Paper presenting three ideas regarding potential simplifications of missile-control systems in order to make them more reliable without sacrificing system performance. The three methods presented include an autorotating-vane spoiler, a bellows flap, and free controls. All are based on modified airplane control systems.

Report discussing the low-speed stability and control characteristics of a modified model of the MX-1554A with a triangular wing and triangular stabilizing surfaces, which are designed to give more satisfactory stability and control than previous versions. Other modifications included an increase in slotted-flap span, redesigned tip aileron, fuselage tail cone, and speed brakes. Results provided include the effect of flow-control devices, tank and pylon location, a ground board, rotary stability derivatives, and a single support strut on the stability, control, and aerodynamic characteristics.

Report presenting the overall performance and rotating stall characteristics of a single-stage compressor with a hub-tip ratio of 0.76 and a symmetrical velocity diagram over a wide range of weight flow for several different design speed percentages. No discontinuities in performance were noted at an operating condition. Results regarding the overall performance, types of rotating stall observed, circumferential extent of stall zones, flow fluctuations incited by rotating stall, rotating-stall hysteresis, and a theoretical analysis are provided.

Report presenting a method for calculating the lift and pitching-moment characteristics of circular cylindrical bodies in combination with triangular, rectangular, or trapezoidal wings or tails through the subsonic, transonic, and supersonic speed ranges. A computing table and set of design charts are presented to reduce the calculations to routine operations. Information about lift, center of pressure, effects of wing incidence, and limitations and extensions of the method is provided.

Memorandum presenting a procedure based on the transonic area rule, which has been used to design a four-nacelle delta-wing airplane configuration. A flight test of a model of the configuration showed a zero-lift transonic drag rise of 0.010 which, when compared with estimates, indicated the absence of adverse interference effects.

Memorandum presenting some recently obtained data on the aerodynamic characteristics of low-aspect-ratio wings at supersonic Mach number of 4.04 and 6.9 and discusses some new methods of predicting the lift and drag of such wings. The plan forms, airfoil sections, and thickness ratios of the wings tested are provided.

Memorandum presenting an investigation of the performance characteristics of a double-shroud ejector for the purpose of evaluating its effectiveness as an exit nozzle. Calculations based on ejector performance data, taken with the ejector discharging into quiescent air, indicate that thrust performance on the order of ideal nozzle thrust may be obtained over a Mach number range of 0.8 to 2.3 from a double-shroud ejector. The results of a simplified theoretical analysis are in fair agreement with those experimentally obtained.

Report presenting testing of a 14-inch supersonic mixed-flow rotor of high specific mass flow and an inlet radius ratio of 0.52, which was designed for impulse operation and uniform work output and tested in Freon-12. Results regarding the overall rotor performance, casing friction, entrance flow, distribution of static pressure on the casing, and exit flow are provided.

Report presenting data from an investigation of the effects of slot location and slot geometry on the flow in a square tunnel for a Mach number range up to 1.4. Calculated static-pressure and angle-of-flow distributions along the slotted boundary are presented for several slot configurations in a tunnel with two opposite walls slotted.

Report presenting information on the amount and relative intensity of atmospheric turbulence for altitudes up to 60,000 as obtained by airplanes and balloon-borne instruments. Analysis of the data obtained indicated that there are substantial reductions in turbulence at higher altitudes in the weather conditions measured in the tests. Results regarding gust distributions, including non-thunderstorm turbulence, thunderstorm turbulence, total gust distributions, and a comparison of gusts are also provided.

Report discussing a flight test of a four-nacelle delta-wing airplane configuration based on the transonic area rule in order to counteract the effects of high pressure drag at transonic and supersonic speeds. The testing verified that the transonic area rule can make designing complex aircraft with low transonic and supersonic pressure drag much easier.

Report presenting an analytical investigation to evaluate the effects of permeability variations on surface temperatures and coolant flows for ranges of temperature and Reynolds number that are of particular interest for gas-turbine blades. Results regarding small-orifice calibrations, effect of orifices in series with porous surfaces on permeability correlation, effect of permeability variations on coolant-flow rates and porous-wall temperatures, evaluation of the experimental porous blade, and design features for transpiration-cooled turbine blades are provided.

"A metal-ceramic composition containing approximately 80 percent chromium plus 20 percent aluminum oxide (Al(sub 2)O(sub 3)) by weight has been investigated for possible gas-turbine blade use. The results of modulus-of-rupture, thermal-shock, and blade-performance studies indicate that this material may have adequate thermal-shock resistance; however, the strength for the application appears marginal" (p. 1).

Report presenting the results of testing on a high-pressure-ratio, axial-flow compressor rotor designed to operate efficiently at high speeds. High flows are needed to increase engine thrust without increasing engine front area. Results regarding the overall total-pressure ratio and adiabatic efficiency, effect of angle of attack on efficiency, determination of the effect of mean radius rotor inlet Mach number and Reynolds number on turning angle, and other information about ideal operation of the rotor are provided.

"A method is presented for estimating the rolling moments caused by wing-tail interference for missiles composed of wing-tail-body combination. The considerations involved in determining the structure of the downwash field behind lifting cruciform wing-body combinations and the rolling moment on cruciform wings of various plan forms induced by an infinite line vortex are discussed in detail. Computations of induced rolling moments for several missile designs are compared with experimental results" (p. 1).

From Introduction: "The purpose of this paper is to provide further information on the effects of Reynolds number on the aerodynamic characteristics of the wing of reference 1 as well as to provide load distributions for the wing at Mach numbers of 1.6 and 1.9."

Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 to determine the static longitudinal stability and control characteristics of a 1/16-scale model of the Douglas D-558-II research airplane. The results indicated a high degree of longitudinal stability that decreased slightly with increasing Mach number and lift coefficient.

Report presenting testing of a 20 degree semiangle conical-inlet ramjet engine with a design Mach number of 2.13 in free supersonic jets to determine the inlet and combustion performance over a fuel-air ratio and Mach number range. Results regarding preflight and flight testing are provided.

Report presenting an investigation in the Langley 300 mph tunnel to determine the low-speed static stability and control characteristics of a model of the Bell X-1 airplane equipped with a 4-percent-thick, aspect-ratio-4 wing. Tests were also made to determine optimum flap deflection for a slotted flap. Results regarding longitudinal stability and control, high lift devices, lateral and directional stability, and lateral and directional control are provided.

Report presenting an investigation of the effects of adding leading-edge roughness to the surfaces of an unswept, untapered, 6-percent-thick, circular-arc-airfoil wing equipped with a full-span, 0.2-chord, plain, trailing-edge aileron. Results regarding the rolling-effectiveness data, addition of roughness on a wing, and variation of drag coefficient are provided.

Report presenting some of the factors affecting the two-dimensional characteristics of flap-type controls equipped with overhang nose balances at a Mach number of 2.40. The effects of changing nose-balance overhang, altering the shape of the nose balance, beveling the afterbody of the basic wing forward of the flap nose, varying wing-flap gap size, fixing transition, and varying the flap trailing-edge thickness are presented.

Report presenting a flight investigation of the variation of the intensity of buffeting with lift and Mach number using a Douglas D-558-II research airplane over a range of Mach numbers and altitudes. Buffeting was encountered during flight at all Mach numbers attained and during level flight at Mach numbers above 0.9. Results regarding the relationship between lift, angle of attack, and buffeting, buffet frequencies, and intensity of buffeting are provided.

Report presenting a method for calculating the steady-state rolling effectiveness of flexible sweptback wings at subsonic and supersonic speeds. Comparisons between the experimental and calculated values are presented for a wide range of wing-aileron configurations.

Report presenting an investigation of a 45 degree sweptback-wing model with interchangeable round and sharp leading edges to determine the effect of leading-edge separation on the loads experienced by the models in gusts. Leading-edge separation was found to increase the gust load, which appeared to vary based on the gust-gradient distance and velocity.