Report presenting a wind-tunnel investigation of a model equipped with a 60 degree delta wing and a 60 degree delta horizontal all-movable canard control surface to determine the stability, control, and canard-surface hinge-moment characteristics at low speeds and at a Reynolds number of 9 x 10(exp 6). Two longitudinal positions of the canard surface were tested. Results regarding lift and pitching moment, drag, and hinge moment are provided.

Report presenting an investigation with sting-mounted rocket-propelled models in free flight at approximately zero lift to determine the effect of wing flexibility on the damping-in-roll characteristics of a wing-body combination over a range of Mach numbers.

Report of an investigation using three rocket-propelled delta-wing-body combinations for a range of Mach numbers to determine the damping-in-pitch characteristics. All models were statically stable but dynamically unstable at transonic speeds. Information about trim, lift, and drag is also provided.

Report presenting the results of force and moment tests at Mach numbers from 3.0 to 6.3 on bodies of revolution of fineness ratios from 5 to 10 and on flat-bottom bodies of fineness ratio 10 along with theoretical predictions for these bodies. Testing included eight cone and cone-cylinder models, six nose-cylinder models, and three flat-bottom bodies.

Memorandum presenting an investigation to determine the effects of jet exhaust and Reynolds number on the flow over the vertical stabilizer and rudder of the Douglas D-558-II research airplane with special attention to an understanding of the rudder reversals experienced in flight on the full-scale airplane. Tests were made at Mach numbers of 1.62, 1.93, and 2.41 over a range of ratios of jet static pressure to stream static pressure from the jet-off ratio to about 40 and for a maximum range of sideslip angles of 6 degrees. Results regarding the effect of varying jet static-pressure ratio, effect of varying sideslip angle, effect of varying Reynolds number, and effect of varying angle of attack.

Memorandum presenting characteristics of a hydraulic control as determined by analyzing transient data obtained with a turbojet engine operating in the altitude wind tunnel. The excellent overall performance of the speed control is attributed to the elimination of large lags in the control system, thereby permitting the use of relatively high loop gains while still maintaining satisfactory damping in transients. Some information regarding the frequency-response analysis of speed control, simulation of speed control, and acceleration control are provided.

Memorandum presenting an investigation of a can-type flame holder employing a fuel-air-mixture control sleeve in a 20-inch-diameter ramjet combustor conducted by free-jet and direct-connect techniques at a simulated flight Mach number of 3.0 and altitudes from about 70,000 to 80,000 feet. Results regarding the effect of shortening combustion chamber and effect of pilot-burner variables are provided.

Memorandum presenting an investigation of the effect of the number and width of annular flame-holder gutters on afterburner performance in a 26-inch-diameter afterburner test rig. The burner inlet temperature was held at 1250 degrees Fahrenheit. Results regarding the effect of gutter width on stability limits and effect of flame-holder blockage on pressure drop are provided.

Report presenting five fuels of boiling temperatures and several hydrocarbon types in a jet-propulsion annular combustor to determine the effect of fuel boiling temperature and paraffinic and aromatic hydrocarbon types on combustion efficiency and altitude operational limit. At the severe inlet-air condition, the highest combustion efficiencies were obtained with the paraffinic and aromatic fuels with low boiling temperatures were found to vary from 30 to 58 percent.

The performances of Navy Jet Mix and MIL-F-5624A (JP-3) fuels were compared in J33, J47, and NACA experimental annular combustion chambers. Combustion efficiencies, altitude operational limits, and carbon-forming tendencies wer determined and discussed. The results indicate that Jet Mix fuel can be utilized satisfactorily in a number of current turbojet engines over the normal operating range. Small differences in combustion efficiences and altitude operational limits existed between the two fuels but these differences depended on the particular combustor and simulated altitude and rotor speed condition. Excessive carbon deposition is not predicted for Jet Mix fuel, although this property may be marginal.

Report presenting results from a limited flight program to obtain information on airplane response and actual rates and amounts of control motion used by service pilot in performance of squadron operational training. Results regarding control deflection, control rates, airplane angular velocities, airplane angular accelerations, angle of attack and angle of sideslip, airplane load factors, and airspeed and altitude are provided.

Report presenting an investigation to determine the high altitude performance of the J57-P-1 turbojet engine and components conducted at the NACA Lewis altitude wind tunnel. Four conditions were tested: engine operation with both the compressor bleed ports closed, with the large compressor bleed port open, with both compressor bleed ports open, and normal engine operation with the automatic control.

Report presenting an investigation in the supersonic tunnel using a canard missile configuration designated as NACA RM-4. Measurements of lift, drag, and pitching moment were made over a range of Mach numbers and angles of attack. The data is presented without analysis.

Report presenting the aerodynamic stability derivatives and pitch and yaw control effectiveness of two full-scale guided bombs over a range of Mach numbers in free-flight drop tests. Results regarding performance information, roll control operation, and aerodynamic characteristics are provided.

Report presenting an investigation in the stability tunnel of the use of spoilers for obtaining static longitudinal stability of a model of a canard missile in reverse flight. Results indicated that stable pitching-moment slopes can be obtained at angles of attack up to 11 degrees in the low speed range of the tests, but further investigation of high subsonic speeds will be necessary.

Report presenting measurements of longitudinal stability and drag characteristics of a fin-stabilized body of revolution with a fineness ratio 12 at low angles of attack using the free-fall method. Information about the data obtained from testing as well as the experimental coefficients related to body normal-force, total longitudinal-force, and body moment with Mach number is provided.

"Aerodynamic data have been obtained for a 45-degree sweptback wing-body-canopy configuration at transonic speeds with the canopy placed on the body so that the cross-sectional area of the canopy approximately filled the concave portion of the basic wing-body cross-sectional-area distribution curve (design location) and with the canopy placed 0.0614 of the body length forward of the design location. Data have also been obtained for the basic wing-body combination. Placing the canopy in the rear position significantly reduced the drag of the configuration at transonic speeds, increased the lift, and did not appreciably affect the slope of the pitching-moment curve" (p. 1).

"Preliminary measurements have been made of velocity and temperature fluctuations in the flow behind a heated grid in a uniform airstream. Temperature correlation shows a reasonable degree of isotropy, and the temperature fluctuations die out at large distances more slowly than the turbulence, as has been predicted theoretically under some strongly simplifying postulates" (p. 1).

Pressure distributions were measured over rectangular wings of aspect ratio 2 and triangular wings of aspect ratios 2 and 4 at Mach numbers of 1.45 and 1.97. The investigation includes some comparison of the effects of Reynolds number and of thickening the wing root sections on the loading.

Report presenting an investigation at Mach numbers of 1.61 and 2.01 to determine the control effectiveness and hinge-moment characteristics for a series of 25.4-percent-chord trailing-edge controls on a trapezoidal wing with a 23 degree sweptback leading edge, aspect ratio of 3.1, and taper ratio of 0.4. Pressure distribution and hinge-moment measurements were made at a range of angles of attack and control deflections. Results regarding effect of control deflection, effect of wing angle of attack, effect of Reynolds number, effect of trailing-edge thickness, effect of hinge-line gap, effect of Mach number, and effect of control size and location are provided.

Memorandum presenting two-spool matching procedures which may be employed to analyze turbojet, turboprop, and stationary power plants. The procedures were applied to obtain the sea-level static equilibrium performance of a simple two-spool turbojet engine in which the compressor and turbine performances were based on experimental results. Results regarding engine performance at sea-level static conditions, component performance, and effect of compressor-discharge bleed are provided.

Report presenting an experimental investigation in the 7- by 10-foot tunnel in a range of Mach numbers to determine the drag and opening characteristics of a model of a Kaman Aircraft Corporation Rotochute. The Rotochute is a two-bladed flapping rotor with governor-controlled blades designed for lowering cargo containers from high-speed aircraft tested at various Mach numbers simulating constant rates of descent.

Report presenting an investigation of several two-dimensional supersonic inlet configurations at a Mach number of 2.01 and an angle of attack of 0 degrees. Two inlets similar in supersonic diffuser design but one with a subsonic diffusers about half the length of the other one were also investigated. Results regarding the inlet design, pressure recovery, shadowgraphs, and suggestions for inlet improvement are provided.

Memorandum presenting an exploratory investigation in the 9- by 12-inch blowdown tunnel to determine the effect of inboard spoilers located along the 20- and 30-percent-chord lines on the static longitudinal stability characteristics of a semispan 45 degree sweptback wing-body combination with a leading-edge chord-extension. The model pitching-moment characteristics were improved by spoilers extending from 15 percent semispan to 45 percent semispan. Results regarding pitching moment, lift, drag, rolling moment, and lateral center of pressure are provided.