"The basic aerodynamic characteristics of a 0.04956-scale model of the Convair TF-102A airplane with controls undeflected have been determined at Mach numbers from 0.60 to 1.135 for angles of attack up to approximately 22 deg in the Langley 8-foot transonic tunnel. In addition, comparisons have been made with data obtained from a previous investigation of a 0.04956-scale model of the Convair F-102A airplane. The results indicated the TF-102A airplane was longitudinally stable for all conditions tested" (p. 1).

Memorandum presenting an investigation made in the stability tunnel with a 2.3-scale spinning model of a typical mortar shell. The tests were made to measure the aerodynamic forces and moments acting on a typical spinning mortar shell. Results regarding the basic configuration, effect of changes in tail configuration, effect of changes in the nose configuration, and comparison of mortar shell and antisubmarine rocket are provided.

From Introduction: "The design and flight evaluation of an airborne target simulator for use in tracking studies of fighter-type airplanes equipped with optical gunsights have recently been reported (ref. 1). In this equipment the target airplane was represented by a movable dot of light projected on the windshield of the test airplane."

Report presenting an investigation of the transonic flutter characteristics of two 64 degree sweptback delta wings. Both of the wings had simulated streamwise ribs and orthogonal spanwise spars, but the wings had different stiffness and mass.

Report presenting an investigation by the transonic-bump method of the static longitudinal aerodynamic characteristics of a series of swept, highly tapered, thin wings in the high-speed 7- by 10-foot tunnel. Testing occurred over a range of Mach and Reynolds numbers and angles of attack. Results regarding lift and drag characteristics and longitudinal stability characteristics are provided.

Memorandum presenting an investigation of a semispan-wing-fuselage model with a 60 degree delta wing with an aspect-ratio-8.2 blunt trailing-edge flap-type control in the 9- by 12-inch blowdown tunnel. Control hinge-moment and effectiveness characteristics were obtained over an angle-of-attack range of plus or minus 10 degrees at control deflections up to 90 degrees.

"Damage to the compressor blades of turbojet engines due to ingestion of foreign objects is a growing problem, the solution of which has been made more difficult by the large percentage of damaging materials that have remained unknown. A rapid emission spectroscopic method was devised to identify the chemical composition of these foreign objects. Results on laboratory-prepared specimens and blades from damaged engines show that the method can be utilized to determine the nature of the ingested foreign objects" (p. 1).

"Measurements of runway roughness were made on runaways at Washington National Airport, New York International Airport, La Guardia Airport, and Logan International Airport, Boston, Mass. This report presents these measurements in the form of tables as well as plots" (p. 1).

Report presenting testing of the performance of a 16-inch tip-diameter rotor designed for impulse operation at the mean radius with a relative Mach number of 1.53 and 114 degrees of turning. Results regarding the rotor with guide vanes, blade-element performance, rotor alone, and modified rotor hub contour are provided.

"A 1/13-scale Republic F-105 wing-root inlet configuration in which inlet components were varied was tested in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1,41, 1.81, and 2,01 corresponding to Reynolds numbers per foot of 4,19 X 10(exp 6) , 3.74 X 10(exp 6) , and 3.46 x 10(exp 6) respectively. Angles of attack ranged from -4 deg to 15 deg and a few configurations were tested in a sideslip range from -8 deg to 4 deg. Inlet performance and engine-face flow distortions as affected by pitch, sideslip, inlet-lip sweep, contraction ratio, boundary-layer control, and engine bypass are presented and discussed" (p. 1).

A combination sliding-ring and pressure-balancing seal capable of transferring pressurize air from stationary to rotating parts was developed and experimentally investigated at sliding velocities and cooling-air pressures up to 10,000 feet per minute and 38.3 pounds per square inch absolute, respectively. Leakage of cooling air was completely eliminated with an expenditure of balance air less than one-fourth the leakage loss of air from labyrinth seals under the same conditions. Additional cooling of the carbon-base seal rings was required, and the maximum wear rate on the rings was about 0.0005 inch per hour.

"An experimental investigation of combustor total-pressure loss was undertaken to confirm previous theoretical analyses of effects of geometric and flow variables and of heat addition. The results indicate that a reasonable estimate of cold-flow total-pressure-loss coefficient may be obtained from the theoretical analyses. Calculated total-pressure loss due to heat addition agreed with experimental data only when there was no flame ejection from the liner at the upstream air-entry holes" (p. 1).

Report presenting flutter characteristics at transonic speeds of a model of a fighter-type-airplane wing over a range of Mach numbers. The results indicated an abrupt increase in flutter speed ratio near a Mach number of 1.0, with only slight increases noted as it was increased to 1.4. Results regarding the effect of flutter-boundary shape are provided.

Report presenting an investigation of a transonic turbine with a 0.6 hub-tip radius ratio in order to determine the effect of stator and rotor secondary flows on turbine performance. Results regarding the overall performance, stator exit surveys, and rotor exit surveys are provided.

Characteristic velocities of six single-element injectors that separately varied propellant spreading and mixing were measured over a range of oxidant-fuel weight ratios of 2 to 7. Hydrogen inlet temperature was -320 degrees F. Injectors that both mixed and spread the propellants had the highest characteristic-velocity efficiency. Spreading of either propellant produced about the same increment efficiency. The increase in efficiency due to mixing was relatively small. With similar injectors, oxygen-hydrogen required about 0.2 to 0.5 of the combustor volume of oxygen-heptane for the same efficiency.

"An investigation was made at high subsonic speeds in the Langley high-speed 7- by 10-foot tunnel to determine the static aerodynamic forces and moments on a missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination. The results indicated significant variations in all the aerodynamic components with changes in chordwise location of the missile. Increasing the angle of attack caused increases in the induced effects on the missile model because of the wing-fuselage-pylon combination" (p. 1).

Report presenting a wind-tunnel investigation of bomb-release problems by measuring static forces for computation of bomb drop paths. Forces and moments were measured on bombs of three fineness ratios and on a swept-wing fighter-bomber configuration for several positions of the bomb under an open bomb bay. Results regarding contour paths and drop-path calculations are provided.

Report presenting a wind-tunnel investigation of bomb-release problems by measuring static forces for computation of bomb drop paths. Forces and moments were measured on bombs of three fineness ratios and on a swept-wing fighter-bomber airplane for various positions of the bomb under an open bomb bay. The wing of the plane is shown to have a significant effect on the bomb forces before and after the bomb emerged from the bomb bay.

Report presenting an experimental investigation of the pressures induced on a flat plate by a propulsive jet exhausting from sonic and supersonic nozzles at a free-stream Mach number of 1.80. Measurements of the pressure distribution on a flat-plate wing were made at zero angle of attack for four different locations of the jet exhaust nozzle beneath the wing. Results regarding the jet-off pressure coefficients, jet-on pressure coefficients, and incremental pressure coefficients are provided.

Report presenting an investigation at high subsonic speeds of a complete model with a highly tapered wing and several tail configurations. The complete model was tested with a chord-plane tail, a T tail, and a biplane tail. A discussion regarding the pitching-moment characteristics, lift and drag characteristics, and stabilizer characteristics is provided.

"A supersonic wind-tunnel investigation on store interference has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.61. Forces and moments were measured on a large ogive-cylinder store in the presence of a 45 degree swept-wing-fuselage bomber configuration for a number of store locations below the fuselage center line. Results of the investigation show that large variations of store lift, drag, and pitch occur with changes in store or airplane angle of attack, store vertical location, and store horizontal location" (p. 1).

The performance results, as well as a compressor-turbine match point study based on a particular mode of engine operation, are compared with those previously obtained with the same turbine having first-stator areas 70, 95.6, and 132 percent of design. Maximum efficiencies for all turbine configurations were high, on the order of 87 to 89 percent. The efficiencies obtained at the match points for the 87-, 95.6-, and 132-percent turbines were slightly lower. No match point for the 70-percent turbine was obtained because, with first-stator areas less than 75.5 percent of design, the turbine would develop insufficient work to drive the compressor at the match point.

Report presenting an investigation at high subsonic speeds to determine the static aerodynamic forces and moments on a canard missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination. Significant variations in all the aerodynamic components were noted with changes in chordwise location of the missile. Results regarding force and moment characteristics and effects of angle of attack and Mach number are provided.

Report presenting measurements made at Mach numbers of 4.0 and 8.3 of the drag, static stability, damping in pitch, and boundary-layer transition characteristics of several high-drag bodies of revolution that might be used for high-speed entry into the earth's atmosphere. The static stability was found to be high with centers of pressure as far aft as 91 percent of the length from the nose. Results regarding the force and moment data, boundary-layer transition, a comparison of roughness height to boundary-layer thickness, other causes of boundary-layer instability, and Reynolds numbers for high-speed entry into the Earth's atmosphere are provided.