From Introduction: "An investigation was conducted in an NACA Lewis altitude chamber to determine the altitude performance characteristics of a J47-25 axial-flow turbojet engine over a range of engine-inlet Reynolds number indices corresponding to altitudes from 18,000 to 54,000 feet and flight Mach numbers from 0.50 to 1.10. Reynolds number at a given corrected engine speed and is a function only of engine-inlet total pressure and temperature, was used instead of various set altitudes and flight Mach number combinations (reference 1). An example is included in the appendix to illustrate the method of obtaining conventional performance parameters for a given flight condition from the data such as presented herein."

Report presenting data obtained three single annular-type combustors with different combustor inlet-air pressure profiles over a range of engine speeds. Results regarding effect of changing combustor inlet-air pressure profile and hole geometry on combustor performance, performance of the prototype J40-WE-8 turbojet engine combustor, correlation of combustion efficiency with engine fuel-air ratio and combustion parameter, and comparison of several combustors from different turbojet engines are provided.

Report presenting the performance characteristics of one convergent and three convergent-divergent nozzles obtained over a range of nozzle pressure ratios. Results regarding one-dimensional flow theory and the performance characteristics themselves are provided.

Report presenting a study of the altitude-starting limits of a production turbojet engine with an axial-flow compressor and a multiple through-flow combustor. The ignition limits, flame-propagation limits, and acceleration limits of the engine were improved to increase the starting limits to relatively high altitude.

Report of an investigation of the overall performance characteristics of a complete missile configuration in the 8- by 6-foot supersonic wind tunnel at several Mach numbers, angles of attack, canard-control-surface deflections, and a designated Reynolds number based on wing mean aerodynamic chord. The investigation showed that at a Mach number of 2.0, the addition of engines to a no-engine configuration increased drag and moved the aerodynamic center rearward but produced little additional lift. Results regarding force and moment evaluation and engine-internal-flow evaluation are provided.

Memorandum presenting an investigation of the stability of several bodies of revolution having fineness ratios smaller than 1.0 and having rounded fronts and blunt bases. Free-drop tests were made in the vertical 20-foot free-spinning tunnel to determine the behavior of the various bodies in descent.

Report presenting testing of the rolling effectiveness and drag of half-delta wing-tip ailerons on rectangular and tapered wings sweptback 0 and 45 degrees for a range of Mach numbers. The rolling effectiveness was relatively uniform across the Mach number range and was lower at subsonic speeds and higher at supersonic speeds than the partial-span plain ailerons.

Report presenting the longitudinal and lateral characteristics of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees and cambered and twisted for a uniform load at lift coefficient 0.25 and Mach number 1.5. The investigation occurred over a range of sideslip angles. The results indicated that the longitudinal characteristics were essentially unaffected by Reynolds number or the sideslip angles investigated.

Report discussing an investigation of two transonic research airplane models at a range of Mach numbers and Reynolds numbers. The main difference between the models was the aspect ratio of the horizontal tail. Results regarding the stability, control, incremental horizontal-tail characteristics, downwash, horizontal-tail load, stability factors, and a tailless configuration are provided.

Report presenting the results from several recent flights on the Northrop X-4 No. 2 airplane, including the longitudinal stability characteristics over a range of Mach numbers in straight and accelerated flight and the short-period longitudinal-oscillation characteristics.

The performance characteristics of a downward canted normal-shock side (scoop) inlet located downstream of a triangular control surface are presented for free-stream Mach numbers of 1.5 and 1.8 in terms of total pressure recovery and mass flow ratio for various boundary-layer removal systems, angles of attack, control surface deflections and adverse yaw. An engine operating condition for a hypothetical turbojet engine is established, and the match point characteristics of the engine-inlet configuration are summarized. It is shown that the diffuser performance increases with increased boundary-layer removal and decreases because of the presence of the wake from the forward control surface.

Report presenting an investigation of liquid-film cooling at a variety of air temperatures and Reynolds numbers. Results regarding the effect of coolant flow per circumferential length on liquid-cooled length, correlation of heat transfer from hot gas to liquid film for constant coolant flow per circumferential length, and generalized plot of film-cooling data based on heat-transfer correlation at constant coolant flow per circumferential length are provided.

Report discussing the division of load among the wing, fuselage, and tail for several aircraft configurations at subsonic and supersonic speeds. The load that each component carries at various Mach numbers and angles of attack is described.

Report discussing an investigation to determine the aerodynamic characteristics of a model of a tailless delta-wing airplane configuration with a leading edge swept back 60 degrees at a range of Mach numbers. Information about lift-curve slope, buffeting, drag rise, hinge-moment coefficients, transonic trim, and stability is provided.

"Forced-convection heat-transfer data have been obtained for water flowing in an electrically heated tube of circular cross section at water pressures of 200 and 2000 pounds per square inch, and temperatures in the nonboiling region, for water velocities ranging between 5 and 25 feet per second. The results indicate that conventional correlations can be used to predict heat-transfer coefficients for water at pressures up to 2000 pounds per square inch and temperatures in the nonboiling region" (p. 1).

"A camera designed for use in flight has been developed by the NACA Lewis laboratory to photograph cloud droplets in their natural suspension in the atmosphere. A magnification of 32 times is employed to distinguish for measurement purposes all sizes of droplets greater than 5 microns in diameter. Photographs can be taken at flight speeds up to 150 miles per hour at 5-second intervals, A field area of 0.025 square inch is photographed on 7-inch-width roll film accommodating 40 exposures on an 18-foot length" (p. 1).

From Introduction: "The performance of several tail-pipe burners with fixed area exhaust nozzles is reported in references 1 to 4, and the performance of an NACA-designed tail-pipe burner with a variable-area exhaust nozzle is reported in reference 5. Operational characteristics of the tail-pipe burner are also discussed."

Report presenting a free-flight investigation of two rocket-powered model configurations to determine the damping in roll. The model had rectangular wings of 4.5 aspect ratio and were the same except for the airfoil sections. Results regarding rolling velocity and total-drag coefficient are provided.

Report presenting experimental force and moment data obtained by pressure measurements on a wing of aspect ratio 8.02, 45 degree sweepback of the quarter-chord line, taper ratio of 0.45, and NACA 63(sub 1)A012 airfoil sections, which are compared with the calculated loadings obtained by standard methods and several variations of the methods. Results regarding the system of identifying solutions, spanwise load distribution, lift-curve slope, center of pressure, wing pitching moment, and induced drag are provided.

Report presenting an investigation in the transonic tunnel to determine the flow phenomena, pressure recovery, and external drag of a forward-located underslung air scoop mounted on a basic body of revolution with fineness ratio 11, which when cut off to provide an exit for the internal flow had a fineness ratio of 8. Results regarding the surface pressure distributions, drag, lift and pitching moment, and flow into the inlet on the modified model are provided.

Memorandum presenting minimum spark-ignition energies for 12 pure fuels measured at reduced pressure, and the data obtained were extrapolated to 1 atmosphere. Some of the fuels investigated included normal and cycloparaffins, olefins, carbon disulfide, and oxygenated compounds such as alcohol, ether, propylene oxide, and tetrahydropyran.

Report presenting an investigation to determine the effect of varying the span and deflection angle of a 15-percent-chord slat on the longitudinal aerodynamic characteristics of a semispan wing with 49.1 degrees of sweepback at the leading edge, an aspect ratio of 3.78, a taper ratio of 0.586, and NACA 65A006 airfoil sections. Force measurements and chordwise pressure distributions were obtained on the wing and extended slat with and without a deflected trailing-edge flap.

The structural damping in the torsion mode of vibration of a series of untwisted, laminated thin beams simulating propeller blades is presented. The number of lamination were varied, as well as the bonding material and the method of joining lamination. Application of the data to the calculation of the minimum flutter speed of thin propeller blades indicates that appreciable gains in the minimum flutter speed may be obtained for laminated blades using a Cycleweld bond.

Report presenting an investigation in the high-speed tunnel for a range of Mach numbers to determine the lateral control characteristics of a wing-fuselage combination with the wing quarter-chord line swept back 32.6 degrees, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 section. Results regarding yawing-moment characteristics, spoiler-slot-deflector testing, and rolling-moment coefficient are provided.