Memorandum presenting measurements of the dielectric constant for suspensions of two types of boron powder in mineral oil as a function of concentration of boron particles, moisture content, temperature, and frequency of oscillation. Also investigated were the effects of boron-powder concentration and moisture content on the dielectric losses of mineral-oil suspensions of the two boron powders.

The variation of dielectric constant has been measured as a function of the concentration of magnesium particles; the shape, size, and degree of oxidation of the particles; the temperature; and the frequency of oscillation. The variation of dielectric constant and settling rate was investigated as a function of time. Also investigated were the effects of particle concentration, shape and time on dielectric losses.

Report presenting the use of Von Karman's two-dimensional transonic similarity law as applied to drag data of three different thickness wings with NACA 65-series sections and aspect ratios of 7.6 over a range of Mach numbers. The correlation was found to be satisfactory, with results better in the subsonic range than in the supersonic range.

Report presenting pressure distributions of three triangular wing models: a wing-alone model, the same wing combined with a body, and a mock-up of a triangular-wing airplane. Results regarding the separation-vortex air flow over triangular wings, general comments regarding the applicability of the study, chordwise pressure distribution, section lift characteristics, center of pressure, and span load distribution are provided.

Report presenting an investigation of the low-speed characteristics of a 25-foot span triangular wing with an aspect ratio of 2. the airfoil section of the wing was a symmetrical double wedge with 5-percent maximum thickness at 20-percent chord. Results regarding the longitudinal characteristics, lateral characteristics, and directional characteristics are provided.

Report presenting a study of the characteristics of a large-scale triangular wing to include the effects of section modifications. The wing in this report is the same as the one in the previous report but features various degrees of rounding of the wing leading edge and wing maximum thickness rather than having sharp edges. Results regarding the effects of airfoil section modifications, visible trailing vortices, and surveys in the extended chord plane are provided.

Report presenting an investigation to determine the aerodynamic characteristics in sideslip of a triangular wing of aspect ratio 2.04 in combination with a body of fineness ratio 12.5 and a vertical tail surface. The body combined with the triangular plan-form wing caused no significant changes in the lift characteristics of the wing and only a 1-percent decrease in the static margin. Results regarding the longitudinal characteristics, lateral and directional characteristics, and estimation of tail and rudder effectiveness are provided.

Memorandum presenting a study to determine locations of pressure sensors for controlling the spike position of a blunt-lip, axisymmetric inlet with internal contraction. The inlet performance was determined at Mach numbers of 0.63 and 1.5 to 2.0 for airflow schedules corresponding to those of a given turbojet engine over a wide range of ambient temperatures. The use of the ratio of a throat static pressure to either a local total or the spike-tip total pressure provided a signal that could set nearly maximum pressure recoveries at Mach numbers of 1.7 to 2.0 and within 6 percent of maximum recovery at Mach 1.5.

"Investigation of the control parameters of an external-internal compression inlet indicates that the cowl-lip shock provides a signal to position the spike and to start the inlet over a Mach number range from 2.1 to 3.0. Use of a single fixed probe position to control the spike over the range of conditions resulted in a 3.7-count loss in total-pressure recovery at Mach 3.0 and 0 deg angle of attack. Three separate shock-sensing-probe positions were required to set the spike for peak recovery from Mach 2.1 to 3.0 and angles of attack from 0 deg to 6 deg" (p. 1).

"This report presents the results of wind-tunnel tests of a 0.22-scale model of the North American XP-82 airplane with several modifications designed to reduce the buffeting of the airplane. The effects of various modifications on the air flow over the model are shown by means of photographs of tufts. The drag, lift, and pitching-moment coefficients of the model with several of the modifications are shown" (p. 1).

Memorandum describing wind-tunnel tests made to determine the aerodynamic characteristics of a 20-percent-chord plain aileron on a semispan wing with the NACA 0012-64 section. The report includes the results of tests of the wing unswept and swept back 45 degrees and with the aileron deflected from 0 to 10 degrees.

Memorandum presenting wind-tunnel tests that have been made to determine the aerodynamic characteristics of a model tail plane with modified NACA 65-010 sections and a tapered plan form. Results were obtained with the model tail plane unswept and swept back. The data show the lift, drag, pitching-moment, and hinge-moment coefficient variation with angle of attack and flap deflection at various Mach numbers.

"A solution is presented for the coupled modes and frequencies of swept wings mounted on a fuselage. The energy method is used in conjunction with power series to obtain the characteristic equations for both symmetrical and asymmetrical vibration. A numerical example which is susceptible to exact solution is presented, and the results for the exact solution and the solution presented in this paper show excellent agreement" (p. 1).

Report presenting the results of strength tests on thick-skin wing structures. Some of the factors that were found to have influence on the buckling behavior and strength are shown with data and the conditions under which a combination of multiweb and multipost construction may be used are discussed. Results regarding circular-arc airfoils, multiweb beams, and multipost stiffened beams are provided.

Memorandum presenting flight and wind-tunnel measurements made of the low-speed stalling characteristics on a swept-wing jet aircraft. Included in the study are the effects on the stalling characteristics of a number of wing modifications. Results regarding the roll-off characteristics and maximum lift and stalling characteristics are provided.

Memorandum presenting flight tests conducted on two straight-wing jet airplanes of generally similar configuration, one exhibiting a diving tendency and the other a climbing tendency, in order to investigate the cause for the particular type of behavior of each airplane at high Mach numbers. The results showed that the diving tendency experienced by the one airplane was due to the predominant effect of an increased angle of attack of the horizontal tail.

"This report contains the flight-test results of the lateral and directional-stability and control phase (including tests with wing-tip tanks) of a general flying-qualities investigation of the Lockheed P-80A airplane (Army No. 44-85099). These tests were conducted at indicated airspeeds up to 494 miles per hour (0.691 Mach number) at low altitude and up to 378 miles per hour (0.816 Mach number) at high altitude. These tests showed that the flying qualities of the airplane were for the most part in accordance with the requirements of the Army Air Forces Stability and Control Specifications" (p. 1).

This report contains the flight-test results of the stalling characteristics measured during the flying-qualities investigation of the Lockheed P-8OA airplane (Army No. 44-85099). The tests were conducted in straight and turning flight with and without wing-tip tanks. These tests showed satisfactory stalling characteristics and adequate stall warning for all configurations and conditions tested.

Report presenting tests to determine the flight characteristics of an F-86A airplane equipped with an area-suction boundary-layer-control system on the flaps and to investigate the possible operational problems which may arise on a flight installation of boundary-layer control. Results regarding the airplane with slatted leading edge, suction requirements, airplane with suction flap and various leading-edge configurations, factors affecting flap lift increment, and operational characteristics of boundary-layer control are provided.

This report contains the flight-test results of the longitudinal-stability and -control phase of a general flying qualities investigation of the Lockheed P-80A airplane (Army No. 44-85099). The tests were conducted at indicated airspeeds up to 530 miles per hour (0.76 Mach number) at low altitude and up to 350 miles per hour (0.82) Mach number) at high altitude. These tests showed that the flying qualities of the airplane were in accordance with the requirements of the Army Air Forces Stability and Control Specification except for excessive elevator control forces in maneuvering flight and the inadequacy of the longitudinal trimming control at low airspeeds.

From Summary: "Flight tests were conducted on a straight-wing fighter-type jet airplane to investigate the lateral-control characteristics associated with a wing-dropping tendency encountered at high subsonic Mach numbers. The chief factors found to account directly for the wing-dropping tendency were a progressive reduction in aileron-control effectiveness with increasing Mach number, and an increase in effective dihedral above a Mach number of 0.8 which made the lateral trim particularly sensitive to small changes in sideslip angle."

Memorandum presenting tests conducted to determine the flight characteristics of an F-86F airplane equipped with an area-suction-type boundary-layer control installation on the trailing-edge flaps. Measurements were made of the lift, drag, and engine bleed-air requirements. Results regarding the aerodynamic characteristics as well as some miscellaneous characteristics are provided.

Report presenting flight measurements on a swept-wing jet aircraft to determine the effects of adding forward camber and an increased leading-edge radius on the low-speed stalling characteristics, the high-speed static longitudinal stability, and the airplane drag. The modified leading edge produced values of maximum lift somewhat greater than the slats on a normal airplane, but the stall was unacceptable because of an abrupt roll-off.

Report presenting tests to determine the flight characteristics of an F-86 airplane equipped with a blowing-type boundary-layer-control installation on the trailing-edge flaps. The effectiveness of the flap was determined in conjunction with slatted leading edges and an inflatable rubber boot on the leading edge. Measurements were made of lift, drag, flow requirements, and computations for take-off, climb, and landing.