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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
Force and Pressure Measurements on Several Canopy-Fuselage Configurations at Transonic Mach Numbers 1.41 and 2.01
Report presenting an investigation on canopy pressures and canopy-fuselage forces and moments under conditions of combined pitch and sideslip. The canopy configurations tested varied in windshield shape (flat, vee, and round) and were tested at two Mach numbers and Reynolds numbers.
Date:
December 15, 1955
Creator:
Robins, A. Warner
System:
The UNT Digital Library
Component Operating Trends During Acceleration and Deceleration of Two Hypothetical Two-Spool Turbojet Engines
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.
System:
The UNT Digital Library
Wing Pressure Distributions Over the Lift Range of the Convair XF92A Delta-Wing Airplane at Subsonic and Transonic Speeds
Report presenting chordwise pressure distributions measured over the left wing of the Convair XF-92A delta-wing airplane to determine the effect of lift on the wing characteristics at subsonic and transonic Mach numbers. Results regarding the chordwise pressure distributions, wing-section aerodynamic characteristics, spanwise distributions, and elevon-section loads are provided.
Date:
November 30, 1955
Creator:
Keener, Earl R. & Jordan, Gareth H.
System:
The UNT Digital Library
Ditching investigation of a 1/25-scale model of a 255,000-pound transport airplane
"An investigation was made of a 1/25-scale dynamically similar model of a 255,000-pound transport airplane in order to study its behavior when ditched. The model was free-launched from the Langley tank no. 2 monorail carriage into calm water. Various landing attitudes, flap settings, speeds, and configurations were investigated" (p. 1).
Date:
July 13, 1955
Creator:
Windham, John O.
System:
The UNT Digital Library
Investigation of some wake vortex characteristics of an inclined ogive-cylinder body at Mach number 1.98
Report presenting measurements of the pitot-pressure distributions in the flow field, pressure distributions over the body, and downwash distributions through shed vortices for an inclined body of revolution at a free-stream Mach number of 1.98. Results regarding the experimental pressure distributions and vortex positions, vortex strengths computed from experiment, comparisons of theoretical and experimental vortex paths, and comparisons of theoretical and experimental downwash distributions through the body vortices are provided.
Date:
August 23, 1955
Creator:
Jorgensen, Leland H. & Perkins, Edward W.
System:
The UNT Digital Library
Investigation of Equilibrium Temperatures and Average Laminar Heat-Transfer Coefficients for the Front Half of Swept Circular Cylinders at a Mach Number of 6.9
Report presenting the average heat-transfer coefficients and equilibrium temperatures for the front half of an isothermal cylinder with a laminar boundary layer as determined by wind tunnel testing at Mach number 6.9 and a range of Reynolds numbers and sweep angles.
Date:
August 18, 1955
Creator:
Feller, William V.
System:
The UNT Digital Library
Preliminary performance data of several tail-pipe-cascade-type model thrust reversers
Report presenting the reverse-thrust performance of several tail-pipe-cascade-type model thrust reversers over a range of exhaust-nozzle pressure ratios from 1.2 to 2.4. Both symmetrical and asymmetrical cascade blade shapes were investigated. Results regarding the performance of tail-pipe-cascade-type model thrust reversers having symmetrically shaped cascade blades and the performance of tail-pipe-cascade-type model thrust reversers having asymmetrically shaped cascade blades are provided.
Date:
August 29, 1955
Creator:
Henzel, James G., Jr. & McArdle, Jack G.
System:
The UNT Digital Library
Theoretical Investigation of Laminar Heat Transfer on Yawed Infinite Cylinders in Supersonic Flow and a Comparison With Experimental Data
Report presenting a theoretical method for calculating heat transfer in the laminar boundary layer on yawed infinite cylinders in compressible flow. The method can be applied to a cylinder of arbitrary cross section and arbitrary chordwise wall-temperature distribution. The variation in local heat transfer around the surface of the cylinder was found to have little functional dependence on yaw angle or wall temperature.
Date:
August 9, 1955
Creator:
Beckwith, Ivan E.
System:
The UNT Digital Library
Experimental investigation of a transonic compressor rotor with a 1.5-inch chord length and an aspect ratio of 3.0 2: blade-element performance
Report presenting a transonic compressor rotor with double-circular-arc blade sections, which were designed and tested to investigate the aerodynamic effects of using a short blade chord and a high aspect ratio. The report presents the blade-element performance and performance analysis.
Date:
August 18, 1955
Creator:
Schwenk, Francis C. & Tysl, Edward R.
System:
The UNT Digital Library
Some Effects of Fluid in Pylon-Mounted Tanks on Flutter
Report presenting fluid-dynamics studies of a tank of fineness ratio 7.0 which was pylon mounted on a simplified two-dimensional flutter model in order to determine the effects of the fluid on flutter. The flutter speed was determined for three cases: with various amounts of water in the tank, with weights with the same mass and moment of inertia as the fluid considered to be a frozen solid, and with weights with the same mass and moment of inertia as the actual fluid. Results regarding the flutter speed, effects of inertia on flutter, and amplitude of flutter are provided.
Date:
July 19, 1955
Creator:
Reese, James R.
System:
The UNT Digital Library
The Unsteady Normal-Force Characteristics of Selected NACA Profiles at High Subsonic Mach Numbers
Report presenting a wind-tunnel investigation at subsonic Mach numbers up to 0.9 to measure the root-mean-square variation of the normal forces on 27 NACA airfoil sections. The effects of thickness-chord ratio, camber, location of minimum pressure, and leading-edge radius were investigated.
Date:
May 27, 1955
Creator:
Polentz, Perry P.; Page, William A. & Levy, Lionel L., Jr.
System:
The UNT Digital Library