National Advisory Committee for Aeronautics (NACA) - 13,806 Matching Results

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Maximum rates of control motion obtained from ground tests

Description: Report discusses the results of testing to determine the maximum rates of control stick (elevator) motion and corresponding maximum stick forces that could be exerted based on experiments with several pilots. The main topics explored were the comparison of the maximum rates of push and pull, maximum rates of push and pull when a mental restriction was placed on the pilot, and maximum rates at which the pilot though he would apply the elevator control forces versus the actual application of forces. Information about experimental procedures and the rig the testing occurred on is included.
Date: May 1944
Creator: Beeler, De E.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of control-surface characteristics [part] 16: pressure distribution over an NACA 0009 airfoil with 0.30-airfoil-chord beveled-trailing-edge flaps

Description: Report discusses pressure-distribution tests of a plain flap with interchangeable beveled trailing edges on an NACA 0009 airfoil. From Summary: "The flap chord was 30 percent of the airfoil chord and the bevel chords were 15 and 20 percent of the flap chord. The purpose of these tests was to supply pressure-distribution data that may be used for structural and aerodynamic design of horizontal and vertical tail surfaces."
Date: April 1944
Creator: Hoggard, H. Page, Jr. & Bulloch, Marjorie E.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation at low speed of sideslipping, rolling, yawing, and pitching characteristics for a model of a 45 degree swept-wing fighter-type airplane

Description: Report presenting an investigation in the stability tunnel at low speed to determine the rolling characteristics at combined angles of attack and sideslip for a model of a fighter-type airplane with a 45 degree sweptback wing. Testing was performed with the original vertical tail and a vertical tail with a 27 percent larger exposed area. Results regarding the static longitudinal stability, directional stability, and effect of the different tails are presented.
Date: September 1, 1955
Creator: Jaquet, Byron M. & Fletcher, H. S.
Partner: UNT Libraries Government Documents Department

An experimental investigation of the flow phenomena over bodies at high angles of attack at a Mach number of 2.01

Description: Report presenting an investigation in the supersonic pressure tunnel at Mach number 2.01 to study the wake patterns in the lee of bodies at high angles of attack. The configurations tested consisted of two cylindrical body shapes, one circular and one elliptical in cross section, with a fineness-ratio-3.5 ogival nose and a fineness-ratio-6 conical nose. Results regarding vapor-screen photographs, wake characteristics, wake patterns, wake characteristics, and testing with transition strips are included.
Date: October 27, 1955
Creator: Gapcynski, John P.
Partner: UNT Libraries Government Documents Department

Some effects of propeller operation on the distribution of the load on the vertical tail surface of a typical pursuit airplane

Description: Report discusses the results of testing on the pressure distribution at several longitudinal sections of the vertical tail surface of the Curtiss P-40K airplane at various angles of attack and angles of yaw and with the propeller removed and propeller operating. Results regarding the chordwise pressure distributions, effects of propeller operation on the spanwise distribution of normal-force coefficient, total normal-force coefficients, and effect of propeller operation on the variation of vertical-tail normal-force coefficients are presented.
Date: March 1944
Creator: Sweberg, Harold H. & Dingeldein, Richard C.
Partner: UNT Libraries Government Documents Department

Some flight measurements on pressure distribution during tail buffeting

Description: Report presenting pressure-distribution measurements obtained from the horizontal tail surfaces of the Curtiss P-40K airplane during low-speed pull-ups to abrupt stall in which tail buffeting was experienced. The chordwise load distributions during buffeting are similar to those experienced during angle-of-attack changes. The location of the stall and frequency of stall disturbances are also described.
Date: October 1945
Creator: Boshar, John
Partner: UNT Libraries Government Documents Department

Modified tubular combustor as high-temperature gas generators

Description: A pair of combustors and transition liners in a quarter-annular, direct-connect assembly was operated at temperatures up to 2400 degrees F to determine the feasibility of using production-type combustor systems as high-tmeperature gas generators for turbine-cooling studies. Operation at high temperatures for 32 hours was possible when minor liner modifications were made that provided greater cooling-air flow between the turbine casing and interior components.
Date: October 21, 1955
Creator: Friedman, Robert & Zettle, Eugene V
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of rounded horns and of guards on a horizontal tail surface

Description: Report discussing an investigation of the aerodynamic effects of horn balances with various plan forms and of guards on a horizontal tail surface. Rounding the adjacent horn and stabilizer edges causes negligible changes to aerodynamic effects except for the area moment of the horn. A solid horn guard mounted on the end of the stabilizer was found to increase the rate of change of lift with angle of attack and elevator deflection.
Date: October 1944
Creator: Liddell, Robert B. & Lockwood, Vernard E.
Partner: UNT Libraries Government Documents Department