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  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Serial/Series Title: NACA Technical Reports
 Collection: Technical Report Archive and Image Library
Wind-tunnel tests of a 10-foot-diameter gyroplane rotor

Wind-tunnel tests of a 10-foot-diameter gyroplane rotor

Date: January 1, 1936
Creator: Wheatley, John B
Description: This report presents the results of wind-tunnel tests on a model gyroplane rotor 10 feet in diameter. The rotor blades had zero sweepback and zero offset; the hub contained a feathering mechanism that provided control of the rotor rolling moment, but not of the pitching moment. The rotor was tested with 4 blades and with 2 blades. The entire useful range of pitch settings and tip-speed ratios was investigated including the phase of operation in which the rotor turned very slowly, or idled.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of a Clark Y wing with a narrow auxiliary airfoil in different positions

Wind-tunnel tests of a Clark Y wing with a narrow auxiliary airfoil in different positions

Date: January 1, 1933
Creator: Weick, Fred E
Description: Aerodynamic force tests were made on a combination of a Clark Y wing and a narrow auxiliary airfoil to find the best location of the auxiliary airfoil with respect to the main wing. The auxiliary was a highly cambered airfoil of medium thickness having a chord 14.5 per cent that of the main wing. It was tested in 141 different positions ahead of, above, and behind the nose portion of the main wing, the range of the test points being extended until the best aerodynamic conditions were covered. A range of positions was found in which the combination of main wing and auxiliary gave substantially greater aerodynamic efficiency and higher maximum lift coefficients (based on total area) than the main Clark Y wing alone. In the optimum position tested, considering both the maximum lift and the speed-range ratio, the combination of main wing and auxiliary gave an increase in the maximum lift coefficient of 32 per cent together with an increase in the ratio of 21 per cent of the respective values for the main Clark Y wing alone.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests on a series of wing models through a large angle of attack range. Part I : force tests

Wind-tunnel tests on a series of wing models through a large angle of attack range. Part I : force tests

Date: January 1, 1930
Creator: Knight, Montgomery
Description: This investigation covers force tests through a large range of angle of attack on a series of monoplane and biplane wing models. The tests were conducted in the atmospheric wind tunnel of the National Advisory Committee for Aeronautics. The models were arranged in such a manner as to make possible a determination of the effects of variations in tip shape, aspect ratio, flap setting, stagger, gap, decalage, sweep back, and airfoil profile. The arrangements represented most of the types of wing systems in use on modern airplanes. The effect of each variable is illustrated by means of groups of curves. In addition, there are included approximate autorotational characteristics in the form of calculated ranges of "rotary instability." a correction for blocking in this tunnel which applies to monoplanes at large angles of attack has been developed, and is given in an appendix. (author).
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Wind-tunnel tests on airfoil boundary layer control using a backward-opening slot

Wind-tunnel tests on airfoil boundary layer control using a backward-opening slot

Date: January 1, 1932
Creator: Bamber, Millard J
Description: This report presents the results of an investigation to determine the effect of boundary layer control on the lift and drag of an airfoil. Boundary layer control was accomplished by means of a backward-opening slot in the upper surface of the hollow airfoil. Air was caused to flow through this slot by a pressure which was maintained inside the airfoil by a blower. Various slot locations, slot openings, and wing pressures were used. The tests were conducted in the 5-foot atmospheric wind tunnel of the Langley Memorial Aeronautical Laboratory. Under the test conditions, the maximum lift coefficient was increased about 96 per cent for one slot arrangement, and the minimum drag coefficient was decreased about 27 per cent for another, both being compared with the results obtained with the unslotted airfoil. It is believed from this investigation that the above effects may be increased by the use of larger slot openings, better slot locations, multiple slots, improved airfoil profiles, and trailing edge flaps.
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Wind-tunnel tests on combinations of a wing with fixed auxiliary airfoils having various chords and profiles

Wind-tunnel tests on combinations of a wing with fixed auxiliary airfoils having various chords and profiles

Date: January 1, 1934
Creator: Weick, Fred E
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
Wing characteristics as affected by protuberances of short span

Wing characteristics as affected by protuberances of short span

Date: January 1, 1934
Creator: Jacobs, Eastman N
Description: The drag and interference caused by short-span protuberances from the surface of an airfoil have been investigated in the NACA variable-density wind tunnel at a Reynolds number of approximately 3,100,000, based on the chord length of the airfoil. The effects of variations of protuberance span length, span position, and shape were measured by determining how the wing characteristics were affected by the addition of the various protuberances.
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Wing-fuselage interference, tail buffeting, and air flow about the tail of a low-wing monoplane

Wing-fuselage interference, tail buffeting, and air flow about the tail of a low-wing monoplane

Date: January 1, 1935
Creator: White, James A
Description: This report presents the results of wind tunnel tests on a Mcdonnell Douglas airplane to determine the wing-fuselage interference of a low-wing monoplane. The tests included a study of tail buffeting and the air flow in the region of the tail. The airplane was tested with and without the propeller slipstream, both in the original condition and with several devices designed to reduce or eliminate tail buffeting. The devices used were wing-fuselage fillets, a NACA cowling, reflexed trailing edge of the wing, and stub auxiliary airfoils.
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Wing-nacelle-propeller interference for wings of various spans force and pressure-distribution tests

Wing-nacelle-propeller interference for wings of various spans force and pressure-distribution tests

Date: January 1, 1937
Creator: Robinson, Russell G
Description: Report presents the results of an experimental investigation made in the NACA full-scale wind tunnel to determine the effect of wing span on nacelle-propeller characteristics and, reciprocally, the lateral extent of nacelle and propeller influence on a monoplane wing. The results provide a check on the validity of the previous research on nacelles and propellers with 15-foot-span wings tested in the 20-foot wind tunnel and reported in technical reports 415, 462, 505, 506, and 507.
Contributing Partner: UNT Libraries Government Documents Department
Wing pressure distribution and rotor-blade motion of an autogiro as determined in flight

Wing pressure distribution and rotor-blade motion of an autogiro as determined in flight

Date: January 1, 1935
Creator: Wheatley, John B
Description: This report presents the results of tests in which the pressure distribution over the fixed wing of an autogiro was determined in both steady and accelerated flight. In the steady-flight condition, the rotor-blade motion was also measured. These data show that in steady flight the rotor speed as a function of the air speed is largely affected by the variation of the division of load between the rotor and the wing; as the load on the wing increases, the rotor speed decreases. In steady flight the presence of the slipstream increased both the wing lift at a given air speed and the maximum lift coefficient of the wing above the corresponding values without the slipstream. In abrupt high-speed turns, the wing attained a normal force coefficient of unity at almost the initial value of the air speed and experienced its maximum load before maximum acceleration occurred.
Contributing Partner: UNT Libraries Government Documents Department
Working charts for the determination of propeller thrust at various air speeds

Working charts for the determination of propeller thrust at various air speeds

Date: January 1, 1935
Creator: Hartman, Edwin P
Description: A set of propeller performance charts, based on a torque speed coefficient has been constructed from full-sized metal propeller data obtained in the NACA propeller-research tunnel.
Contributing Partner: UNT Libraries Government Documents Department