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368
Wind-tunnel investigation of an N.A.C.A. 23012 airfoil with two arrangements of a wide-chord slotted flap
"An investigation has been made in the N.A.C.A. 7- by 10-foot wind tunnel of a large-chord N.A.C.A. 23012 airfoil with several arrangements of a 40-percent-chord slotted flap to determine the section aerodynamic characteristics of the airfoil as affected by slot shape, flap location, and flap deflection. The flap positions for maximum lift, the polar for arrangements considered favorable for take-off and climb, and the complete section aerodynamic characteristics for selected optimum arrangements were determined. A discussion is given of the relative merits of the various arrangements" (p. 1).
Date:
June 1939
Creator:
Harris, Thomas A.
System:
The UNT Digital Library
Wind-tunnel investigation of boundary-layer control by suction on NACA 655-424 airfoil with double slotted flap
Report presenting an investigation at a range of Reynolds numbers in the two-dimensional low-turbulence tunnels to determine the effectiveness of boundary-layer control by suction and of suction-slot location in increasing the maximum lift and decreasing the drag of a NACA 65(sub 5)-424 airfoil equipped with a double slotted flap. Results regarding the determination of slot configurations, lift, and drag and lift-drag ratio are provided.
Date:
June 1948
Creator:
Racisz, Stanley F. & Quinn, John H., Jr.
System:
The UNT Digital Library
Wind-Tunnel Investigation of Boundary-Layer Control by Suction on the NACA 653-418, a = 1.0 Airfoil Section with a 0.29-Airfoil-Chord Double Slotted Flap
Note presenting tests to find the maximum lift of the NACA 65(sub 3)-418 airfoil section equipped with a 0.29-airfoil-chord double slotted flap and a boundary-layer suction slot located at 0.45 airfoil chord. Results regarding lift characteristics, drag characteristics, and boundary layer and related characteristics are provided.
Date:
June 1946
Creator:
Quinn, John H., Jr.
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.
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.
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
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.
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.
System:
The UNT Digital Library