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Wind-Tunnel and Flight Tests of Slot-Lip Ailerons

Description: "The slot-lip ailerons developed by the NACA consist of a flap-type spoiler with an adjoining continuously open slot. The ailerons were developed in an investigation of the delayed response, or lag, of spoiler-type lateral controls. This report presents the results of tests of these slot-lip ailerons made on wing models in the 7 by 10-foot wind tunnel, on a Fairchild 22 airplane in the full-scale wind tunnel and in flight, and on the Weick W1-A airplane in flight" (p. 537).
Date: June 11, 1937
Creator: Shortal, Joseph A.
Partner: UNT Libraries Government Documents Department

Effect of Tip Shape and Dihedral on Lateral-Stability Characteristics

Description: This report presents the results of wind tunnel tests to determine the effect of wing-tip shape and dihedral on some of the aerodynamic characteristics of Clark Y wings that affect the performance and lateral stability of airplanes. Force tests at several angles of yaw and rotation tests at zero yaw were made. From these tests the rates of change of rolling moment, yawing moment, and cross-wind force coefficients with angle of yaw and the rate of change of rolling moment coefficient with rolling were determined.
Date: August 27, 1935
Creator: Shortal, Joseph A.
Partner: UNT Libraries Government Documents Department

The aerodynamic characteristics of a slotted Clark y wing as affected by the auxiliary airfoil position

Description: From Summary: "Aerodynamic force tests on a slotted Clark Y wing were conducted in a vertical wind tunnel to determine the best position for a given auxiliary airfoil with respect to the main wing. A systematic series of 100 changes in location of the auxiliary airfoil were made to cover all the probable useful ranges of slot gap, slot width, and slot depth. The results of the investigation may be applied to the design of automatic or controlled slots on wings with geometric characteristics similar to the wing tested. The best positions of the auxiliary airfoil were covered by the range of the tests, and the position for desired aerodynamic characteristics may easily be obtained from charts prepared especially for the purpose."
Date: 1932~
Creator: Wenzinger, Carl J. & Shortal, Joseph A.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of wings with ordinary ailerons and full-span external-airfoil flaps

Description: Report presents an investigation carried out in the NACA 7- by 10-foot wind tunnel of an NACA 23012 airfoil equipped, first, with a full-span NACA 23012 external-airfoil flap having a chord 0.20 of the main airfoil chord and with a full-span aileron with a chord 0.12 of the main airfoil chord on the trailing edge of the main airfoil and equipped second, with a 0.30-chord full-span NACA 23012 external-airfoil flap and a 0.13-chord full-span aileron. The results are arranged in three groups, the first two of which deal with the airfoil characteristics of the two airfoil-flap combinations and with the internal-control characteristics of the airfoil-flap-aileron combinations. The third group of tests deals with several means for balancing ailerons mounted on a special large-chord NACA 23012 external-airfoil flap. The tests included an ordinary aileron, a curtained-nose balance, a frise balance, and a tab.
Date: March 12, 1937
Creator: Platt, Robert C. & Shortal, Joseph A.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Research Comparing Lateral Control Devices, Particularly at High Angles of Attack 5: Spoilers and Ailerons on Rectangular Wings

Description: "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.
Partner: UNT Libraries Government Documents Department

Development of the N.A.C.A. Slot-Lip Aileron

Description: "An investigation of the undesirable delayed action, or lag, of the spoiler-type lateral control device led to the development of the NACA slot-lip aileron. The tests were made in the 7- by 10-foot wind tunnel with a 4- by 8-foot wing hinged at the tunnel jet boundary and restrained in roll by elastic cords. Time histories were taken of the motion of the control device under test and of the resulting wing motion" (p. 1).
Date: November 1935
Creator: Weick, Fred E. & Shortal, Joseph A.
Partner: UNT Libraries Government Documents Department

The Effect of Multiple Fixed Slots and a Trailing-Edge Flap on the Lift and Drag of a Clark Y Airfoil

Description: "Lift and drag tests were made on a Clark Y wing equipped with four fixed slots and a trailing-edge flap in the 5-foot vertical wind tunnel of the National Advisory Committee for Aeronautics. All possible combinations of the four slots were tested with the flap neutral and the most promising combinations were tested with the flap down 45 degrees. Considering both the maximum lift coefficient and the speed-range ratio with the flap neutral no appreciable improvement was found with the use of more than the single leading-edge slot" (p. 3).
Date: 1932
Creator: Weick, Fred E. & Shortal, Joseph A.
Partner: UNT Libraries Government Documents Department

Preliminary Stability and Control Tests in the NACA Free-Flight Wind Tunnel and Correlation With Full-Scale Flight Tests

Description: Note presenting a study of stability and control of airplanes by means of dynamic scale models in the 12-foot free-flight wind tunnel. Tests of a scale model of the F-36A airplane were used to develop the testing technique and to afford a comparison of tests of a model in the tunnel with flight tests of the corresponding airplane. Results regarding longitudinal stability and control and lateral stability and control are provided.
Date: June 1941
Creator: Shortal, Joseph A. & Osterhout, Clayton J.
Partner: UNT Libraries Government Documents Department

Wind Tunnel Research Comparing Lateral Control Devices, Particularly at High Angles of Attack 8: Straight and Skewed Ailerons on Wings With Rounded Tips

Description: Tests showed the effect of the ailerons and the tip shapes on the general performance of the wing, as well as on the lateral control and stability characteristics. The hinge moments were not measured but the approximate values are given in the first report of the series.
Date: February 1933
Creator: Weick, Fred E. & Shortal, Joseph A.
Partner: UNT Libraries Government Documents Department

Effect of Sweepback and Aspect Ratio on Longitudinal Stability Characteristics of Wings at Low Speeds

Description: Note presenting an analysis of the available data on the longitudinal stability characteristics of sweptback wings at low speeds. The analysis indicated that the shape of the pitching-moment curve near the stall for sweptback wings is greatly dependent on the aspect ratio. The addition of a horizontal tail behind the wings may be destabilizing and requires further investigation.
Date: July 1946
Creator: Shortal, Joseph A. & Maggin, Bernard
Partner: UNT Libraries Government Documents Department