An altitude-test-chamber investigation of a 28-inch-diameter ram-jet engine at a simulated flight Mach number of approximately 2.0 for altitudes of 40,000 to 50,000 feet was conducted at the NACA Lewis laboratory. Three different flame holders, varying in the number and size of the annular gutters, in conjunction with several fuel-injection systems were investigated. The combustion efficiency for the flame-holder fuel-injection system that provided the best over-all operational fuel-air-ratio range (0.03 to 0.075) was over 0.9 at a fuel-air ratio of about 0.065 for the altitude range investigated.

A heat-transfer investigation was conducted with air flowing through an electrically heated Inconel tube having either a long-approach or a right-angle-edge entrance, an inside diameter of 0.402 inch, and a length of 24 inches over a range of Reynolds numbers up to 375,000 and average inside-tube-wall temperatures up to 2000 degrees R. Good correlation of heat-transfer data was obtained for both entrances, which substantiates work previously reported. A fair correlation of friction data was obtained for both entrances. The entrance configuration had little effect on the average heat-transfer and friction coefficients.

Report presenting the results of an experimental investigation of the downwash and wake characteristics behind two highly swept wings in a supersonic stream. Results regarding the rate of change of downwash with angle of attack at zero lift, variation of downwash angle with angle of attack, and wake are provided.

From Introduction: "This paper, which should be of interest to those concerned with transonic wind tunnels, covers the design and operating characteristics of the nozzle."

Report presenting an investigation to determine the lateral control characteristics of a 20-percent-chord flap-type aileron of various spans on a semispan wing-fuselage model in the transonic speed range. The wing of the model had 45 degrees of sweepback, an aspect ratio of 3.7, a taper ratio of 1.0, and an NACA 65A009 airfoil section parallel to the free stream.

Memorandum presenting a pressure-distribution investigation of a wing of a complete supersonic aircraft configuration as conducted in the 4- by 4-foot supersonic tunnel at Mach number 1.59 based on the mean aerodynamic chord. The experimental life and drag coefficients were less than those predicted by linear theory. Results regarding section pressure characteristics, section characteristics, spanwise characteristics, and overall wing characteristics are provided.

Report presenting the first sample of time-history data of airspeed, altitude, and normal accelerations obtained by the NACA VGH recorder in transport operations. This data defines the distribution of normal accelerations and airspeeds in greater detail than what was obtainable with the V-G recorder. Results regarding effective gust velocities, proportion of time spent in rough air, values of airspeed in descent, and variations in load experience are provided.

Report presenting the pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 measured in the Mach number range of 0.60 to 1.08 by the wing-flow method. Variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60. Results regarding the pressure-recovery characteristics and application of the data to fuselage installations are provided.

"The rolling effectiveness of a thin, tapered, and essentially unswept wing having outboard partial-span plain ailerons has been determined by means of rocket-powered test vehicles. The rolling power decreased abruptly in the Mach number range from 0.85 to 0.95 and more gradually at higher speeds. At the maximum Mach number of the tests (1.95), the rolling effectiveness was only 20 percent of that at a Mach number of 0.85" (p. 1).