National Advisory Committee for Aeronautics (NACA) - 165 Matching Results

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A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel

Description: Report presenting an investigation to study the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel. The results indicated that the large increases in allowable center-of-gravity travel could be obtained using the devices. Results regarding the basic aerodynamic data, effect of tail configuration on the allowable center-of-gravity travel, and a comparison of measured and predicted values of the allowa… more
Date: January 21, 1953
Creator: Johnson, Joseph L., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Modified tubular combustor as high-temperature gas generators

Description: A pair of combustors and transition liners in a quarter-annular, direct-connect assembly was operated at temperatures up to 2400 degrees F to determine the feasibility of using production-type combustor systems as high-tmeperature gas generators for turbine-cooling studies. Operation at high temperatures for 32 hours was possible when minor liner modifications were made that provided greater cooling-air flow between the turbine casing and interior components.
Date: October 21, 1955
Creator: Friedman, Robert & Zettle, Eugene V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Component Operating Trends During Acceleration and Deceleration of Two Hypothetical Two-Spool Turbojet Engines

Description: Memorandum presenting an investigation of the compressor and turbine operating trends during acceleration and deceleration of two hypothetical two-spool turbojet engines. The two engines have the same component performance maps but the arbitrarily specified ratio of outer- to inner-spool moment of inertia for the second engine is 4 times that specified for the first engine. Results regarding the acceleration characteristics and deceleration characteristics are provided.
Date: April 21, 1955
Creator: Dugan, James F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Measurements of Horizontal-Tail Loads on the Bell X-5 Research Airplane at a Sweep Angle of 58.7 Degrees

Description: A flight investigation was made at altitudes of 40,000, 25,000 and 15,000 feet to determine the horizontal-tail loads of the Bell X-5 research airplane at a sweep angle of 58.7 deg over the lift range of the airplane for Mach numbers from 0.61 to 1.00. The horizontal-tail loads were found to be nonlinear with lift throughout the lift ranges tested at all Mach numbers except at a Mach number of 1.00. The balancing tail loads reflected the changes which occur in the wing characteristics with inc… more
Date: July 21, 1955
Creator: Reed, Robert D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effect of fluid injection on the compressible turbulent boundary layer: preliminary tests on transpiration cooling of a flat plate at M = 2.7 with air as the injected gas

Description: Report presenting local values of heat-transfer rate and temperature-recovery factor obtained on a transpiration-cooled flat plate. The results show primarily that transpiration cooling in a turbulent boundary layer at M = 2.7 has marked effects on the heat transfer and recovery temperature for nearly uniform air injection along the plate.
Date: December 21, 1955
Creator: Rubesin, Morris W.; Pappas, Constantine C. & Okuno, Arthur F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Evaporation of JP-5 fuel sprays in air streams

Description: Report presenting a continuous sampling-probe technique used to determine the percentage of JP-5 fuel spray evaporated under conditions common in ramjet engines. Fuel was injected contraststream from a multiple-orifice injector and sampling data were obtained at several distances downstream of the injector. An expression is generated for a description of this phenomenon.
Date: February 21, 1956
Creator: Foster, Hampton H. & Ingebo, Robert D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Interference Lift, Drag, and Pitching Moment of a Series of Triangular-Wing and Body Combinations at a Mach Number of 1.94

Description: Report presenting an investigation at Mach number 1.94 of a series of triangular-wing and body combinations to determine the interference lift, drag, and pitching moment. The models had a series of seven flat-plate triangular wings of varying scale, four with semiapex angles of 30 degrees, and three with semiapex angles of 45 degrees. Results indicated that the interference between the wing and the body gave an increase in lift over the wing and body alone, but at the expense of more drag.
Date: December 21, 1955
Creator: Coletti, Donald E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Theoretical Investigation of a Compensating Network With Application to Roll Control Systems for Automatic Interceptors

Description: Memorandum presenting a theoretical analysis of an airplane automatic control system incorporating a compensating network. The compensating network is a computing network that has characteristics that are the inverse of the airframe; consequently, airplane dynamics are eliminated from the system response. Results regarding the displacement control system, the velocity command system, and the acceleration control system are provided.
Date: July 21, 1955
Creator: Sherman, Windsor L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An experimental investigation at a Mach number of 2.01 of the effects of body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effect of changes in body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations. A series of 13 bodies of a given length and volume but various cross-section shapes were tested at a Mach number of 2.01. The results showed that changes in drag at zero lift due to changes in body cross-section shape from the basic circular shape are small and of the same order a… more
Date: July 21, 1955
Creator: Carlson, Harry W. & Gapcynski, John P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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

Description: Report presenting an investigation of aircraft which are required to maneuver rapidly at extreme altitudes, which involves reaching maximum loads at high angles of attack. Load information is necessary for that flight condition and for aircraft that reach their maximum loads at high speed and high dynamic pressures. Results regarding the wings and wing-body combinations are provided.
Date: July 21, 1955
Creator: Katzen, Elliott D. & Pitts, William C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a 1/4-Scale Model of the Republic F-105 Airplane in the Langley 19-Foot Pressure Tunnel: Longitudinal Stability and Control of the Model Equipped with a Supersonic-Type Elliptical Wing-Root Inlet

Description: Memorandum presenting development tests on a 1/4-scale model of the Republic F-105 airplane in the 19-foot pressure tunnel. The tests in this particular report include longitudinal stability and control tests of the basic design provided by the contractor, tests of various modifications designed to improve the stability characteristics of the model with the trailing-edge flaps deflected, brief exploratory lateral-control and rudder-effectiveness tests, and stall studies and duct air-flow measur… more
Date: July 21, 1954
Creator: Kelly, H. Neale & Cancro, Patrick A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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: Static Longitudinal Stability and Control, M = 2.01

Description: Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of various vertical locations of the wing and horizontal tail on the aerodynamic characteristics in pitch and of a supersonic airplane configuration at Mach number 2.01. The model was equipped with a wing and horizontal tail, each having a 45 degree sweep and an aspect ratio of 4. The configurations investigated included a high-wing, a mid-wing, and a low-wing arrangement, each with fo… more
Date: February 21, 1956
Creator: Spearman, M. Leroy & Driver, Cornelius
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of turbines suitable for use in a turbojet engine with high compressor ratio and low compressor-tip speed 5: experimental performance of two-stage turbine with downstream stator

Description: An experimental investigation of a highly loaded two-stage turbine with a downstream stator revealed that (1) at equivalent design work and speed the brake internal efficiency was 0.81 and the maximum efficiency obtained was 0.85, and (2) the downstream stator left very little energy in the form of tangential velocity in the gas and, in general, performed well with 0.78 recovery being obtained at equivalent design work and speed.
Date: October 21, 1951
Creator: Davison, Elmer H.; Petrash, Donald A. & Schum, Harold J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Model ditching investigation of the Boeing 707 jet transport

Description: Report presenting an investigation of the ditching characteristics of the Boeing 707 jet transport in tank no. 2. Various conditions of damage, landing attitude, and speed were investigated. Data were obtained from visual observations, acceleration records, and motion pictures.
Date: November 21, 1955
Creator: Thompson, William C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel III : the effectiveness and hinge moments of a skewed wing-tip flap

Description: Results of wind-tunnel tests of a semispan model of a triangular wing of aspect ratio 2 with a skewed wing-tip flap are presented. Lift, drag, pitching-moment, and hinge-moment data are included for subsonic Mach numbers up to 0.95. The flap showed extremely high hinge moments and low effectiveness as a longitudinal control. Although less affected by compressibility, this flap is indicated to be inferior to a constant-chord flap when applied to this triangular wing.
Date: September 21, 1948
Creator: Kolbe, Carl D. & Tinling, Bruce E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Investigation of a large-scale model at low speed

Description: From Introduction: "This report presents the aerodynamic characteristics at low speed end high Reynolds number as determined in the Ames 40- by 80 foot wind tunnel."
Date: January 21, 1949
Creator: McCormack, Gerald M. & Walling, Walter C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Investigation at Transonic and Supersonic Speeds of a Wing-Aileron Configuration Simulating the D-558-2 Airplane

Description: "An investigation of the rolling effectiveness at transonic and supersonic speeds of a wing-aileron configuration simulating the D-558-2 airplane has been made by means of a rocket-propelled test vehicle. The variation of rolling effectiveness with Mach number is similar to that obtained previously for tapered sweptback wings having full-span, 0.2-chord ailerons" (p. 1).
Date: July 21, 1948
Creator: Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of 24-inch supersonic axial-flow compressor in air 2: performance of compressor rotor at equivalent tip speeds from 800 to 1765 feet per second

Description: Report presenting an investigation of a 24-inch-diameter rotor for a supersonic axial-flow compressor in air up to an actual tip speed of 1654 feet per second and a maximum equivalent tip speed of 1765 feet per second. Results regarding overall performance, rotor-inlet characteristics, rotor-passage flow characteristics, and rotor-outlet characteristics are provided.
Date: January 21, 1949
Creator: Johnsen, Irving A.; Wright, Linwood C. & Hartmann, Melvin J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel 2: the effectiveness and hinge moments of a constant-chord plain flap

Description: Report presenting a semispan triangular wing with a constant-chord trailing-edge flap to evaluate the aerodynamic characteristics of the wing with landing speeds up to a Mach number of 0.95. Tests were included to ascertain the effects of the addition of a body and of modifications to the airfoil section. Results regarding the wing alone with low Mach number, wing alone with high Mach number, effect of the body, effect of the flap, effect of Mach number, lift-drag ratio, and wing-profile modifi… more
Date: September 21, 1948
Creator: Stephenson, Jack D. & Amuedo, Arthur R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Tests to Determine the Drag of Fin-Stabilized Parabolic Bodies at Transonic and Supersonic Speeds

Description: Report presenting testing on parabolic bodies of revolution of two fineness ratios in the transonic and supersonic range. One had a body fineness ratio of 7.87 and one had a ratio of 12 and were tested under different Mach number ranges. Experimental results and drag estimates of various portions of the body are provided.
Date: April 21, 1948
Creator: Alexander, Sidney R.; Chauvin, Leo T. & Rumsey, Charles B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurement Through the Speed of Sound of Static Pressures on the Rear of Unswept and Sweptback Circular Cylinders and on the Rear and Sides of a Wedge by the NACA Wing-Flow Method

Description: Report presenting static-pressure measurements made through the speed of sound by the NACA wing-flow method at the back of two unswept circular cylinders and one sweptback cylinder. Static pressures were found to decrease considerably with an increase in Mach number. Information about the length and diameter of the cylinders and how it affects measurements is provided.
Date: July 21, 1948
Creator: Sawyer, Richard H. & Daum, Fred L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of wing characteristics at a Mach number of 1.53 3: unswept wings of differing aspect ratio and taper ratio

Description: Report presenting testing of seven models that from two different wing series: a series of taper ratio 0.5 and differing aspect ratio and a series of aspect ratio 4 and differing taper ratio. Measurements of lift, drag, and pitching moment were made at Mach number 1.53. The aerodynamic parameters generally varied with aspect ratio and taper ratio in the manner indicated by the linear theory.
Date: June 21, 1948
Creator: Nielsen, Jack N.; Matteson, Frederick H. & Vincenti, Walter G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An investigation at low speed of a 51.3 degrees sweptback semispan wing with a raked tip and with 16.7-percent-chord ailerons having three spans and three trailing-edge angles

Description: Report presenting a wind-tunnel investigation at low speed to determine the aerodynamic characteristics of a 51.3 degree sweptback semispan wing with a raked tip and with 16.7-percent-chord sealed plain ailerons. Lift, drag, pitching-moment, and hinge-moment data were obtained for the wing with transition free and fixed with various spans of aileron deflected as lift flaps. The rolling moment, yawing moment, hinge moment, and aileron seal pressure characteristics were determined for each of the… more
Date: July 21, 1948
Creator: Fischel, Jack & Schneiter, Leslie E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of a nacelle on the low-speed aerodynamic characteristics of a swept-back wing

Description: Wind-tunnel tests of a simplified nacelle on a semispan wing having approximately 35 degrees of sweepback were made at low speeds to evaluate the effects of the nacelle on the aerodynamic characteristics of the wing. Force, moment, and pressure-distribution measurements are presented for the nacelle underslung and centrally mounted on the wing and mounted on a strut below the wing.
Date: July 21, 1948
Creator: Hanson, Frederick H., Jr. & Dannenberg, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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