Report presenting a compilation of most of the zero-lift drag obtained from free-flight measurements on fin-stabilized bodies of revolution. Results regarding friction drag, base pressure and base drag, pressures on a forward facing step, and fin pressure drag are provided.

Report presenting development tests on a model of the Republic F-105 airplane at a Mach number of 0.20. The purpose of the current investigation is to obtain the longitudinal force and moment characteristics of the model equipped with trailing-edge flaps of various spans and deflections. Results regarding the longitudinal stability characteristics and effect of the horizontal tail are provided.

Report presenting an investigation of the aerodynamic characteristics of several plate- and bell-type outlets discharging air into a transonic stream. The variation in discharge coefficient of the outlets is presented as a function of the rate of discharge. The discharge coefficient, jet wake, and surface pressure distribution are also provided.

Report presenting an investigation in the transonic tunnel of the aerodynamic characteristics of a scale model of an X-1 airplane in order to correlate wing pressure-distribution results obtained in a slotted wind tunnel with flight test data on the full-scale airplane. Results regarding basic pressure measurements, and correlation of pressure measurements are provided.

Comparisons of the shock phenomena and drag-rise increments for representative wing and central-body combinations with those for bodies of revolution with the same axial distributions of cross-sectional area normal to the air stream. An investigation was also presented of representative wing-body combinations with the body so indented that the axial distributions of cross-sectional areas for the combinations were the same as that for the original body. Results regarding unswept wing and cylindrical body, delta wing and cylindrical body, swept wing and cylindrical body, swept wing and curved body, and applications of the transonic drag-rise concept are provided.

From Introduction: "Problems associated with the use of aluminum borohydride for ignition in aircraft are discussed. A detailed description of its properties and results of static chamber tests to determine the effect of diluting aluminum borohydride with n-pentane on flammability in dry air are included in this investigation."

Report presenting drag coefficients during power-off transonic flight for the Bell X-1 airplane with a 10-percent-thick wing over a range of Mach numbers and pressure altitudes. The data was compared to an X-1 with an 8-percent-thick wing and a wind tunnel test with a 10-percent-thick wing. Information about necessary angle of attack, drag-rise Mach number, maximum lift-drag ratio, and drag coefficient at zero lift is provided.

Memorandum presenting development tests on a scale model of the Republic F-105 airplane in the 19-foot pressure tunnel. The second phase, which is presented in this report, was made at a Reynolds number of 9.0 x 10(exp 6) and a Mach number of 0.20. The purpose of the tests was to obtain the longitudinal force and moment characteristics of the model equipped with trailing-edge flaps of various spans and deflections.

A series of flight tests have been made at the Langley Flight Research Division at the request of the Bureau of Aeronautics, Department of the Navy, to determine the flying qualities of the Grumman F8F-1 air- plane. This paper presents the test results necessary to determine the longitudinal stability and control characteristics end the stalling characteristics. The range of Mach numbers covered in this investigation was approximately 0.10 to 0.62, and no attempt was made to investigate compressibility effects at higher Mach numbers.

"Knock-limited performance data were obtained for three fuels on an R-1830-75 engine in a B-24D airplane at engine speeds of 1800, 2250, and 2600 rpm, a spark advance of 25 degrees B.T.C., and carburetor-air temperatures of 85 F for 1800 and 2250 rpm and 100 F for 2600 rpm. The test fuels were a blend of 80 percent 28-R plus 20 percent triptane (leaded to 4.5 ml TEL/gal), a blend of 80 percent 28-R plus 15 percent toluene (leaded to 4.5 ml TEL / gal), and 28-R fuel. The knock-limited manifold pressure of the toluene blend depreciated more in the lean region than the triptane blend or 28-R fuel" (p. 1).