This report presents the results of a flight investigation to determine the effect on the performance of a turbosupercharged engine of an exhaust-gas-to-air heat exchanger installed between the engine-exhaust collector ring and the turbosupercharger. The background, results, and discussion of the investigation are described.

Report presenting measurements of the pitot-pressure distributions in the flow field, pressure distributions over the body, and downwash distributions through shed vortices for an inclined body of revolution at a free-stream Mach number of 1.98. Results regarding the experimental pressure distributions and vortex positions, vortex strengths computed from experiment, comparisons of theoretical and experimental vortex paths, and comparisons of theoretical and experimental downwash distributions through the body vortices are provided.

Report presenting a procedure for estimating the range of peak airplane load factors and maneuvering tail loads likely to be experienced in pitch-up maneuvers. Results of computations indicated that though the load factors and maneuvering tail loads were not critical in pitch-up maneuvers at 35,000 feet, they were likely to exceed design levels at 15,200 feet.

Report presenting the results of an estimation of the limit forces on airfoils at supersonic speeds. The limit pressure coefficient attainable on an airfoil is shown to be about 70 percent of the pressure coefficient for a vacuum over a wide range of Mach numbers.

Report presenting an investigation of burner liners in a turbojet engine to determine the principal factors limiting the burner-liner service life. The investigation covered a range of engine speeds and testing was conducted to determine whether bare, ceramic-coated, or shielded thermocouples would give the most correct temperature readings.

The nature of the flow at the exit of a row of turbine blades for the range of conditions represented by four different blade configurations was evaluated by the conservation-of-momentum principle using static-pressure surveys and by analysis of Schlieren photographs of the flow. It was found that for blades of the type investigated, the maximum exit tangential-velocity component is a function of the blade geometry only and can be accurately predicted by the method of characteristics. A maximum value of exit velocity coefficient is obtained at a pressure ratio immediately below that required for maximum blade loading followed by a sharp drop after maximum blade loading occurs.

Memorandum presenting an investigation in the supersonic pressure tunnel to determine the static longitudinal stability and control characteristics of several missiles at a Mach number of 2.01. The present paper consists largely of a data presentation of the results obtained at combined angles of pitch and sideslip. Appendices are included in which the body, wind, and stability-axes systems are described and the transfer equations necessary to convert the basic data to other forms are shown.

Memorandum presenting the effects of resin coating methods on some physical properties of laminates prepared with glass fabric, Fiberglas 181, and bonded with two commercial polyester resins. The resins used were Laminac 4126 and Selectron 5003. The resin coating methods used were roller coating, application of a dilute solution of resin, resin immersion, application of monomeric styrene, and vacuum impregnation.

Report presenting a study of the application of Wiener filter theory to the design of a beam-rider guidance system operating in the presence of glint noise. The theory is then used to establish the theoretical lower limit of root-mean-square error and the corresponding desired transfer-function characteristics.

Report presenting a wind-tunnel investigation at low speed in the 300 mph 7- by 10-foot tunnel to determine the effect of deflector projection on the control effectiveness of spoiler-slot-deflectors on a 30 degree sweptback wing-fuselage model equipped with either a 15-percent-chord spoiler or a spoiler-slot-deflector. Results regarding the aerodynamic characteristics, wing longitudinal characteristics, rolling-moment characteristics, and pressure distributions are provided.

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of various external-store configurations on the longitudinal and lateral aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane. Results regarding accuracy and remarks on effects of stores are provided.

Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of the addition of one body-mounted external store, tip tanks, and several tip-mounted missile configurations on the aerodynamic characteristics in pitch of a fighter model with a low-aspect-ratio, unswept wing at Mach number 1.82. Many of the tip-mounted store configurations were found to produce increased lift-curve slopes and drag increments which decreased with increasing lift coefficient above lift coefficients of about 0.06.

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 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 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.

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.

An investigation was conducted to relate the engine performance of the heat-resistant alloys, Stellite 21, Hastelloy B, cast S-816, forged S-816, X-40, Nimonic 80, Refractory 26, N-155, and Iconel X to their stress-rupture properties. The engine test consisted of the repetition of a 20-minute cycle, 15 minutes at rated speed and approximately 5 minutes at idle. The results of the investigation indicated a direct correlation between stress-rupture life and blade life for the relatively low-strength alloys. The stress-rupture life and blade life for the relatively high-strength alloys did not correlate because of the effects of the vibratory stresses and the corrosive-gas atmosphere.

Report presenting a wind-tunnel investigation on two series of twisted and cambered wings, which were identical except for wing section, to compare the effects of NACA 4-digit and NACA 64A chordwise distributions of thickness on the longitudinal aerodynamic characteristics of the wings. Results regarding the low-speed results, high-speed results, and flow studies are provided.

Report presenting a sample of data on atmospheric turbulence on Lockheed U-2 airplanes during research flights. The intensity, amount, and extent of atmospheric turbulence observed in the United States is in good agreement with data from England and Western Europe. Results regarding overall gust distribution, intensity of turbulence, percent of rough air, and size of turbulent areas are provided.

"The strength of modern lightweight thin-wall structures is generally limited by the strength of the compression members. An adequate design of these members requires a knowledge of the compressive stress-strain graph of the thin-wall material. The "pack" method was developed at the National Bureau of Standards with the support of the National Advisory Committee for Aeronautics to make possible a determination of compressive stress-strain graphs for such material" (p. 133).

Report presenting an investigation in the high-speed tunnel using the transonic bump technique in order to study the effectiveness of full-span flap-type controls on 31 unswept rectangular wings. Results regarding lift-curve slope, flap-effectiveness parameter, and the agreement between predicted and experimental results are also provided.

"An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the performance and windmilling drag characteristics of an original and a modified turbojet engine of the same type. Data have been obtained at simulated altitudes from 5000 to 45,000 feet, simulated flight Mach numbers from 0.09 to 1.08, and engine speeds from 4000 to 12,500 rpm. Engine performance data are presented for both engines to show the effects of altitude at a flight Mach number of 0.25 and of flight Mach number at an altitude of 25,000 feet" (p. 1).

Combustion chamber performance properties of a 3000-pound-thrust axial-flow turbojet engine were determined. Data are presented for a range of simulated altitudes from 15,000 to 45,0000 feet and a range of Mach numbers from 0.23 to 1.05 for various modifications of the engine.