"This paper deals with the analysis of 2-spar cantilever wings in torsion, taking cognizance of the fact that the spars are not independent, but are interconnected by ribs and other structural members. The principles of interaction are briefly explained, showing that the mutual relief action occurring depends on the "pure torsional stiffness" of the wing cross section. Various practical methods of analysis are outlined" (p. 45).

From Summary: "Procedures for applying these analytical methods to experimentally measured blade-metal temperatures are presented. Data are presented for the leading and trailing edge of a symmetrical water-cooled blade to illustrate the validity of the methods for those portions of the blade. In addition to the application to turbine blades, the methods can be applied to any heat-transfer apparatus having a profile that can be approximated by the shape discussed."

Memorandum presenting an analysis comparing engine performance determined by use of a method involving adjustment of engine cycle calculations using JP-4 fuel with performance obtained using hydrogen as a fuel.

Memorandum presenting hypothetical two-spool nuclear-powered turbojet engines with sea-level static design compressor total-pressure ratios of 20, 15, and 9 and total-pressure losses between the inner-spool compressor exit and turbine inlet of 10 and 30 percent. Results regarding compressor operating lines, gas-generator performance, engine performance, and some general remarks are provided.

Report presenting flight testing over a range of Mach numbers to determine the rolling behavior of a swept-wing airplane with lateral-longitudinal coupling. Results regarding the size of the tail area, speed effects, engine gyroscopic effects, and wing-tip extensions are provided.

Report discussing a flight investigation to obtain experimental information on the handling qualities of a fighter airplane that a human controlled by supplying signals to an attitude type of automatic pilot. The pilots were found to prefer the control-force characteristics provided by a damper rather than a spring feel system. Information about characteristics in pitch, characteristics in roll, dynamic lateral stability, and rough-air flying, tracking, and landing characteristics is provided.

"Skin temperatures and surface pressures have been measured on a slightly blunted cone-cylinder-flare configuration to a maximum Mach number of 9.89 with a rocket-propelled model. The cone had a total angle of 25 deg and the flare had a 10 deg half-angle. Temperature data were obtained at eight cone locations, four cylinder locations, and seven flare locations; pressures were measured at one cone location, one cylinder location, and three flare locations" (p. 1).

Report presenting an investigation of the mechanism of interaction of compression shock with boundary layer. Shockless pressure distributions at supercritical Mach numbers were found to be accounted for by a marked thickening of the boundary layer for some distance ahead of a shock wave.

Memorandum presenting an experimental investigation of the cooling requirements and internal thrust performance of an air-cooled, plug-type, variable-area exhaust nozzle in a turbojet-engine afterburner over a range of exhaust-gas total temperatures and exhaust-nozzle pressure ratios.

Memorandum presenting an investigation of the cooling requirements and internal thrust performance of an air-cooled, plug-type, variable-area exhaust nozzle in a turbojet engine afterburner over a range of exhaust-gas total temperatures and exhaust-nozzle pressure ratios.

Report presenting an experimental investigation conducted to determine the lateral-directional aerodynamic characteristics at transonic speeds of missile configurations with three blunted cone-cylinder bodies. Modifications of the basic model were tested to determine the effects of relative lengths of the bodies and the effects of seals between the cylindrical parts of the bodies. Cross-wind force, drag, yawing moment, and rolling moment were measured through a range of angles of sideslip, angles of attack, and Mach numbers.

Report presenting testing of a model of an airplane configuration with thin, highly tapered, 45 degree sweptback surfaces at a range of Mach numbers to obtain the lateral stability characteristics of the configuration. Results regarding the time history, trim characteristics, lateral-force derivative, vector plots, and downwash and sidewash are provided. At Mach number 1.3, the model experienced a violent combined lateral-longitudinal motion and large angles of sideslip and attack with large rolling velocities.

Report presenting the results of a wind-tunnel investigation at subsonic and supersonic Mach numbers to determine the aerodynamic characteristics of a wing-body combination with a triangular wing of aspect ratio 2. The mean surface of the wing was twisted and cambered to support a nearly elliptical span load distribution at Mach number 1.53 and a lift coefficient of 0.25. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.

Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the aerodynamic characteristics in pitch and sideslip of a canard airplane model at Mach numbers 1.41 and 2.01. Two wings of equal area but differing in plan form were investigated. Results regarding the longitudinal and lateral characteristics are provided.

Memorandum presenting a low-speed investigation to determine the effect of double-slotted flaps on the aerodynamic characteristics of a 45 degree sweptback wing. The flap had a span of 0.35 wing semispan with the inboard end at 0.16 semispan. Results regarding lift characteristics, pitching-moment characteristics, and drag characteristics are provided.

Report presenting aerodynamic-heating data for a range of Mach numbers from free-flight testing on a sealed trailing-edge flap on a clipped 60 degree delta fin. Measurements were taken on both sides and on the upper and lower surfaces of the fin just before the hinge line. Heat-transfer coefficients on the windward side were found to be about 2.5 times the average of the measurements on the leeward side.

Report presenting an investigation at transonic speeds in the 7- by 10-foot tunnel to determine hinge-moment and effectiveness characteristics of a horn-balanced control on an aspect-ratio-3, 45 degree sweptback wing. The investigation was extended through the transonic speed range by testing in the high velocity field over a reflection plane on the sidewall of the tunnel.

Wind-tunnel tests have been made to determine the static longitudinal stability of several models of a short-range artillery shell at Mach numbers of 0.8, 0.9, 1.0, and 1.2. The results of the tests indicated that the best of the spool-shaped shells was statically stable in pitch at all test Mach numbers for an angle-of-attack range up to about 10 degrees. The best of the finned shells was stable to a maximum angle of attack of about 6 degrees.

A tank investigation has been conducted on a 1/8-size powered dynamic model of the Grumman JRF-5 airplane equipped with twin hydro-skis. The results of tests using two types of skis are presented: one had vertical sides joining the top surface to the chine; the other had the top surface faired to the chine to eliminate the vertical sides. Both configurations had satisfactory longitudinal stability although the model had a slightly greater stable elevator range available when the skis without the vertical sides were attached. Free model tests indicated no instability present when one ski emerged before the other. Considerable excess thrust was available at all speeds with either type of skis. A hump gross load-resistance ratio of 3.37 was obtained with the skis with the vertical sides and 3.53 with the other skis. Landing behavior in smooth water with yaw up to 15deg and roll up to 15deg in opposite directions was satisfactory with either type of skis.

Report presenting wind tunnel tests of NACA 65(216)-420 and 66(218)-420 airfoils at speeds up to and slightly above the critical. Section coefficients of lift, drag, and pitching-moment and extensive pressure-distribution data are presented. The critical speed for these airfoils at their design life coefficient of 0.4 is shown to be about 460 miles per hour at seal level and about 415 miles per hour at 25,000 feet altitude.

Report presenting testing of several basic inlet shapes at a range of Mach numbers to determine their mass-flow and pressure recovery characteristics when operated as auxiliary inlets. There is an interest in determining more information about the flow characteristics of inlets at transonic speed range due to the growing complexity of aircraft cooling, ventilation, and boundary-layer control. Results regarding inlet performance, flush circular inlets, flush rectangular inlets, circular scoops, and ramp static-pressure distributions are presented.

Report presenting an investigation of a swept-wing fighter airplane in the transonic tunnel to determine store and pylon loads and the effect of store installation of drag and stability, horizontal-tail loads at sideslip angles of 0 degrees and 5 degrees, and the extent of drag-rise reductions possible by enlarging the fuselage afterbody. Results regarding store and pylon installation, horizontal-tail characteristics, and effects of "area-rule" modifications are provided.

A systematic research program is being carried out in the Langley high-speed 7- by 10-foot tunnel to determine the aerodynamic characteristics of various arrangements of the component parts of research-type airplane models, including some complete model configurations. Data are being obtained on characteristics in pitch, sideslip, and during steady roll at Mach numbers from 0.40 to about 0.95. This paper presents results which show the effect of taper ratio on the aerodynamic characteristics in sideslip of wing-fuselage combinations having wings with a sweep of 45 degrees at the quarter-chord line, an aspect ratio of 4, and a NACA 65A006 airfoil section.