Memorandum presenting an approximate subsonic theory developed for the solid blockage interference in circular wind tunnels with walls slotted in the direction of flow. The theory indicated the possibility of obtaining zero blockage interference. Tests in a circular slotted tunnel based on the theory confirmed the theoretical predictions.

Report presenting testing of a 42.7 degree sweptback tapered wing with three types of ailerons tested at a Mach number of 1.9 and a Reynolds number of 2,200,000; the wing geometry was similar to that of an XS-2 airplane. The purpose of the investigation was to determine the effectiveness of ailerons at these specified flight characteristics. Results regarding the aerodynamic characteristics of the wing are also provided.

Report presenting an experimental investigation of a submerged air inlet incorporating a cascade of airfoils for turning and diffusing the entering air. Variables associated with submerged air inlets and airfoil-cascade designs were considered, including changes to the ramp plan form and angle for the submerged inlet and the cascade-axis inclination, cascade-blade angle, solidity, and inclination of the center line of the duct for the cascade.

Report presenting measurements of the longitudinal stability and control characteristics of a canard airplane configuration using the wing-flow method. The investigation included measurements of lift, pitching moment, and rolling moment of the semispan model with control settings between several different degrees. The experimental data are presented in summarized or abridged form and calculated trim curves are presented for various flight loading conditions.

Report presenting the total drag coefficients of 60 degree cone cylinders of fineness ratio 2.07 measured in free flight from Mach numbers of 1.5 to 8.2. Results regarding the smooth 60 degree cone cylinder, rifled models, and discontinuity lines in the shadowgraph pictures are provided.

Report presenting drag coefficients determined by the accelerometer method for the Bell X-1 airplane with 8-percent-thick wing and 6-percent-thick tail in power-off flight over a range of Mach numbers and lift coefficients. Results regarding the variation of computed lift and drag coefficients, variation of lift coefficient with Mach number, and effect of Mach number on lift-drag ratio are provided.

Memorandum presenting an investigation of a series of five 75S-T6 aluminum-alloy elementary skin and spar-cap combinations with skin varying from 0.051 to 0.500 inch in thickness to determine the temperature and stress gradients resulting from the application of heat to the surface. The data are presented in the form of tables of the measured temperatures and stresses calculated from the measured strains.

Report presenting results and analysis of the longitudinal stability and control characteristics of the Douglas D-558-I airplane at a range of altitudes and Mach numbers. It was found that large and rapid changes in elevator deflection and force were required for balance at Mach numbers above 0.84 due to a sharp decrease in elevator-stabilizer effectiveness.

Report presenting visual observations and flow analyses made of annular liquid flow with cocurrent air flow in 2- and 4-inch-diameter horizontal transparent tubes. The experiments occurred over a range of air mass velocities, air temperatures, and Reynolds numbers. Results regarding the velocity and thickness of liquid films, description of water-film disturbances, effect of flow variables on liquid-film characteristics, and relation between disturbances and flow conditions are provided.

Report presenting a comparison of the calculated response characteristics corresponding to the maximum maneuver of a variable-incidence, a canard, and a conventional tail-aft-control, beam-rider, guided missile. All the configurations were designed to be the same except for the effects of changes in lift ratio. Results regarding limited control-surface deflection, limited angle of attack of the critical surface, servo energy, surface-deflection interference, and size of surfaces are provided.

Report presenting measurements of pressure made over the chord of a swept-wing model at four stations along the span by the NACA wing-flow method. The model was an untapered 45 degree sweptback wing of aspect ratio 3.5 with 2-inch-chord NACA 65-210 airfoil sections normal to the leading edge. Results regarding the chordwise pressure distributions and spanwise distributions of section lift, drag, and pitching moment.

Report presenting pressure distributions, tuft patterns, and schileren surveys of a sweptback wing-fuselage combination in the 8-foot transonic tunnel at a range of Mach numbers and angles of attack. The wing had 45 degrees of sweepback, an aspect ratio of 4.0, a taper ratio of 0.6, and an NACA 65A006 airfoil section. Results regarding an angle of attack of 0 degrees, 4 degrees, 6 degrees, 8 degrees, 12 degrees, and 20 degrees are provided.

Report presenting an investigation of zero-lift drag of a fin-stabilized wing-body combination made at high-subsonic and supersonic speeds in a range of Reynolds numbers. The data are presented with that from a wingless body and similar winged body with a slightly different ratio of body frontal area to wing area. Results regarding total drag and wing-plus-interference drag are provided.

Report of testing on an untapered 35-degree sweptback airfoil-flap model, representative of a wing or tail surface, with several 1/4-chord full-span flaps differing in aerodynamic balance. A plain flap, a horn-balanced flap, and a beveled-trailing-edge flap were compared to a flap that had a 31-percent-flap-chord overhang balance. Information about lift, pitching-moment, and hinge-moment characteristics is provided.

Report presenting tests of three types of nose shapes with a circular underslung inlet inlet located well forward of the body of revolution at a Mach number of 1.42. Total-pressure measurements and shadowgraphs of the different configurations were obtained.

Report presenting an investigation of the drag of spherically blunted conical models of fineness ratio 3 at a range of Mach and Reynolds numbers. Results of the tests showed that slightly blunted models had less drag than cones of the same fineness ratio through the Mach number range. Results regarding the total drag, wave drag, and viscous effects are provided.

Report presenting an investigation at low speed in the low-turbulence tunnel to determine the effects of variations in propeller-shank geometry and propeller-spinner-juncture configuration on the aerodynamic characteristics of an NACA 1-series cowling-spinner combination with an eight-blade dual-rotation propeller. Results regarding internal flow and external flow are provided.

"Values of total drag coefficient were measured for four round-nosed bodies of revolution in free flight at Mach numbers from 0.6 to 1.5 and Reynolds numbers from 10 x 10(6) to 50 x 10(6). The bodies were designed by rounding off the sharp, fineness-ratio-3.56 nose of a previously tested configuration. The nose radii tested were 27.4, 38.7, 80.6, and 100 percent of the maximum body radius and corresponded to values of 0.075, 0.150, 0.650, and 1.000, respectively, for the ratio of nose-sphere frontal area to body frontal area" (p. 1).

Report presenting a pilot-opinion survey conducted with a conventional fighter airplane fitted with special servo devices for varying in flight the dihedral effect, static directional stability, and directional damping. Results showing the boundaries that define satisfactory and tolerable lateral oscillatory characteristics are presented.

Report presenting measurements of the position errors of angle-of-attack and sideslip detectors located on the fuselage of a 35 degree swept-wing fighter airplane over a range of Mach numbers and at lift coefficients up to the buffet boundary. Results regarding the angle of attack and sideslip are provided.

Report presenting a rocket-propelled missile model with cruciform, triangular, inline wings and tails, which has been tested through a range of Mach numbers at small wing-deflection angles. Results regarding the stability and damping, control effectiveness, and hinge moments are provided.

From Introduction: "Because of the unusual nature of this equipment, and because it is proving to be very useful for certain kinds of aerodynamic research, this report has been prepared. It contains a description of the equipment and its use to obtain aerodynamic coefficients. The imperfections in the wind-tunnel air stream and their effect on model tests are also discussed."

Pressure distributions and forces for a series of four bodies of revolution having nose-fineness ratios varying from 4 to 10 have been obtained and compared with theory for a Mach number of 3.12, a Reynolds number range of 2x10(sup)6 to 14x10(sup)6, and angles of attack from zero to 9 degrees. In general, a comparison of the experimental data with a second-order theory showed good agreement for the range of variables investigated.

Memorandum presenting the pressure recovery, mass flow, and drag of a twin-scoop, side-inlet-body combination measured at Mach number 1.4 and 1.7. The inlet was located on a body having an ogival nose followed by a cylindrical section and a total fineness ratio of 5.