Report presenting an investigation of the effect of wing-tip mounted tanks on the rolling characteristics of a wing, aspect ratio 3 with the quarter-chord line swept back 35 degrees, through a range of Mach numbers and angles of attack using the free-roll method.

Report presenting the lift, drag, and pitching-moment characteristics of a wing-fuselage combination employing a wing with the leading edge swept back 63 degrees and cambered and twisted for a uniform load at a lift coefficient of 0.25 and Mach number 1.53. The experimental results are compared to those from other investigations. A maximum lift-drag ratio of 8.9 and a minimum drag coefficient of 0.0145 was obtained.

Memorandum presenting an investigation of the drag and pressure distribution on a body of revolution of fineness ratio 12 as measured by the free-fall method. Analysis of the results has provided knowledge of the mechanism of the abrupt drag rise which occurs near the speed of sound, and demonstrates that the theoretical method described in a previous report satisfactorily predicts the shape of the measured pressure distributions at low supersonic speeds.

The first report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for eleven radial stations of the NACA 10-(3)(066)-033 propeller.

Report presenting a wind-tunnel investigation at low speed to determine the lateral control characteristics of a 51.3 degree sweptback-wing model equipped with either plain or stepped spoiler ailerons with a fixed projection of 5-percent-wing chord and various spans and spanwise locations. The results indicated that spanwise rolling-effectiveness charts of flap-type ailerons can not be used to predict effectiveness of spoiler-type ailerons on swept wings. Results regarding the wing aerodynamic characteristics with spoiler ailerons retracted, wing aerodynamic characteristics with spoiler ailerons projected, and a comparison of spoiler-type and flap-type ailerons.

Report presenting an investigation of the pressure distribution on the full-span droop-nose flap of a wing with the leading edge swept back 47.5 degrees and symmetrical circular-arc airfoil sections. Flap pressure distributions were obtained for the base configuration and various deflections of the full-span droop-nose flap and other flap deflection combinations. Information regarding the flow and section characteristics, spanwise loading parameters, center-of-pressure variation, and flap normal-force and hinge-moment coefficients is provided.

The third investigation in a series to determine the fundamental characteristics of trailing-edge controls at transonic speeds. This particular report uses a 35 degree sweptback untapered airfoil model with an aspect ratio of 3 and a flap with a bevelled trailing edge with a trailing-edge angle of 23 degrees. Results regarding lift, pitching-moment, and hinge-moment characteristics are provided.

Memorandum presenting an investigation of the effect of skewed plain nose flaps on a thin, low-aspect-ratio triangular wing in combination with a high fineness-ratio fuselage conducted at low speeds and high Reynolds numbers. The plan form of the flaps was such that the flap chord varied from zero percent of the wing chord at the model center line to 100 percent at about 91-percent wing semispan. The results indicated that the nose flaps provided a significant delay in the occurrence of both the leading-edge type of separation and tip stalling.

Report presenting testing using a Northrop X-4 to obtain stability and control data during airplane acceptance tests. The data includes a time history of a complete pull-up, time histories of several level and accelerated flight runs, and the effect of dive-brake extension on the longitudinal and lateral trim.

Report presenting an investigation of various external-store configurations on a model of a tailless airplane with a sweptback wing over a range of Mach numbers. The investigation was performed out of a desire to reduce the drag interference caused by external stores as much as possible. Results regarding the aerodynamic characteristics in pitch, lift-drag ratios, effect of Mach number, variation of control effectiveness, aerodynamic characteristics in yaw, and variation of stability parameters are provided.

Report presenting an investigation of the pressure distribution over a rectangular wing with a 9-percent-thick symmetrical circular-arc section and a 30-percent-chord trailing-edge flap. Results are given for pressure distributions, Schileren and liquid-film studies, and wing section characteristics are provided.

"Wind-tunnel tests were conducted to determine the longitudinal stability characteristics of a full-scale Northrop XSSM-A-3 missile. Various wing modifications were investigated in an effort to provide a configuration that would maintain longitudinal stability to lift coefficients necessary for landing the missile during flight tests. The results of the tests led to the choice of a wing with an increased leading-edge radius" (p. 1).

"An investigation has been made in the Langley gust tunnel with two identical airplane models approximating 1/40-scale models of the B-29, coupled in tandem with a boom so that the individual centers of gravity were equidistant from the single coupling joint at the tail of the lead airplane. Time histories of the boom joint load were obtained as the models were flown through a gust. The results indicate that on a similar configuration involving airplanes the size of B-29 airplanes a load on the boom joint of 10,000 to 14,000 pounds could be induced by encountering a gust of 50 feet per second and having a gradient distance of 17 chords, at a forward speed of 380 feet per second and that the total load is extremely sensitive to the steadiness of flight that can be maintained with or without a gust" (p. 1).

The data obtained from the flight of a simplified (dummy) rocket-propelled model of the MX-656 have been analyzed to determine the booster-model characteristics and the model-alone characteristics up to a Mach number of 1.3. The data indicate that the model-booster combination is satisfactory. The model alone is longitudinally stable i n the Mach number range covered by the test (0.9 to 1.3) with the center of gravity at -15 percent of the mean aerodynamic chord. With the stabilizer setting at 0 deg. the variation of normal-force coefficient with Mach number is not large. The total-drag-coefficient variation with Mach number is not unusual. About 12 percent of the total drag at a Mach number of 1.3 can be attributed to body base drag.