"Aerodynamic forces and moments have been obtained in the Langley 9- by 12-inch blowdown tunnel on an external store and on a 45 degree swept-back wing-body combination measured separately at Mach numbers from 0.70 to 1.96. The wing was cantilevered and had an aspect ratio of 4.0; the store was independently sting-mounted and had a Douglas Aircraft Co. (DAC) store shape. The angle of attack range was from -3 degrees to 12 degrees and the Reynolds number (based on wing mean aerodynamic chord) varied from 1.2 x10(6) to 1.7 x 10(6)" (p. 1).

Report presenting an experimental airplane crash in order to study the performance of a prototype crash-fire inerting system for reciprocating-engine-powered airplanes. A fire did not occur during this crash, indicating that the crash-fire inerting system functioned satisfactorily as a complete unit. Further improvements in the crash-fire system are also provided.

"A wind-tunnel investigation was made to determine the effects of ejecting high-velocity air near the leading edge of plain trailing-edge flaps on a 35 degree sweptback wing. The tests were made with flap deflections from 45 degrees to 85 degrees and with pressure ratios across the flap nozzles from sub-critical up to 2.9. A limited study of the effects of nozzle location and configuration on the efficiency of the flap was made. Measurements of the lift, drag, and pitching moment were made for Reynolds numbers from 5.8 to 10.1x10(6)" (p. 1).

Report presenting an investigation in the 16-foot transonic tunnel to determine the lateral-control effectiveness of differentially deflected horizontal-tail surfaces mounted behind a 45 degree sweptback wing-fuselage combination. The effectiveness of the differentially deflected horizontal tail as a lateral-control device was found to be essentially independent of angle of attack and Mach number even in the transonic region. Results regarding the effects of differential deflection of horizontal-tail surfaces and effects of the vertical tail are provided.

Report presenting an investigation in the pressure wind tunnel to determine the effect of an operating propeller on the aerodynamic characteristics of a model of a vertical-rising airplane with an unswept wing with an aspect ratio of 3. Lift, longitudinal force, pitch, and roll characteristics, with and without power, are presented for the complete model and various combinations of model components.

Report presenting an investigation to determine the longitudinal stability, lift, and drag characteristics of a rocket-powered model of a canard configuration with a 45 degree sweptback wing of aspect ratio 6.0, taper ratio of 0.6, and NACA 65A009 airfoil section. The variations with Mach number of lift, drag, and longitudinal stability were compared with a tailless and a conventional model with the same wing.

Report presenting an investigation of the effects of leading-edge camber without twist on an aspect-ratio-3 delta wing of thickness ratio 3, a body with an ogive nose, and a cylindrical afterbody. Results regarding the base pressures and body characteristics and wing-body combinations are provided.

Report presenting experimental results showing the static longitudinal-stability and -control characteristics of a model of a fighter airplane with a low-aspect-ratio unswept wing and an all-movable horizontal tail. The investigation was made over a Mach number range from 0.60 to 0.90 and from 1.35 to 1.90. Results regarding the pitching moment at zero lift, longitudinal stability, and longitudinal control are provided.

Report presenting the results of static tests conducted for the purpose of determining the lift forces and hinge moments associated with a flat-plate paddle vane, externally hinged near a rocket-nozzle exit and operating on the jet for vane deflection angles ranging from -4 degrees to 25 degrees. Results regarding vane aerodynamic characteristics, performance of rocket motor, and vane erosion

Report presenting an investigation to determine the aerodynamic characteristics of a wing-fuselage configuration with a wing with quarter-chord line swept back 35 degrees, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section. Lift, drag, and pitching-moment characteristics, downwash angles, and wake characteristics for various angles of attack and Mach numbers are provided.

From Introduction: "Data are presented in graphical form to show the engine performance over a range of altitudes from 5000 to 50,000 feet and flight Mach numbers from 0.21 to 0.97. Curves are presented to show the windmilling characteristics of the engine. All engine performance data obtained in the investigation are also presented in tabular form."

"The hydrodynamic characteristics of a 1/10-size powered dynamic model of the XP5Y-1 flying boat were determined in Langley tank no. 1. Stable take-offs were possible at all practicable positions of the center of gravity and flap deflections. An increase in gross load from 123.5 to 150.0 pounds (21.5 percent) had only a slight effect on the stable range for take-off" (p. 1).

Report presenting a method for the design of supersonic-wind-tunnel nozzles that produce uniform flow over a continuously variable Mach number range without the use of flexible walls. Experimental results from a preliminary investigation of the tunnel are included, including calibration survey of flow, Mach number distributions, and pressure gradients are provided.

Report presenting an experimental and analytical investigation of the flutter of uniform sweptback cantilever wings. The experiments used groups of wings sweptback by rotating and by shearing with angles of sweep ranging from 0 to 60 degrees. Results regarding the experimental investigation and a discussion and comparison of the analytical and experimental results are provided.

The results of power-off force tests and flight tests of a model with a thin unswept low-aspect-ratio wing are presented. The tests were made with the flaps retracted and deflected. The effects on the lateral flight characteristics of decreasing directional stability were noted.

The preignition characteristics of the R-2800 cylinder, as effected by fuel consumption, engine operating variables, and spark plug type and condition, were evaluated. The effects on preignition-limited performance of various percentages of aromatics (benzene, toluene, cumene, xylene) in a base fuel of triptane were investigated. Two paraffins (triptane and S + 6.0 ml TEL/gal) and two refinery blends (28-R and 33-R) were preignition rated. The effect of changes in the following engine operating variables on preignition limit was determined: inlet-air temperature, rear spark plug gasket temperature, engine speed, spark advance, tappet clearance, and oil consumption. Preignition limits of the R-2800 cylinder using Champion C34S and C35S and AC-LS86, LS87, and LS88 spark plugs were established and the effect of spark plug deterioration was investigated.