Report presenting an investigation of the low-speed stability and control characteristics of a 1/15-scale free-flying model of the Convair XB-58 airplane. Results regarding the longitudinal stability and control and a pod-drop investigation are provided.

Report presenting testing of the Republic F-105 at low speeds to determine the results of additional longitudinal stability tests of measurements of the hinge moments and normal force of the all-movable horizontal tail on a model equipped with a supersonic-type elliptical wing-root inlet.

Report presenting an investigation of the problem of applying controls to low-aspect-ratio wings of triangular plan form by using the NACA wing-flow method with parallel-sided models with sharp leading and trailing edges. Results regarding the data analysis, Reynolds number and separation effects, flap effectiveness, plan-form characteristics, angle of zero lift, and triangular plan-form flying-wing characteristics are provided.

Report presenting a discussion of the aerodynamic forces and moments on inclined bodies of revolution. An approximate theory to allow for the effects of viscosity is developed and applied. Results regarding the variation of lift and pitching moment, and center of gravity are provided.

Report presenting tests using the NACA wing-flow method to determine the effect of sweepback angle on the longitudinal characteristics of a scale semispan model of the Bell X-5 variable-sweep airplane at a range of Mach numbers. Lift, drag, and pitching moments were obtained for a range of angles of attack.

Report presenting an investigation with the dual purpose of determining the effect of two bodies in various positions, symmetrically located from the plane of symmetry, on the aerodynamic characteristics of a wing-fuselage model and determining the aerodynamic loads on one of two bodies. Some of the most significant effects were obtained for the direct-mounted tip bodies which gave a large increase in the lift-curve slope of the basic model.

Report presents the results of a study of combustion in a spark-ignition engine given in NACA Technical Reports 704 and 727. The present investigation was made with the NACA high-speed motion-picture camera, operating at 40,000 photographs a second, and with a cathode-ray oscillograph operating on a piezoelectric pick-up in the combustion chamber. Photographs are presented showing that the origin of knock is not necessarily in the end gas. The data obtained indicates that knock takes place only in a part of the cylinder charge which has been previously ignited either by autoignition or by the passage of the flame fronts but which has not burned to completion. Mottled regions in the high-speed Schlieren photographs are demonstrated to represent combustion regions.

"The NACA injection impeller was developed to improve the mixture distribution of aircraft engines by discharging the fuel from a centrifugal supercharger impeller and thus to promote a thorough mixing of fuel and charge air. Experiments with a double-row radial aircraft engine indicated that for the normal range of engine power the NACA injection impeller provided marked improvement in mixture distribution over the standard spray-bar injection system used in the same engine. The mixture distribution at cruising conditions was excellent; at 1200, 1500, and 1700 brake horsepower, the differences between the fuel-air ratios of the richest and the leanest cylinders were reduced to approximately one-third their former values" (p. 217).

An analysis has been made of available data on vee tail surfaces. Previously published theoretical studies of vee tails have been extended to include the control effectiveness and control forces in addition to the stability. Tests of two isolated tail surfaces with various amounts of dihedral provided a check of the theory. Methods for designing vee tails were also developed and are given in the present paper.

Memorandum presenting an investigation of the low-speed stability and control characteristics of a scale free-flying model of the Convair XB-58 airplane. The model was flown over an angle-of-attack range from 9 to 30 degrees and only relatively low-altitude conditions were simulated. The stability and control characteristics were found to be satisfactory over the range investigated with the center of gravity at the 0.25 mean aerodynamic chord.

Theoretical pressure distributions and measured lift, drag, and pitching moment characteristics at three values of Reynolds number are presented for a group of NACA four-digit-series airfoil sections modified for high-speed applications. The effectiveness of flaps applied to these airfoils and the effect of standard leading-edge roughness were also investigated at one value of Reynolds number. Results are also presented of tests of three conventional NACA four-digit-series airfoil sections.

"Several electrically heated finned steel cylinders enclosed in jackets were cooled by air from a blower. The effect of the air conditions and fin dimensions on the average surface heat-transfer coefficient q and the power required to force the air around the cylinders were determined. Tests were conducted at air velocities between the fins from 10 to 130 miles per hour and at specific weights of the air varying from 0.046 to 0.074 pound per cubic foot. The fin dimensions of the cylinders covered a range in pitches from 0.057 to 0.25 inch average fin thicknesses from 0.035 to 0.04 inch, and fin widths from 0.67 to 1.22 inches" (p. 269).