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Measurements of the pressure distribution on the horizontal-tail surface of a typical propeller-driven pursuit airplane in flight III: tail loads in abrupt pull-up push-down maneuvers

Description: Results regarding the total horizontal-tail load and the root bending-moment increments calculated by use of existing rational procedures compared with the experimental values obtained in pull-up push-down maneuvers on a propeller-driven pursuit-type airplane for six combinations of power, indicated airspeed, and pressure altitude.
Date: February 1948
Creator: Sadoff, Melvin & Clousing, Lawrence A.
Partner: UNT Libraries Government Documents Department

Longitudinal-stability characteristics of the Northrop X-4 airplane (USAF No. 46-677)

Description: Report presenting the results from several recent flights on the Northrop X-4 No. 2 airplane, including the longitudinal stability characteristics over a range of Mach numbers in straight and accelerated flight and the short-period longitudinal-oscillation characteristics.
Date: June 29, 1950
Creator: Sadoff, Melvin & Sisk, Thomas R.
Partner: UNT Libraries Government Documents Department

Measurements of the pressure distribution on the horizontal tail surface of a typical propeller-driven pursuit airplane in flight II: the effect of angle of sideslip and propeller operation

Description: Report presenting measurements in sideslipping flight of the pressure distribution over the horizontal tail surface of a tractor-propeller-driven pursuit airplane to determine the effects of angle of sideslip and propeller operation on the tail-load distribution. Results regarding the reduction of data, effect of sideslip and power on tail loads, effect of sideslip and power on tail moments, and a comparison of the calculated loading with experimental results.
Date: May 1947
Creator: Sadoff, Melvin & Clousing, Lawrence A.
Partner: UNT Libraries Government Documents Department

Summary report of results obtained during demonstration tests of the Northrop X-4 airplanes

Description: Report presenting results during demonstration flight tests of the Northrop X-4 No. 1 and No. 2 airplanes. Results regarding the static and dynamic longitudinal- and lateral-stability characteristics, the stalling characteristics, and the buffet boundary.
Date: December 13, 1950
Creator: Sadoff, Melvin & Sisk, Thomas R.
Partner: UNT Libraries Government Documents Department

Stall Characteristics Obtained from Flight 10 of Northrop X-4 No. 2 Airplane (USAF No. 46-677)

Description: NACA instrumentation has been installed in the X-4 airplanes to obtain stability and control data during the acceptance tests conducted by the Northrop Aircraft Corporation. This report presents data obtained on the stalling characteristics of the airplane in the clean and gear- down configurations. The center of gravity was located at approximately 18 percent of the mean aerodynamic chord during the tests. The results indicated that the airplane was not completely stalled when stall was gradually approached during nominally U accelerated flight but that it was completely stalled during a more abruptly approached stall in accelerated flight. The stall in accelerated flight was relatively mild, and this was attributed to the nature of the variation of lift with angle of attack for the 001-614 airfoil section, the plan form of the wing, and to the fact that the initial sideslip at the stall produced (as shown by wind-tunnel tests of a model of the airplane) a more symmetrical stall pattern.
Date: February 27, 1950
Creator: Sadoff, Melvin & Sisk, Thomas R.
Partner: UNT Libraries Government Documents Department

Measurements of the pressure distribution on the horizontal-tail surface of a typical propeller-driven pursuit airplane in flight I: effects of compressibility in steady straight and accelerated flight

Description: Report presenting pressure-distribution measurements made in steady straight and accelerated flight over a horizontal tail surface of a typical pursuit airplane. Results regarding the variation of horizontal-tail loads with Mach number, variation of root bending moments and fuselage torsional moments with Mach number, and variation of section loads with Mach number are provided.
Date: July 1947
Creator: Sadoff, Melvin; Turner, William N. & Clousing, Lawrence A.
Partner: UNT Libraries Government Documents Department

Preliminary results of a flight investigation to determine the effect of negative flap deflection on high-speed longitudinal-control characteristics

Description: Report presenting flight testing on two propeller-driven airplanes with wings of NACA 66-series and NACA 230-series airfoil sections to determine the effect of deflecting the landing flaps upward on the high-speed longitudinal-control characteristics.
Date: December 16, 1947
Creator: White, Maurice D.; Sadoff, Melvin; Clousing, Lawrence A. & Cooper, George E.
Partner: UNT Libraries Government Documents Department

Analytical study of the comparative pitch-up behavior of several airplanes and correlation with pilot opinion

Description: From Introduction: "An extension of the work presented in reference 2, the method was applied to six swept-wing airplanes for which the pilot opinion was well documented. The analytical results obtained are used herein to illustrate how wind-tunnel data may be used to predict the pitching motions and the comparative pitch-up behavior of new airplane designs or to assess the effects of modifications on existing airplanes."
Date: June 12, 1957
Creator: Sadoff, Melvin; Stewart, John D & Cooper, George E
Partner: UNT Libraries Government Documents Department

Flight investigation of the longitudinal stability and control characteristics of the Douglas D-558-I airplane (BuAero No. 37972) at Mach numbers up to 0.89

Description: Report presenting results and analysis of the longitudinal stability and control characteristics of the Douglas D-558-I airplane at a range of altitudes and Mach numbers. It was found that large and rapid changes in elevator deflection and force were required for balance at Mach numbers above 0.84 due to a sharp decrease in elevator-stabilizer effectiveness.
Date: June 25, 1951
Creator: Sadoff, Melvin; Roden, William S. & Eggleston, John M.
Partner: UNT Libraries Government Documents Department

A method for evaluating the loads and controllability aspects of the pitch-up problem

Description: Report presenting a procedure for estimating the range of peak airplane load factors and maneuvering tail loads likely to be experienced in pitch-up maneuvers. Results of computations indicated that though the load factors and maneuvering tail loads were not critical in pitch-up maneuvers at 35,000 feet, they were likely to exceed design levels at 15,200 feet.
Date: August 23, 1955
Creator: Sadoff, Melvin; Matteson, Frederick H. & Havill, C. Dewey
Partner: UNT Libraries Government Documents Department

The Effect of Blunt-Trailing-Edge Modifications on the High-Speed Stability and Control Characteristics of a Swept-Wing Fighter Airplane

Description: An investigation was conducted on a 35 deg swept-wing fighter airplane to determine the effects of several blunt-trailing-edge modifications to the wing and tail on the high-speed stability and control characteristics and tracking performance. The results indicated significant improvement in the pitch-up characteristics for the blunt-aileron configuration at Mach numbers around 0.90. As a result of increased effectiveness of the blunt-trailing-edge aileron, the roll-off, customarily experienced with the unmodified airplane in wings-level flight between Mach numbers of about 0.9 and 1.0 was eliminated, The results also indicated that the increased effectiveness of the blunt aileron more than offset the large associated aileron hinge moment, resulting in significant improvement in the rolling performance at Mach numbers between 0.85 and 1.0. It appeared from these results that the tracking performance with the blunt-aileron configuration in the pitch-up and buffeting flight region at high Mach numbers was considerably improved over that of the unmodified airplane; however, the tracking errors of 8 to 15 mils were definitely unsatisfactory. A drag increment of about O.OOl5 due to the blunt ailerons was noted at Mach numbers to about 0.85. The drag increment was 0 at Mach numbers above 0.90.
Date: May 26, 1954
Creator: Sadoff, Melvin; Matteson, Frederick H. & Van Dyke, Rudolph D., Jr.
Partner: UNT Libraries Government Documents Department