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332 Matching Results
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Force and Pressure Measurements on Several Canopy-Fuselage Configurations at Mach Numbers 1.41 and 2.01
Memorandum presenting an investigation conducted in the supersonic pressure tunnel on canopy pressures and canopy-fuselage forces and moments under conditions of combined pitch and sideslip. The canopy configurations tested varied in windshield shape, location on the fuselage, and fineness ratio. Results regarding force and moment data, pressure data, and force and pressure correlation are provided.
Date:
December 15, 1955
Creator:
Robins, A. Warner
System:
The UNT Digital Library
A comparison with flight data of vertical-tail loads in various maneuvers estimated from sideslip angles and rudder deflections
Report presenting a comparison of the vertical-tail loads determined from pressure-distribution measurements in flight in various maneuvers with the corresponding vertical-tail loads. Some of the maneuvers investigated included slow rolls, steady sideslips, fishtails, and rolling pull-outs.
Date:
December 11, 1947
Creator:
Turner, Howard L.
System:
The UNT Digital Library
A suggested method of analyzing for transonic flutter of control surfaces based on available experimental evidence
Report presenting the results of a study of the movement of shocks on a three-dimensional wing with and without aileron flutter occurring. The studies include a number of changes and variations to the wing and control. Results for the standard wing and aileron, spoilers at 50 percent chord, upper and lower surface, faired bumps at the 50-percent-chord and 70-percent-chord positions, variations of thickness ratio along the span, vent holes between upper and lower surface, aileron-contour change, aileron mass overbalance, dampers, wing flutter, buffeting forces on fixed controls, and static characteristics are provided.
Date:
December 16, 1947
Creator:
Erickson, Albert L. & Stephenson, Jack D.
System:
The UNT Digital Library
Aerodynamic Characteristics Including Scale Effect of Several Wings and Bodies Alone and in Combination at a Mach Number of 1.53
From Introduction: "In the present report, the results for the wings and bodies of revolution alone are first analyzed in comparison with exiting theory."
Date:
December 20, 1946
Creator:
Van Dyke, Milton D.
System:
The UNT Digital Library
An Investigation at Low Speed of a Large-Scale Triangular Wing of Aspect Ratio Two 2: The Effect of Airfoil Section Modifications and the Determination of the Wake Downwash
Report presenting a study of the characteristics of a large-scale triangular wing to include the effects of section modifications. The wing in this report is the same as the one in the previous report but features various degrees of rounding of the wing leading edge and wing maximum thickness rather than having sharp edges. Results regarding the effects of airfoil section modifications, visible trailing vortices, and surveys in the extended chord plane are provided.
Date:
December 10, 1947
Creator:
Anderson, Adrien E.
System:
The UNT Digital Library
High-Speed Aerodynamic Characteristics of Four Thin NACA 63-Series Airfoils
Memorandum presenting high-speed wind-tunnel tests of four thin NACA 63-series airfoil sections with a design lift coefficient of 0.2 with the uniform-load type of mean camber line to determine the effectiveness of forward movement of the minimum-pressure position in improving the high-speed lift characteristics of low-drag airfoils. Results regarding the tunnel-wall effects, lift coefficient, drag coefficient, and moment coefficient are provided.
Date:
December 31, 1947
Creator:
Ilk, Richard J.
System:
The UNT Digital Library
Comparison of the transonic drag characteristics of two wing-body combinations differing only in the location of the 45 degree sweptback wing
Report presenting the drag of a series of wing-body combinations by the free-fall method in order to provide information on the drag characteristics of promising transonic and supersonic airplane arrangements. Time histories, Mach number variations, and drag coefficients for several areas of the body are provided.
Date:
December 8, 1947
Creator:
Mathews, Charles W. & Thompson, Jim Rogers
System:
The UNT Digital Library
An experimental investigation of NACA submerged air inlets on a 1/5-scale model of a fighter airplane
From Summary: "The results of an experimental investigation of an NACA submerged-air-inlet system on a 1/5-scale model of a fighter airplane are presented. Preliminary development tests were conducted to select the optimum entrance configuration. Duct-system total-pressure losses and pressure distributions over the lip and ramp of this air intake were obtained."
Date:
December 5, 1947
Creator:
Gault, Donald E.
System:
The UNT Digital Library
Tests of the landing on water of a model of a high-speed airplane - Langley tank model 229
Report presenting an investigation at the tank no. 2 monorail of the landing on smooth water of a dynamic model of a hypothetical jet- and rocket-propelled airplane designed to fly at transonic speeds. The model skipped out of the water and experienced maximum normal accelerations up to 7.4g and maximum longitudinal accelerations up to 4.5g. Results of landing the basic model and landing the modified model that has a slightly different fuselage are provided.
Date:
December 9, 1947
Creator:
King, Douglas A.
System:
The UNT Digital Library
Investigation of wing characteristics at a Mach number of 1.53 1: triangular wings of aspect ratio 2
Report presenting wind-tunnel testing conducted on three sharp-edge wing models with a thickness ratio of 5 percent and a common triangular plan form of aspect ratio 2. Measurements of lift, drag, and pitching moment were made at Mach number 1.53. The experimental lift and moment curves were found to conform essentially with the superposition principle of the linear theory.
Date:
December 19, 1947
Creator:
Vincenti, Walter G.; Nielsen, Jack N. & Matteson, Frederick H.
System:
The UNT Digital Library
Supersonic-Tunnel Tests of Two Supersonic Airplane Model Configurations
Report presenting supersonic-tunnel tests of two models of similar supersonic airplane configurations at Mach numbers of 1.55, 1.90, and 2.32 to determine values of the drag, lift, pitching moment, yawing moment, and side force. The models were similar except for the vertical wing location relative to the body axis and horizontal tail; one had a high wing and one had a low wing. Results regarding the precision of data, Reynolds numbers of tests, results at the different Mach numbers, and Schileren photographs are provided.
Date:
December 31, 1947
Creator:
Ellis, Macon C., Jr.; Hasel, Lowell E. & Grigsby, Carl E.
System:
The UNT Digital Library
High-Speed Wind-Tunnel Investigation of the Lateral Control Characteristics of Plain Ailerons on a Wing with Various Amounts of Sweep
"A three-dimensional investigation of straight-sided-profile plain ailerons on a wing with 30 degrees and 45 degrees of sweepback and sweepforward was made in a high-speed wind tunnel for aileron deflections from -10 degrees to 10 degrees and at Mach numbers from 0.60 to 0.96. Wing configurations of 30 degrees generally reduced the severity of the large changes in rolling-moment and aileron hinge-moment coefficients experienced by the upswept wing configurations as the result of compression shock and extended to higher Mach numbers the speeds at which such changes occurred" (p. 1).
Date:
December 19, 1947
Creator:
Luoma, Arvo A.; Bielat, Ralph P. & Whitcomb, Richard T.
System:
The UNT Digital Library
Comparative Tests of the Rolling Effectiveness of Constant-Chord, Full-Delta, and Half-Delta Ailerons on Delta Wings at Transonic and Supersonic Speeds
Report presenting comparative tests of the rolling power of plain constant-chord, full-delta, and half-delta ailerons on delta wings with varying degrees of sweepback were tested on rocket-propelled test vehicles. Results regarding the effect of leading-edge sweepback, a comparison of rolling effectiveness, and comparison with theory are provided.
Date:
December 12, 1949
Creator:
Sandahl, Carl A. & Strass, H. Kurt
System:
The UNT Digital Library
Low-Speed Investigation of Deflectable Wing-Tip Ailerons on an Untapered 45 Degrees Sweptback Semispan Wing With and Without an End Plate
Report presenting a low-speed wind-tunnel investigation to determine the characteristics of deflectable wing-tip ailerons on an untapered 45 degree sweptback semispan wing. Ailerons with triangular and parallelogram plan forms with a maximum chord of 0.625 wing chord and a flat-plat profile were investigated. The aerodynamic characteristics in pitch and lateral control characteristics are included.
Date:
December 14, 1949
Creator:
Fischel, Jack & Watson, James M.
System:
The UNT Digital Library
Investigation of Pressure Distribution over an Extended Leading-Edge Flap on a 42 Degrees Sweptback Wing
Pressure distribution over an extended leading-edge flap on a 42 degree swept-back wing was investigated. Results indicate that the flap normal-force coefficient increased almost linearly with the angle of attack to a maximum value of 3.25. The maximum section normal-force coefficient was located about 30 percent of the flap span outboard of the inboard end and had a value of 3.75. Peak negative pressures built up at the flap leading edge as the angle of attack was increased and caused the chordwise location of the flap center of pressure to be move forward.
Date:
December 19, 1947
Creator:
Conner, D. William & Foster, Gerald V.
System:
The UNT Digital Library
Preliminary Tests to Determine the Maximum Lift of Wings at Supersonic Speeds
Report presenting the results of a test program in a supersonic tunnel to determine the maximum lift of wings operating at supersonic speeds. A variety of wing plan forms of several thickness distributions were tested at a range of Mach numbers, Reynolds numbers, and angles of attack. The lift results, drag results, and Schileren photographs are described.
Date:
December 11, 1947
Creator:
Gallagher, James J. & Mueller, James N.
System:
The UNT Digital Library
Tests of Submerged Duct Installation on a Modified Airplane in the Ames 40- by 80-foot Wind Tunnel
Memorandum presenting an investigation of an NACA submerged intake installation on a modified fighter airplane conducted to determine the full-scale aerodynamic characteristics of this installation. Additionally, tests were conducted on the submerged inlet with revised entrance lips and deflectors to determine the configuration which would result in the best dynamic pressure recovery measured at the inlet for this installation without a major rework of the entrance.
Date:
December 11, 1947
Creator:
Martin, Norman J.
System:
The UNT Digital Library
Experimental Investigation of a Preloaded Spring-Tab Flutter Model
"An experimental investigation was made of a preloaded spring-tab flutter model to determine the effects on flutter speed of aspect ratio, tab frequency, and preloaded spring constant. The rudder was mass-balanced, and the flutter mode studied was essentially one of three degrees of freedom (fin bending coupled with rudder and tab oscillations). Inasmuch as the spring was preloaded, the tab-spring system was a nonlinear one" (p. 1).
Date:
December 15, 1947
Creator:
Smith, N. H.; Clevenson, S. A. & Barmby, J. G.
System:
The UNT Digital Library
Yaw Characteristics and Sidewash Angles of a 42 Degree Sweptback Circular-Arc Wing With a Fuselage and With Leading-Edge and Split Flaps at a Reynolds Number of 5,300,000
Report presenting testing of the low-speed aerodynamic characteristics in yaw of a 42 degree sweptback wing of circular-arc airfoil sections in the pressure tunnel. The wing had an aspect ratio of 3.94, taper ratio of 0.625, and no dihedral or twist. Results regarding lateral-stability parameters of plain wing, effect of wing flaps on lateral-stability parameters, effect of fuselage on lateral-stability parameters, a comparison with the NACA 64(sub 1)-112 wing, characteristics in the extended yaw range, and airflow characteristics in the region of a vertical tail are provided.
Date:
December 10, 1947
Creator:
Salmi, Reino J. & Fitzpatrick, James E.
System:
The UNT Digital Library
Preliminary Results of a Flight Investigation to Determine the Effect of Negative Flap Deflection on High-Speed Longitudinal-Control Characteristics
Report presenting flight testing on two propeller-driven airplanes with wings of NACA 66-series and NACA 230-series airfoil sections to determine the effect of deflecting the landing flaps upward on the high-speed longitudinal-control characteristics.
Date:
December 16, 1947
Creator:
White, Maurice D.; Sadoff, Melvin; Clousing, Lawrence A. & Cooper, George E.
System:
The UNT Digital Library
Wind-tunnel investigation of horizontal tails 3: unswept and 35 degrees swept-back plan forms of aspect ratio 6
Report presenting the results of a wind-tunnel investigation of the low-speed aerodynamic characteristics of two semispan horizontal tails with unswept and 35 degree sweptback plan forms. Test results are provided for models with and without standard roughness on their leading edges and with sealed and unsealed radius-nose elevators. Results regarding effectiveness and hinge-moment parameters, static longitudinal stability, effect of standard roughness, and effect of removing the elevator nose seal are provided.
Date:
December 17, 1948
Creator:
Dods, Jules B., Jr.
System:
The UNT Digital Library
Summary of Results of Tumbling Investigations Made in the Langley 20-Foot Free-Spinning Tunnel on 14 Dynamic Models
Report presenting the tumbling characteristics of dynamic models of 14 airplane designs in the free-spinning tunnel for various loadings and configurations. Conventional airplanes were not found to tumble, but tailless and tail-first airplanes might depending on the amount of static longitudinal stability. Results regarding the effect of dimensional and mass characteristics, effect of controls, use of parachutes as a tumble-recovery device, accelerations, and possibility of pilot escape are provided.
Date:
December 31, 1948
Creator:
Stone, Ralph W., Jr. & Bryant, Robert L.
System:
The UNT Digital Library
Calculation of the Aerodynamic Loading of Flexible Wings of Arbitrary Plan Form and Stiffness
"A method is presented for calculating the aerodynamic loading, the divergence speed, and certain stability derivatives of wings and tail surfaces of arbitrary plan form and stiffness. Provision is made for using either stiffness curves and root-rotation constants or influence coefficients in the analysis. Computing forms, tables of numerical constants required in the analysis, and an illustrative example are included to facilitate calculations by means of the method" (p. 1).
Date:
December 24, 1948
Creator:
Diederich, Franklin W.
System:
The UNT Digital Library
Effect of wing sweep, taper, and thickness ratio on the transonic drag characteristics of wing-body combinations
Report presenting the transonic drag characteristics of a series of wing-body combinations and their component parts using the free-fall method. The configurations examined had wings of various sweeps and thickness ratios mounted on identical bodies of fineness ratio 12.
Date:
December 31, 1948
Creator:
Thompson, Jim Rogers & Mathews, Charles W.
System:
The UNT Digital Library