis S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of Injectors With a 200-Pound-Thrust Ammonia-Oxygen Engine

Description: "Characteristic exhaust velocity was measured for a small range of mixture ratios with four different injectors. Performances of parallel-sheet, like-on-like, and triplet injectors were about the same, but a parallel-jet injector had a much lower performance. Performance values for ammonia-oxygen were slightly lower than for heptane-oxygen" (p. 1).
Date: September 4, 1958
Creator: Priem, Richard J. & Clark, Bruce J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Design and Experimental Performance of a 0.35 Hub-Tip Radius Ratio Transonic Axial-Flow-Compressor Rotor Designed for 40 Pounds Per Second Per Unit Frontal Area

Description: Memorandum presenting an investigation to determine the feasibility of a high-performance transonic axial-flow compressor stage with a weight flow of 40 pounds per second per square foot of frontal area. A transonic axial-flow inlet stage with a hub-tip ratio of 0.35 and an axial Mach number of approximately 0.75 was designed and fabricated. Results regarding overall rotor performance, flow parameters, radial matching of blade-element sections, and comparison of blade-element parameters with de… more
Date: September 4, 1958
Creator: Montgomery, John C. & Yasaki, Paul T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Thermal reaction of diborane with trimethylborane

Description: Report presenting testing of diborane and trimethylbornae in a tube at 235 to 300 degrees Celsius in the presence of hydrogen. Methylpentaboranes were produced and separated in a specially designed vacuum fractionation column. Results indicated that two isomers of monomethylpentaborane were isolated and that one had not been previously reported on.
Date: September 4, 1958
Creator: Lamneck, John H., Jr. & Kaye, Samuel
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of the effect of yaw on rates of heat transfer to transverse circular cylinders in a 6500-foot-per-second hypersonic air stream

Description: Report describing equipment that can be used to shock-compress air by helium to 3660 degrees Rankine to generate a 6500-foot-per-second air stream with a flow duration of 40 milliseconds. The influence of yaw on rates of heat transfer to the same circular cylinders was investigated at angles of yaw up to 70 degrees.
Date: August 26, 1958
Creator: Cunningham, Bernard E. & Kraus, Samuel
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of a Full-Scale Aircraft Ejector with Various Spacing Ratios and Correlation with Small-Scale Tests

Description: Memorandum presenting a flight investigation to determine the thrust and pumping characteristics of a family of aircraft exhaust ejectors. Information was obtained on the variation of these characteristics with changes in engine power, flight Mach number, and ejector spacing ratio, and these results were compared to small-scale tests. Results were also obtained showing how a swinging survey probe can be used as a device for calibrating a tail-pipe pressure probe for the measurement of thrust an… more
Date: August 26, 1958
Creator: Havill, C. Dewey & Wingrove, Rodney C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Forces and pitching moments on an aspect-ratio-3.1 wing-body combination at Mach numbers from 2.5 to 3.5 and sublimation studies of the effect of single-elements roughness on the boundary-layer flow

Description: Report presenting lift, drag, and pitching-moment characteristics for a wing-body combination for a range of Mach numbers. The wing had an aspect ratio of 3.1, a sweepback of the leading edge of 19.1 degrees, a taper ratio of 0.39, and a biconvex profile with a thickness of 3 percent of the chord. Results regarding aerodynamic characteristics and visual-flow studies are provided.
Date: August 26, 1958
Creator: Hopkins, Edward J.; Keating, Stephen J., Jr. & Muhl, Richard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a Tilting-Wing Vertical-Take-Off-and-Landing Jet Airplane Model in Hovering and Transition Flight

Description: Report presenting the results of an investigation of the dynamic stability and controllability of a proposed supersonic-cruise, vertical-take-off-and-landing airplane configuration with a tilting wing and engines. The configuration tested was found to have satisfactory take-off, landing, and hovering characteristics. Information about transition flight, including stability and control characteristics, is provided.
Date: August 26, 1958
Creator: Kirby, Robert H. & Hassell, James L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Summary of Flight Data Obtained From 0.12-Scale Rocket-Powered Models of the Chance Vought Regulus 2 Missile

Description: Report discussing the longitudinal static and dynamic stability, overall duct performance, drag, and some static and dynamic lateral-stability data obtained from testing of the Chance Vought Regulus II missile. Five different models with various modifications were used in the investigation.
Date: August 19, 1958
Creator: Wineman, Andrew R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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