Static tests on the compatibility of fluorine with non-metals at atmospheric temperature eliminated many materials from further consideration for use in fluorine systems. Several materials were found compatible at atmospheric pressures. Only Teflon and ruby (aluminum oxide) were compatible at 1500 pounds per square inch gage.

Report presenting an investigation of the hydrodynamic characteristics of a multijet water-based aircraft capable of supersonic speeds and with jet engines exhausting through the step. The step engine exhausts were found to considerably increase afterbody wetting and smooth-water resistance, but they had no significant effect on longitudinal stability. Results regarding spray characteristics, resistance and stability at constant speed, take-off stability, landing stability, and jet noise are provided.

Report presenting two-dimensional porous-wall cascade tests of specified NACA blade sections at typical compressor hub conditions at speeds up to choking. For typical compressor blade hub sections, the angle of attack for best operation at high Mach numbers is about 6 degrees higher than the design angle of attack for low speeds. Results regarding the 65-series blade tests and circular-arc blade-section tests are provided.

Report presenting measurements of the skin temperature and surface pressure on a large-scale, highly polished nose with a relatively sharp-tipped 100 degree total-angle cone followed by a conical flare section of 10 degree half-angle. Heating on the forward 3.0 to 4.5 inches of the 100 degrees cone was generally lower than that on the rearward portion.

Report presenting measurements of the loads of the wing of a Boeing B-47A medium bomber using strain-gage instrumentation during 23 symmetrical push-pull maneuvers at a variety of altitudes, Mach numbers, and gross weights. Time histories of aerodynamic shear, bending moment, and torque at each of four spanwise stations on the left wing and one on the right wing were created. Based on the results, presently available methods seem to be capable of predicting additional and basic loads accurately within the range of flight conditions in the test.

Report discussing testing to determine the effects of control profile on the dynamic hinge-moment and flutter characteristics of a trailing-edge flap-type control. A conventional control and two control profile modifications were examined. Information about spring moments is also provided.

Memorandum presenting a flight investigation using pulse techniques to determine longitudinal and lateral dynamic stability characteristics of the D-558-II research airplane with particular reference to the jet exhaust effects of the rocket engine. Results regarding the longitudinal stability characteristics, and lateral stability characteristics are provided.

From Introduction: "The configuration described in this paper represents one approach to such an airplane and the results of the wind-tunnel and tank evaluations are presented. In the present investigation, the aerodynamic longitudinal characteristics over a Mach number range from 0.6 to 1.97 were obtained."

Memorandum presenting an investigation of the effectiveness of water-vaporization cooling that would be obtained by ejecting water upstream from the stagnation point conducted in a liquid-fuel rocket jet as a stagnation temperature of 4000 degrees Fahrenheit.

Report presenting free-oscillation tests in the high-speed tunnel to determine the effect of control trailing-edge thickness and control aspect ratio on the dynamic hinge-moment characteristics of a trailing-edge, flap-type control. Tests were made at a range of Mach numbers and a range of oscillation reduced frequency at an angle of attack of 0 degrees. Results regarding damping moments and flutter characteristics and spring moments are provided.

"A small-scale transonic investigation of two semispan wings of the same plan form was made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range of 0.70 to 1.10 and a mean-test Reynolds number range of 745,000 to 845,000 to determine the effects of partial-span leading-edge camber on the aerodynamic characteristics of a swept-back wing. This paper presents the results of the investigation of wing-alone and wing-fuselage configurations of the two wings; one, was an uncambered wing and the other had the forward 45 percent of the chord cambered over the outboard 55 percent of the span. The semispan wings had 50deg 38ft sweepback of their quarter-chord lines, aspect ratio of 2.98, taper ratio of 0.45, and modified NACA 64A-series airfoil sections tapered in thickness ratio" (p. 1).

"Preliminary results of one phase of a control-motion study program are presented in the form of plots of load factor.and angular acceleration against indicated airspeed and of time histories of several measured quantities. The results were obtained from 197 maneuvers performed by an F-86A jet-fighter airplane during normal squadron operational training. Most of the tactical maneuvers of which the F-86A is capable were performed at pressure altitudes ranging from 0 to 32,000 feet and at indicated airspeeds ranging from 95 to 650 miles per hour" (p. 1).

Report presenting an investigation in the altitude test chamber to evaluate several afterburner configurations on the XJ79 engine. Data were obtained from nine configurations which show the effect on burner performance of increased burner diameter and modifications to the flameholder, fuel system, and flow swirl.

An investigation of the 1XP excitation of inclined single-rotation propellers has indicated a new concept for determining propeller shaft forces and moments of an inclined propeller. This report presents preliminary results, in particular to the counterrotating propeller.

Memorandum presenting an investigation to determine the operating characteristics of a small side-located control stick with the use of a ground simulator incorporating a power control system. The simulator or pitch chair was designed to produce the pitching motion associated with the short-period mode of an airplane. The general opinion of all of the pilots operating the pitch chair was that they were favorably impressed with their ability to precisely track with the small side-located controller provided the control-system characteristics were desirable.

Report presenting an investigation in the 300 mph 7- by 10-foot tunnel to determine the chordwise and spanwise load distribution on a thin 60 degree delta-wing-fuselage model equipped with double slotted and extended double slotted flaps. The effects of a canard on the loads of the wing with the extended double slotted flaps are also determined.

From Introduction: "This paper presents the results obtained during the phase of the B-52 flight investigation concerned with the steady-state wing loads. Where possible, the effects of Mach number and flexibility on the measured load are analyzed and presented."

Report presenting an investigation in the transonic blowdown tunnel to determine the effects of inlet-lip sweep angle on the internal-flow characteristics of a semielliptical scoop-type inlet with an inlet lip stagger of 30 degrees. the testing was performed at a range of Mach numbers and mass-flow ratios. Results regarding flow over the nose, total-pressure recovery at inlet, flow distortions at inlet, boundary-layer control, and inlet performance are presented.

Memorandum presenting limited flow-field surveys made behind a large-scale thin straight wing of aspect ratio 3, both alone and in combination with a body and vertical tail. The surveys indicated a region of high downwash angles, low dynamic pressures, and rough flow, that extended higher above the wing chord plane, and farther aft, with increasing angle of attack beyond the tail.

"Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 to determine the static longitudinal stability and control characteristics of various arrangements of the Grumman F11F-1 airplane. Tests were made of the complete model and various combinations of its component parts and, in addition, the effects of various body modifications, a revised vertical tail, and wing fences on the longitudinal characteristics were determined" (p. 1).

Report presenting a wind-tunnel investigation to determine the extent to which boundary-layer removal through slots is effective as a means for maintaining extensive laminar layers at high Reynolds numbers. Results regarding drag, suction-flow and pressure-loss distribution, surface pressure distribution, lift, and some of the difficulties involved in obtaining extensive laminar flow are provided.

Report presenting an experimental investigation using a 1 7/8-inch diameter burner to determine the suitability of residual fuel oils as carriers in magnesium slurries. Four residual fuel oils with varying viscosities were investigated by themselves and in slurries of 50 percent magnesium. Results regarding the settling characteristics, blow-out velocity, and combustion efficiency are provided.

"Altitude performance characteristics of the J65-B3 turbojet engine and its components were obtained at engine-inlet conditions corresponding to Reynolds number indices from 0.2 to 0.8 over a range of corrected engine speeds from 70 to 110 percent of rated speed. Engine operational limits up to an altitude of 75,000 feet together with ignition and windmilling characteristics were also obtained. The engine and component data are presented both in graphical and in tabulated form. The operational characteristics are presented in graphical form" (p. 1).

A brief summary is made of methods available to the helicopter designer for obtaining desired stability characteristics by modifications to the airframe design. The discussion is based on modifications made during the establishment of flying-qualities criteria and includes sample indications of theoretical studies of additional methods.