From Summary: "For a number of years now, experimenters have been making measurements of skin friction. Formerly, the main interest was at low Mach numbers; later, measurements were made at supersonic Mach numbers. However, almost all of these measurements were over a limited range of Reynolds numbers. On the other hand, these measurements fairly well determined the effects of Mach number and heat transfer on skin friction. The purpose of this paper is to give the results of skin-friction measurements in turbulent boundary layers at high Mach numbers and high Reynolds numbers where data have not previously existed."

Report discussing tests to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane and to determine the loads on attached stores and detached missiles. An investigation into aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications of aerodynamic characteristics was also carried out at various Mach numbers. Results are presented, but caution is provided in regards to extrapolating results from the model onto a full-scale aircraft.

Memorandum presenting an investigation in the Unitary Plan wind tunnel to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane, and to determine the loads on attached stores and detached missiles in the presence of the model. Results also included a determination of aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications on model aerodynamic characteristics. The results are presented with minimum analysis.

Report presenting an investigation in the supersonic pressure tunnel at two Mach numbers to determine the aerodynamic characteristics of several jet-spoiler controls on a wing having a 45 degree sweepback of the quarter-chord line, an aspect ratio of 3.5, a taper ratio of 0.3, and an NACA 65A005 airfoil section. Testing indicated that the jet-spoiler effectiveness increased with increasing angle of attack and correlated well with the momentum of jet flow.

"A theoretical method is presented for predicting the dynamic lateral stability characteristics of an airplane towed in tandem by a much larger airplane. Values of period and time to damp to one-half amplitude and rolling motions calculated by an analog computer have been correlated with results of two experimental investigations conducted in the Langley free-flight tunnel which were part of a U.S. Air Force program (Project FICON) to develop a satisfactory arrangement by which a bomber could tow a parasite fighter. In general, the theoretical results agree with the experimental results" (p. 1).

Memorandum presenting static longitudinal stability and control characteristics of a flare-stabilized body of revolution employing a movable portion of the flare surface as a pitch control determined for a range of Mach numbers, angles of attack, and control deflections. The variation of lift coefficient with pitching-moment coefficient for the basic configuration with control undeflected was found to be essentially linear, and the stability to increase slightly with increasing Mach number.

Report presenting a study of the effects of mass ratio on the transonic flutter characteristics of untapered 45 degree sweptback wings of aspect ratios 2 and 3.5. A given wing at a given Mach number fluttered at essentially a fixed dynamic pressure regardless of the individual values of the fluid velocity and density. Results regarding the experimental data, analytical results, and a comparison of the two, are provided.

From Introduction: "In order to obtain some insight into the relative merits of canard and outboard-tail control systems at supersonic speeds, a preliminary investigation of a generalized canard and outboard-tail model has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 and the results are presented herein."

Memorandum presenting a technique for predicting the influence of body vortices and the wing shock-expansion field on the pitch-up characteristics of supersonic airplanes to supplement the calculative methods for wing vortices which are well known. The method is applied to the prediction of the pitch-up characteristics of four airplanes with high tails, of which one serves as a calculative example.

Memorandum describing a calculative technique for predicting the influence of body vortices and the wing shock-expansion field on the pitch-up characteristics of supersonic airplanes to supplement calculative methods for wing vortices which are well known. The method is applied to the prediction of the pitch-up characteristics of four airplanes with high tails, of which one serves as a calculative example.

Report presenting an investigation in a chemical jet at a stagnation temperature of 4,000 degrees Fahrenheit at a Mach number of 2.8 to determine the feasibility of cooling models by the ejection of a solid coolant at the stagnation point. A series of conical models were tested with glass, Lucite, nylon, Teflon, and Texolite rods as coolants. Results regarding the cooling properties of each of the materials are provided, and all materials performed adequately with the exception of Teflon.

Report presenting an investigation of a rocket-powered model to study the heat transfer to wing leading edges in the vicinity of their juncture with a cylindrical body. Information about heat-transfer measurements, average heat transfer on cylindrical portions of leading edges, and local heat transfer is provided.

Report presenting some of the concepts and applications underlying the basic arrangement of airplane configurations with tail surfaces outboard of the wing tips. The arrangement was created to be consistent with good supersonic performance characteristics and to avoid some of the stability and trim-drag problems seen with other supersonic configurations. Results regarding stability and control characteristics, lift and drag characteristics, and an analytical study of effects of some design variables are provided.

Report presenting testing of a number of materials and shapes in two supersonic free jets at stagnation temperatures of up to 4,210 degrees Fahrenheit. Some testing was conducted in a supersonic chemical jet and some was conducted in a ceramic-heated air jet. Materials tested included aluminum alloy, copper, Inconel, magnesium, mild steel, molybdenum, stainless steel, titanium, alumina, zirconia, graphite, bakelite, and nylon.

Report presenting an investigation of the landing conditions and landing-gear loads on the Douglas X-3 research airplane during routine research flights. Results regarding the vertical-flight profiles, oscillograph records, time histories of landing-gear loads and airplane center-of-gravity normal accelerations, and peak drag load are provided.

Pressure tunnel investigation of supersonic store interference in vicinity of 22 degree swept wing fuselage configuration at Mach numbers 1.61 and 2.01.

Report presenting an investigation in the supersonic pressure tunnel at Mach numbers 1.61 and 2.01 in which separate forces and moments were measured on a store (with five components), on a 22 degree swept wing (three components), and on a 22 degree swept-wing-fuselage combination (three components) for a range of store positions.

Report presenting an investigation to determine the effectiveness of a leading-edge slat and a trailing-edge split flap in improving the high subsonic speed aerodynamic characteristics of a model of a wing-fuselage combination with a nearly triangular wing. Results regarding the effects of Reynolds number, effects of slats, and effects of flaps are provided.

Report presenting a free-flight investigation of the zero-lift control effectiveness of a steady-flow jet-spoiler roll control on a cruciform 80 degree delta-wing missile over a range of Mach numbers. Measurements were made of the rolling-moment, damping-in-roll derivative, drag, and pressures at the inlet and on the wing near the jet exit. Results indicated that the wing and jet combination magnified the thrust force of the isolated jet alone by factors of 11 at subsonic speeds to 3 at supersonic speeds.

Memorandum presenting a transonic flutter investigation of models of the all-movable horizontal tail of a fighter airplane in the transonic blowdown tunnel. The models were dynamically and elastically scaled by criteria which provide a flutter safety margin. Results regarding some general comments, simulated airplane tests, effects of pitch stiffness with rearward pitch axis, and effect of pitch-axis location are provided.

Report presenting an investigation of the transonic flutter characteristics of models of an all-movable horizontal tail of a fighter airplane. Results regarding simulated airplane tests, the effects of pitch stiffness with rearward pitch axis, and the effect of pitch-axis location are provided.

Report presenting a wind-tunnel investigation to determine the effectiveness of area suction in increasing the lift of a moderately thick straight wing encountering trailing-edge air flow separation. Results regarding a model with undeflected leading-edge flap and tip tanks on and a model with the tip tanks removed are provided.

Combustion blow-out velocities were determined for JP-4 solutions containing: (1) 10 % ethylene - decaborane reaction product, (2) 10% and 20% acetylene - diborane reaction product, and (3) 5.5%, 15.7%, and 30.7% methylacetylene - diborane reaction product. These were compared with blow-out velocities for JP-4, propylene oxide, and neohexane and previously reported data for JP-4 solutions of pentaborane. For those reaction products investigated, the blow-out velocities at a fixed equivalence ratio were higher for those materials containing higher boron concentrations; that is, blow-out velocity increased in the following order: (1) methylacetylene - diborane, (2) acetylene - diborane, and (3) ethylene - decaborane reaction products.

The heat of combustion of the product formed by the reaction acetylene and diborane was found to be 20,100 +/- 100 Btu per pound for the reaction of liquid fuel to gaseous carbon dioxide, gaseous water, and solid boric oxide. The measurements were made in a Parr oxygen-bomb calorimeter, and chemical analyses both of the sample and of the combustion products indicated combustion in the bomb calorimeter to have been 97 percent complete. The estimated net heat of combustion for complete combustion would therefore be 20,700 +/- 100 Btu per pound.