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Wind-tunnel investigation of control-surface characteristics 19: a double flap with an overhang and an internal aerodynamic balance
Report presenting wind-tunnel tests in two-dimensional flow to investigate the aerodynamic characteristics of a double flap with an internal and overhang balance. Three sizes of each type of balance were tested with three relative rates of deflection of the two flaps. Results regarding lift, hinge moment, drag, and pitching moment are provided.
Date:
June 1944
Creator:
Liddell, Robert B.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of Control-Surface Characteristics 22: Medium and Large Aerodynamic Balances of Two Nose Shapes and a Plain Overhang Used With a 0.20-Airfoil-Chord Flap on an NACA 0009 Airfoil
"Blunt-nose and elliptical-nose overhangs of 0.35 and 0.50 flap chord and a plain overhang on a flap having a chord of 0.20 airfoil chord have been tested in two-dimensional flow on an NACA 0009 airfoil. The results of the tests are presented as aerodynamic section characteristics for several flap deflections with the gap at the flap nose sealed or unsealed. Tests were made also to determine the effectiveness of a tab of 0.20 flap chord on the plain sealed flap and on a sealed flap having an elliptical overhang of 0.35 flap chord" (p. 1).
Date:
June 1945
Creator:
Riebe, John M. & McKinney, Elizabeth G.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of Effect of Yaw on Lateral-Stability Characteristics 5: Symmetrically Tapered Wing With a Circular Fuselage Having a Horizontal and a Vertical Tail
Report discussing testing to determine the effect of a horizontal tail on the lateral-stability characteristics of a high-wing, a midwing, and a low-wing monoplane. The model was created from a circular fuselage, an NACA 23012 tapered wing, and an NACA 0009 horizontal tail surface. Information about the effective aspect ratio of the tail, restoring moment of yaw, and vertical-tail effectiveness as compared to the wing position is provided.
Date:
June 1943
Creator:
Wallace, Arthur R. & Turner, Thomas R.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of Horizontal Tails 2: Unswept and 35 Degree Swept-Back Plan Forms of Aspect Ratio 4.5
Memorandum 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. The two models had an aspect ratio of 4.5, taper ratio of 0.5, and an NACA 64A010 airfoil section. Test results are presented with and without standard roughness applied to their leading edges and with sealed and unsealed radius-nose elevators.
Date:
June 3, 1948
Creator:
Dods, Jules B., Jr.
Object Type:
Report
System:
The UNT Digital Library
Wind-tunnel investigation of the aerodynamic characteristics in pitch of wing-fuselage combinations at high subsonic speeds: taper-ratio series
Report presenting a continuation of the program in the high-speed 7- by 10-foot tunnel to investigate the aerodynamic characteristics in pitch, sideslip, and steady roll of model configurations with variations in wing geometric parameters. This report contains the aerodynamic characteristics in pitch of wing-fuselage combinations with wings of aspect ratio 4, sweepback angle of 45 degrees, and three different taper ratios. Results regarding lift characteristics, pitching-moment characteristics, drag characteristics, and lift-drag ratio are provided.
Date:
June 30, 1953
Creator:
King, Thomas J., Jr. & Pasteur, Thomas B., Jr.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Boundary Layer and Wake and Their Relation to Airfoil Characteristics - NACA 65(Sub 1)-012 Airfoil With a True Contour Flap and a Beveled-Trailing-Edge Flap
Note presenting two-dimensional flow tests conduced in the 2.5-by 6-foot test section of the stability tunnel on an NACA 65(sub 1)-012 airfoil with a true contour flap and a beveled-trailing-edge flap to determine lift, drag, hinge moment, boundary layer, and wake characteristics. Measurements indicated that the static-pressure gradient through a boundary layer may be large in regions where the airfoil has a small radius of curvature and that a static-pressure rise exists at the vertical position of minimum wake velocity for a region just behind the trailing edge.
Date:
June 1947
Creator:
Mendelsohn, Robert A.
Object Type:
Report
System:
The UNT Digital Library
Wind-tunnel investigation of the effect of clipping the tips of triangular wings of different thickness, camber, and aspect ratio - transonic bump method
Report presenting an investigation on a transonic bump to determine the aerodynamic characteristics of a series of triangular wings. Four basic triangular-wing plan forms with different aspect ratios, taper ratios, and combinations of tip clipping were tested over a range of Mach and Reynolds numbers. Results regarding angle of attack, drag coefficient, pitching-moment coefficient with lift coefficient, and various curves are provided.
Date:
June 1956
Creator:
Emerson, Horace F.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Effect of Power and Flaps on the Static Lateral Characteristics of a Single-Engine Low-Wing Airplane Model
Tests were made in the Langley 7- by 10-foot tunnel to determine the lateral-stability characteristics with and without power of a model of a typical low-wing single-engine airplane with flaps neutral, with a full-span single slotted flap, and with a full-span double slotted flap. Power decreased the dihedral effect regardless of flap condition, and the double-slotted flap configuration showed the most marked decrease. The usual effect of power in increasing the directional stability was also shown.
Date:
June 1947
Creator:
Tamburello, Vito & Weil, Joseph
Object Type:
Report
System:
The UNT Digital Library
Wind-tunnel investigation of the effect of wing-tip fuel tanks on characteristics of unswept wings in steady roll
Report presenting testing to determine the effects of wing-tip fuel tanks on the rolling characteristics of unswept wings. The investigation included determination of the damping in roll, aileron effectiveness, and lateral maneuverability of a tapered and of a rectangular wing. Results regarding the effect of wing-tip fuel tanks on the damping-moment coefficient in roll and origin of the effect of wing-tip fuel tanks are also provided.
Date:
June 1947
Creator:
Murray, Harry E. & Wells, Evalyn G.
Object Type:
Report
System:
The UNT Digital Library
A Wind-Tunnel Investigation of the Use of Spoilers for Obtaining Static Longitudinal Stability of a Canard-Missile Model in Reverse Flight
Report presenting an investigation in the stability tunnel of the use of spoilers for obtaining static longitudinal stability of a model of a canard missile in reverse flight. Results indicated that stable pitching-moment slopes can be obtained at angles of attack up to 11 degrees in the low speed range of the tests, but further investigation of high subsonic speeds will be necessary.
Date:
June 21, 1954
Creator:
Fletcher, Herman S.
Object Type:
Report
System:
The UNT Digital Library
Wind-tunnel investigation of the vortex wake and downwash field behind triangular wings and wing-body combinations at supersonic speeds
Report presenting an investigation of the flow field behind triangular wings alone and in combination with a pointed cylindrical body at Mach numbers of 1.5 and 2.0 through an angle-of-attack range of 0 to 24 degrees. Results regarding the geometric characteristics of the vortex system and downwash characteristics are provided.
Date:
June 25, 1953
Creator:
Spahr, J. Richard & Dickey, Robert R.
Object Type:
Report
System:
The UNT Digital Library
Wind-tunnel investigation of transonic aileron flutter
Report presenting a partial-span wing tested to determine the cause of a flutter which had occurred in high-speed flight. Changes were made to the wing stiffness, location of the center of gravity of the wing, and the mass balance of the aileron. Results regarding the effect of wing changes on flutter, effect of aileron changes on flutter, shock-wave study, and static aerodynamic coefficients are provided.
Date:
June 9, 1949
Creator:
Erickson, Albert L. & Mannes, Robert L.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Research Comparing Lateral Control Devices, Particularly at High Angles of Attack 5: Spoilers and Ailerons on Rectangular Wings
"This report covers the fifth of a series of systematic investigations in which lateral control devices are compared with particular reference to their effectiveness at high angles of attack. The present report deals with tests of spoilers and ordinary ailerons on rectangular Clark Y wing models. In an effort to obtain satisfactory control throughout the entire angle-of-attack range that can be maintained in flight, various spoilers were tested in combination with two sizes of previously tested ordinary ailerons - one of average proportions and the other short and wide. In addition, one large spoiler was tested alone" (p. 719).
Date:
June 13, 1932
Creator:
Weick, Fred E. & Shortal, Joseph A.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Research Comparing Lateral Control Devices, Particularly at High Angles of Attack 12: Upper-Surface Ailerons on Wings With Split Flaps
"This report covers the twelfth of a series of tests conducted to compare different lateral control devices with particular reference to their effectiveness at high angles of attack. The present wind tunnel tests were made with two sizes of upper-surface ailerons on rectangular Clark Y wing models equipped with full span split flaps. The tests showed the effect of the upper-surface ailerons and of the split flaps on the general performance characteristics of the wings, and on the lateral controllability and stability characteristics" (p. 463).
Date:
June 8, 1934
Creator:
Weick, Fred E. & Wenzinger, Carl J.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Tests and Analysis of Two 10-Foot-Diameter Six-Blade Dual-Rotating Tractor Propeller Differing in Pitch Distribution
Report presenting an investigation to determine the efficiency at low tip speeds of two 10-foot-diameter six-blade dual-rotating propellers differing only in pitch distribution. Propeller forces were determined from wind tunnel testing and by using an analytical method using two-dimensional airfoil section data. Results regarding propeller characteristics, analysis of energy losses, and design considerations are provided.
Date:
June 1948
Creator:
Gilman, Jean, Jr.
Object Type:
Report
System:
The UNT Digital Library
Wind-tunnel tests of a 0.16-scale model of the X-3 airplane at high subsonic speeds : additional stability and control characteristics and the aerodynamic effects of external stores and ram jets
Report presenting additional wind-tunnel tests of a model of the X-3 airplane at low and high subsonic numbers to investigate the lateral and longitudinal-stability and control characteristics. Results regarding the aerodynamic characteristics in pitch and aerodynamic characteristics in yaw are provided.
Date:
June 13, 1950
Creator:
Cleary, Joseph W. & Mellenthin, Jack A.
Object Type:
Report
System:
The UNT Digital Library
Wind-tunnel tests of a 0.16-scale model of the X-3 airplane at high subsonic speeds: wing and fuselage pressure distribution
Report presenting measurements of wing and fuselage pressure distributions made at low and high subsonic Mach numbers on a scale model of the projected X-3 research airplane. Tests were conducted in pitch and yaw and included measurements of the total pressure in the fuselage boundary layer at the location of the left boundary-layer bleed scoop.
Date:
June 22, 1950
Creator:
Cleary, Joseph W. & Mellenthin, Jack A.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Tests of a 0.182-Scale Model of an F4U-1 Airplane with External Stores
Tests were made in the Langley 7- by 10-foot tunnel on a 0.182-scale model of an F4U-1 airplane with external stores. This paper is concerned mainly with presenting the data obtained in this investigation and with a comparison of some of these data with flight-test results determining the feasibility of estimating flight buffet Mach number from tunnel data. The results of this investigation indicate that the incremental drag coefficient due to external stores may be used to estimate the maximum Mach number that the F4U-1 airplane may reach in flight when it is equipped with external stores. This estimation is conservative for the five configurations investigated by mounts varying from 0 to 10 percent of the flight limit Mach number. The free-stream tunnel Mach number corresponding to sonic flow over the lower surface of the wing in the region of the store is a good indication of the lower limit of buffet in flight of the F4U-1 airplane when equipped with external stores. The fluctuations of total pressure over the horizontal tail are not sufficiently large (maximum of 1 percent q(sub o) to cause buffeting of the airplane.
Date:
June 5, 1947
Creator:
Silvers, H. Norman & Spreemann, Kenneth P.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Tests of a 1/6-Scale Model of Republic XF-12 Vertical Tail with Stub Fuselage and Stub Horizontal Tail
"A 1/6-scale model of the Republic XF-12 vertical tail with stub fuselage and stub horizontal tail was tested in the Langley stability tunnel to determine the aerodynamic characteristics of the model, The investigation included a study of the effects of boundary layer thickness, rudder area, and cover-plate alinement on the aerodynamic characteristics. Tuft studies were made in the vicinity of the junction of the vertical and stub horizontal tails" (p. 1).
Date:
June 2, 1945
Creator:
MacLachlan, Robert
Object Type:
Report
System:
The UNT Digital Library
Wind Tunnel Tests of Ailerons at Various Speeds 1: Ailerons of 0.20 Airfoil Chord and True Contour With 0.35 Aileron-Chord Extreme Blunt Nose Balance on the NACA 66,2-216 Airfoil
"Hinge-moment, lift, and pressure-distribution measurements were made in the two-dimensional test section of the NACA stability tunnel on a blunt-nose balance-type aileron on an NACA 66,2-216 airfoil at speeds up to 360 miles per hour corresponding to a Mach number of 0.475. The tests were made primarily to determine the effect of speed on the action of this type of aileron. The balance-nose radii of the aileron were varied from 0 to 0.02 of the airfoil chord and the gap width was varied from 0.0005 to 0.0107 of the airfoil chord. Tests were also made with the gap sealed" (p. 1).
Date:
June 1943
Creator:
Letko, W.; Denaci, H. G. & Freed, C.
Object Type:
Report
System:
The UNT Digital Library
Wind-tunnel tests of ailerons at various speeds 2: ailerons of 0.20 airfoil chord and true contour with 0.60 aileron-chord sealed internal balance on the NACA 66,2-216 airfoil
Report presenting hinge-moment, lift, pressure difference across the balance, and pressure-distribution measurements in the two-dimensional test section of the stability tunnel on a 0.60 aileron-chord sealed internal-balance aileron on a specified NACA airfoil. The primary test objective was to determine the effect of speed on the action of the aileron.
Date:
June 1943
Creator:
Denaci, H. G. & Bird, J. D.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Tests of Several Model Tractor-Propeller and Pusher-Propeller Wing Extension-Shaft Arrangements, Special Report
"Tests were made in the 20-foot propeller-research tunnel to investigate the possibility of obtaining increased net efficiencies of propeller-nacelle units by enclosing the engines in the wings and by using extension shafts. A wing of 5-foot chord was fitted with a propeller drive assembly providing for several axial locations of tractor propellers and pusher propellers. A three-blade 4-foot propeller and a three-blade 3 1/2-foot propeller of special design were tested in this wing with spinners and fairings ranging in diameter from 6 to 16 inches" (p. 1).
Date:
June 1941
Creator:
Harmon, Hubert N.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Tests of the 1/8-Scale Powered Model of the Curtiss XBTC-2 Airplane 1: Preliminary Investigation of Longitudinal Stability
Report presenting a series of wind-tunnel tests made in the 7- by 10-foot tunnel of the Curtiss XBTC-2 model with power. The object of the tests was to determine and to improve, as necessary, the complete aerodynamic characteristics of the model. The report includes the results of the longitudinal stability investigation of the original model along with results from tests of various modifications.
Date:
June 1944
Creator:
Weil, Joseph & Wells, Evalyn G.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Tests on Combinations of a Wing With Fixed Auxiliary Airfoils Having Various Chords and Profiles
This report presents the results of wind tunnel tests on various auxiliary airfoils having three different airfoil sections and several different chord lengths in combination with a Clark Y model wing in a sufficient number of relative positions to determine the optimum with regard to certain criterions of aerodynamic performance. The airfoil sections included a symmetrical profile, one of medium camber, and a highly cambered one. The chord sizes of the auxiliary airfoils ranged from 7.5 to 25 percent of the chord of the main wing, and the span was equal to that of the main wing.
Date:
June 10, 1933
Creator:
Weick, Fred E. & Sanders, Robert
Object Type:
Report
System:
The UNT Digital Library