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Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades
Heat-transfer investigation conducted on cooled as well heated impulse-type turbine blades in a static cascade to determine the effect of direction of heat flow on convective heat-transfer coefficients.
Date:
March 9, 1951
Creator:
Hubbartt, James E. & Schum, Eugene F.
System:
The UNT Digital Library
Investigations toward simplification of missile control systems
Paper presenting three ideas regarding potential simplifications of missile-control systems in order to make them more reliable without sacrificing system performance. The three methods presented include an autorotating-vane spoiler, a bellows flap, and free controls. All are based on modified airplane control systems.
Date:
November 12, 1953
Creator:
Curfman, Howard J., Jr.; Strass, H. Kurt & Crane, Harold L.
System:
The UNT Digital Library
Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings
Report presenting an investigation of an 18-foot-radius helicopter rotor powered by tip-mounted ramjet engines in the helicopter test tower. The engine performance is compared with the performance determined in a previous investigation of a 9-foot-radius rotor with the same engines at similar speeds but with twice the centrifugal forces. Results regarding the propulsive characteristics, minimum specific fuel consumption and corresponding propulsive thrust, and operational characteristics are provided.
Date:
October 7, 1953
Creator:
Radin, Edward J. & Carpenter, Paul J.
System:
The UNT Digital Library
Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data
Report presenting a wind-tunnel investigation of a model equipped with a 60 degree delta wing and a 60 degree delta horizontal all-movable canard control surface to determine the stability, control, and canard-surface hinge-moment characteristics at low speeds and at a Reynolds number of 9 x 10(exp 6). Two longitudinal positions of the canard surface were tested. Results regarding lift and pitching moment, drag, and hinge moment are provided.
Date:
June 17, 1954
Creator:
Burrows, Dale L.
System:
The UNT Digital Library
Wind-Tunnel Investigation to Determine the Horizontal- and Vertical-Tail Contributions to the Static Lateral Stability Characteristics of a Complete-Model Swept-Wing Configuration at High Subsonic Speeds
Results regarding an investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. Generally, Mach number effects within the range studied and wing effects on the tail contribution were small and the overall trends of the data of the present investigation agreed with those which have been established at low speeds.
Date:
July 10, 1953
Creator:
Wiggins, James W.; Kuhn, Richard E. & Fournier, Paul G.
System:
The UNT Digital Library
Rocket-Model Investigation to Determine the Hinge-Moment and Normal-Force Properties of a Full-Span, Constant-Chord, Partially Balanced Trailing-Edge Control on a 60 Degree Clipped Delta Wing Between Mach Numbers of 0.50 and 1.26
Report presenting a free-flight investigation of a rocket-powered research model to determine the hinge-moment and normal-force characteristics of a trailing-edge control on a delta wing between Mach numbers of 0.50 and 1.26. The hinge-line location of 40 percent control chord satisfactorily reduced the high hinge moments associated with plain flap-type controls. Results regarding hinge moments and normal force are provided.
Date:
October 30, 1953
Creator:
Martz, C. William & Goslee, John W.
System:
The UNT Digital Library
A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36 degrees
Report presenting a pressure-distribution investigation of a parabolic body of revolution with a fineness ratio of 12.2, which was performed in the 4- by 4-foot supersonic tunnel at Mach number 1.59 and Reynolds number 3.6 x 10(sub 6), based on body length, for a range of angles of attack. Results regarding basic pressures, aerodynamic coefficients, asymmetrical pressures, comparison of experimental and theoretical pressures, artificial roughness, section coefficients, and body coefficients are provided.
Date:
October 30, 1952
Creator:
Cooper, Morton; Gapcynski, John P. & Hasel, Lowell E.
System:
The UNT Digital Library
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
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 allowable center-of-gravity travel are provided.
Date:
January 21, 1953
Creator:
Johnson, Joseph L., Jr.
System:
The UNT Digital Library
The Effects of a Small Jet of Air Exhausting From the Nose of a Body of Revolution in Supersonic Flow
Report presenting the results of an investigation to determine the effects of a small jet of air exhausting from the nose of an elliptical body of revolution upon boundary-layer transition and the viscous, pressure, and total drag of the forebody at three body stations at Mach number 1.62. The jet effects on body pressure, pressure variations, boundary-layer transition, and total drag are provided.
Date:
November 12, 1952
Creator:
Love, Eugene S.
System:
The UNT Digital Library
Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (With Fins) at a Mach Number of 1.62 in the Langley 9-Inch Supersonic Tunnel
Report presenting an investigation of a fin-stabilized scale model of the NACA RM-10 missile at a Mach number of 1.62. Measurements were made of the lift, drag, and pitching moment of the finned body over a range of angles of attack. Comparisons with the results from other testing facilities are also provided.
Date:
December 19, 1952
Creator:
Coletti, Donald E.
System:
The UNT Digital Library
An experimental study of five annular air inlet configurations at subsonic and transonic speeds
Report presenting an investigation of an NACA 1-80-100 nose inlet fitted alternately with an elliptical, a parabolic, a 14 degree-inch conical, and a 22 degree-inch conical central body at subsonic and transonic speeds in the 8-foot transonic tunnel. Drag, surface-pressure, and pressure-recovery measurements were obtained at 0 degrees angle of attack through a range of Mach numbers. Results regarding tunnel boundary interference, surface-pressure distribution, external drag, pressure recovery, and propulsive thrust comparison are provided.
Date:
August 19, 1953
Creator:
Pendley, Robert E.; Milillo, Joseph R.; Fleming, Frank F. & Bryan, Carroll R.
System:
The UNT Digital Library
Wind-Tunnel Investigation at Low Speed of a Wing Having 63 Degree Sweepback and a Drooped Tip
From Summary: "The results of force tests made at low speed are presented to show the effect of longitudinal static stability produced by drooping the tip of a 63 degree sweptback wing. Five semispan wing models were tested: two incorporated curved drooped tips, two with abruptly drooped tips, and one without droop. The most favorable stability characteristics were measured for a model with an abruptly drooped tip, a fence, and a leading-edge flap; however, the use of these same auxiliary devices on the undrooped wing was nearly as effective."
Date:
April 7, 1955
Creator:
Blackaby, James R.
System:
The UNT Digital Library
Development of a new flutter testing technique using a towed dynamic airplane model equipped with an automatic stabilizing system: Experimental and calculated dynamic stability characteristics for speeds up to 200 mph
Report presenting testing of a towed airplane model in the 19-foot pressure tunnel in conjunction with the development of a flutter testing technique. The model was equipped with an autopilot to keep the model flying straight and level in the tunnel while restrained only in drag. Results regarding period and cycles to damp to half amplitude, time histories, and motions of the flexible wing model are provided.
Date:
March 25, 1955
Creator:
Schneider, William C.
System:
The UNT Digital Library
Simulator studies of a simple homing system
Report presenting simulator studies of a homing missile pursuing a constant-velocity nonmaneuvering target. The missile dynamics in pitch and roll, seeker method of deflection and control, and the missile-target geometry were simulated to determine whether the method of control and detection in conjunction with the missile dynamics were feasible.
Date:
October 6, 1955
Creator:
Passera, Anthony L. & Garner, H. Douglas
System:
The UNT Digital Library
An Investigation of Loads on Ailerons at Transonic Speeds
"Some aileron load characteristics for three thin wings varying in sweep have been presented for Mach numbers from 0.80 to 1.05. For the transonic Mach number range, shock effects exert a large influence on the loading, but the exact location of each shock for a specific wing design cannot be cataloged at the present time. It is shown, however, that the aileron loading, although greater in magnitude than at subsonic speeds, nevertheless varies in as uniform a fashion as at subsonic speeds" (p. 1).
Date:
May 27, 1955
Creator:
Runckel, Jack F. & Gray, W. H.
System:
The UNT Digital Library
Wind-Tunnel Investigation at Low Speed of Sideslipping, Rolling, Yawing, and Pitching Characteristics for a Model of a 45 Degree Swept-Wing Fighter-Type Airplane
Report presenting an investigation in the stability tunnel at low speed to determine the rolling characteristics at combined angles of attack and sideslip for a model of a fighter-type airplane with a 45 degree sweptback wing. Testing was performed with the original vertical tail and a vertical tail with a 27 percent larger exposed area. Results regarding the static longitudinal stability, directional stability, and effect of the different tails are presented.
Date:
September 1, 1955
Creator:
Jaquet, Byron M. & Fletcher, H. S.
System:
The UNT Digital Library
An Experimental Investigation of the Flow Phenomena Over Bodies at High Angles of Attack at a Mach Number of 2.01
Report presenting an investigation in the supersonic pressure tunnel at Mach number 2.01 to study the wake patterns in the lee of bodies at high angles of attack. The configurations tested consisted of two cylindrical body shapes, one circular and one elliptical in cross section, with a fineness-ratio-3.5 ogival nose and a fineness-ratio-6 conical nose. Results regarding vapor-screen photographs, wake characteristics, wake patterns, wake characteristics, and testing with transition strips are included.
Date:
October 27, 1955
Creator:
Gapcynski, John P.
System:
The UNT Digital Library
Wing-load measurements at supersonic speeds of the Douglas D-558-II research airplane
From Summary: "Flight measurements of the aerodynamic wing loads on the D-558-II airplane have been made in the Mach number range from 1.0 to 2.0. Nonlinear wing-panel characteristics occurred with variations in angle of attack. These nonlinear characteristics were apparent primarily at the lower supersonic speeds."
Date:
March 30, 1955
Creator:
Robinson, Glenn H.; Cothren, George E., Jr. & Pembo, Chris
System:
The UNT Digital Library
Statistical measurements of landing contact conditions of the Boeing B-47 airplane
Report presenting a determination of the landing contact conditions of the Boeing B-47 airplane using a specially built motion picture camera. A statistical analysis of the sinking speeds and horizontal speeds was carried out on the photographs.
Date:
October 27, 1955
Creator:
Kolnick, Joseph J. & Morris, Garland J.
System:
The UNT Digital Library
Modified tubular combustor as high-temperature gas generators
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.
System:
The UNT Digital Library
An experimental investigation of the unsteady lift induced on a wing in the downwash field of an oscillating canard control surface
Report presenting the results of an experimental investigation of the unsteady lift induced on a wing in the downwash field of an oscillating canard control surface. The results indicated that existing theories provide a reliable guide for the estimation of the magnitude of the lift derivatives and centers of pressure at low values of reduced frequency and low angles of attack.
Date:
August 15, 1955
Creator:
Reese, David E., Jr.
System:
The UNT Digital Library
Estimation of Incremental Pitching Moments Due to Trailing-Edge Flaps on Swept and Triangular Wings
Report presenting a method by which incremental pitching moments can be estimated for swept and triangular wings with arbitrary types of trailing-edge high-lift flaps. Span-loading theory is combined with two-dimensional airfoil data adjusted for the effects of sweep. Application of the method is demonstrated for 58 cases covering various types of flaps on wings with a wide range of sweep, aspect ratio, and taper ratio.
Date:
June 10, 1955
Creator:
James, Harry A. & Hunton, Lynn W.
System:
The UNT Digital Library
Aerodynamic heating of rocket-powered research vehicles at hypersonic speeds
From Introduction: "The purpose of this paper is to present and discuss skin temperature measurements from two flight tests. Temperature measurements were obtained to a Mach number of 5.4 on the first flight and to a Mach number of 10.4 on the second flight."
Date:
July 19, 1955
Creator:
Piland, Robert O. & Collie, Katherine A.
System:
The UNT Digital Library
Simplified procedures for estimating flap-control loads at supersonic speeds
Report presenting an investigation to determine the possibility of using simplified procedures for the estimation of control loads at supersonic speeds. The results indicated that relatively simple procedures are possible for the estimation of loadings on flap-type controls at supersonic speeds for cases when no flow separation occurs ahead of the hinge line.
Date:
May 27, 1955
Creator:
Czarnecki, K. R. & Lord, Douglas R.
System:
The UNT Digital Library