From Introduction: "The results of the aforementioned study are presented in this report together with the method of analysis employed. The net stability change is shown together with the individual contributions due to flexibility of wing, tail, and fuselage, both including and neglecting the effect of inertial loads."

Wedge and scoop air inlet performance and thrust minus drag comparisons at free stream in supersonic wind tunnel test.

Report presenting the design of a two-stage, solid-fuel, rocket-propelled, general research pilotless aircraft suitable for investigating stability and control at supersonic velocities. The flight test investigation is described and information is provided for zero-length launchers and operational flight-test techniques of two-stage rockets. Results regarding launching characteristics and lateral stabilization and control flight tests are provided.

Report presenting flight tests conducted on two different inlet configurations, a submerged divergent-wall inlet and scoop inlet, to determine their characteristics when installed on a YF-93 airplane. Measurements were made of the pressure-recovery characteristics of the inlets and overall airplane drag for each configuration. Results regarding the induction-system efficiency, airplane drag, and a relative comparison of the inlet installations are provided.

Memorandum presenting a model bomb-release investigation conducted in the 9-inch supersonic tunnel at a Mach number of 1.62 to determine what first-order interference effects are involved in making releases at supersonic speeds and, in some cases, to ascertain what modifications might be made to obtain near-level drops. The results of these tests indicate that the interference effects of the fuselage or wing-pylon upon the bomb release are, in most cases, adverse.

Report presenting an investigation to determine the effects of two spinner shapes on the pressure recovery in an NACA 1-series D-type cowl behind a three-blade propeller with fairly thick shanks. Data were obtained at a range of Mach numbers, inlet velocity ratios, blade angle ratios, and a specified Reynolds number.

"The solution of heat-transfer problems has become vital for many aeronautical applications. The shapes of objects to be cooled can often be approximated by cylinders of various cross sections with flow normal to the axis as, for instance heat transfer on gas-turbine blades and on air foils heated for deicing purposes. A laminar region always exists near the stagnation point of such objects. A method previously presented by E. R. G. Eckert permits the calculation of local heat transfer around the periphery of cylinders of arbitrary cross section in the laminar region for flow of a fluid with constant property values with an accuracy sufficient for engineering purposes" (p. 223).

Report presenting flutter data obtained with the use of rocket-propelled vehicles in the transonic and low supersonic speed ranges for three low-aspect-ratio, highly tapered, swept wings. Structural influence coefficients were obtained for each of the three plan forms and calculated mode shapes and frequencies are provided. Time histories for each of the configurations also demonstrate the flutter pattern of each wing.

Report presenting tests on two 60 degree sweptback wings of aspect ratios 2 and 3 to provide information on the influence of leading-edge radius on the static longitudinal stability characteristics of swept wings.

Memorandum presenting results of three-component force tests of a cylindrical body with an ogival nose equipped with panel-type drag brakes each covering approximately 21 percent of the body circumference and located on opposite sides of the body at the rear end. Results regarding the drag brakes in the horizontal plane, drag brakes in the vertical plane, comparison of drag brakes, and minimum drag are provided.

"At the request of the Air Materiel Command, Army Air Forces an investigation of the low-speed, power-off stability and control characteristics of the McDonnell XP-85 airplane is being conducted in the Langley free-flight tunnel. The XP-85 airplane is a parasite fighter carried in a bomb bay of the B-36 airplane. As a part of the investigation a few force tests were made of a 1/5 scale model of the XP-85 with a conventional tail assembly installed in place of the original design five-unit tail assembly" (p. 1).

Report presenting an investigation in the high-speed tunnel to determine the static aerodynamic forces and moments on a missile model during simulated launching from midsemispan locations of various types of wings. The purpose of the investigation is to determine the nature and origin of the mutual interference experienced by various combinations of wing-fuselage models and externally carried missiles. Results regarding isolated missile characteristics, the effect of varying chordwise position, effects of angle of attack and Mach number, effect of airplane wing geometric characteristics, effect of missile spanwise location, and comparison of wing-fuselage and fuselage effects on the missile forces and moments are provided.

Report presenting a wind-tunnel investigation at Reynolds numbers of about 7,000,000 based on the mean aerodynamic chord of the wing and over a range of Mach numbers. Two airfoils were tested to evaluate the effect of a large leading-edge radius with increased thickness over the forward 40 percent of the chord on the reliability of the predictions of the supersonic area rule. Results regarding the comparison of basic- and modified-wing models, comparison of experimental and computed drag coefficients, and a comparison of indentations are provided.

"At the request of the Air Material Command, Army Air Forces an investigation of the low-speed, power-off stability and control characteristics of the McDonnell XP-85 airplane is being conducted in the Langley free-flight tunnel. The XP-85 airplane is a jet propelled, parasite fighter with a 34 deg sweepback at the wing quarter chord. It was designed to be carried in a bomb bay of the B-36 air plane. The first portion of the investigation consists of a preliminary evaluation of the stability and control characteristics of the airplane from force and fight tests of an unballasted 1/5-scale model. The second portion of the investigation consists of test of a properly balasted 1/10-scale model which will include a study of the stability of the XP-85 when attached to the trapeze for retraction into the B-36 bomb bay" (p. 1).

"Tables I and II of the present paper summarize the gust and draft velocity data for thunderstorm-flights 21 and 22 of August 14, 1946 and August 15, 1946, respectively. These data were evaluated from records of NACA airspeed-altitude and acceleration recorders installed in P-61C airplanes and are of the type presented for previous flights. Table III summarizes the readings of a milliammeter which was used in conjunction with other equipment to indicate ambient-air temperature during thunderstorm surveys. These data were read from photo-observer records and include all cases in which variations of the instrument indications were noted for the present flights" (p. 1).

Buffet boundaries, buffeting-load increments for the stabilizers and elevators, and buffeting bending-moment increments for the stabilizers and wings as measured in gradual maneuvers for a jet-powered bomber airplane are presented. The buffeting-load increments were determined from strain-gage measurements at the roots or hinge supports of the various surfaces considered. The Mach numbers of the tests ranged from 0.19 to 0.78 at altitudes close to 30,000 feet. The predominant buffet frequencies were close to the natural frequencies of the structural components. The buffeting-load data, when extrapolated to low-altitude conditions, indicated loads on the elevators and stabilizers near the design limit loads. When the airplane was held in buffeting, the load increments were larger than when recovery was made immediately.

From Introduction: "In the present report, the concept of velocity diffusion is applied in an analysis of blade losses expressed in terms of the fundamental parameter of wake momentum thickness. Restrictions and limitations involved in the application of the results to cascade performance analyses are discussed."

Report presenting a free-flight rocket-propelled model investigation at Mach numbers from 1.2 to 1.9 to determine the longitudinal and lateral aerodynamic characteristics of a low-drag aircraft configuration. Aerodynamic data in pitch, yaw, and roll were obtained from transient motions induced by small pulse rockets firing at intervals.

"Fuel was injected from different type of injection nozzles into the combustion chamber of the NACA combustion apparatus, operated as a compression-ignition engine. High speed motion pictures were taken of the fuel sprays and combustion. Single-orifice nozzles of 0.008, 0.020, and 0.040 inch diameter, and multiorifice nozzles having 2, 6, and 16 orifices were tested. Nozzles having impinging jets and slit orifices were also included" (p. 327).

Two normal -wedge-inlet configurations (straight and sweptback splitter plates) were investigated in the Lewis 8- by 6-foot supersonic wind tunnel at Mach numbers of 1.50 to 1.99. Negligible differences occurred in the performances of the two normal-wedge inlets. In comparison with a previously tested scoop inlet, the normal-wedge configuration showed superior thrust-minus-drag characteristics at Mach 1.99. However the scoop inlet was better at Mach numbers of 1.80 and 1.50.