Report presenting an investigation to determine the high altitude performance of the J57-P-1 turbojet engine and components conducted at the NACA Lewis altitude wind tunnel. Four conditions were tested: engine operation with both the compressor bleed ports closed, with the large compressor bleed port open, with both compressor bleed ports open, and normal engine operation with the automatic control.

Report discussing the performance of a 20-inch-diameter ram-jet engine at Mach number 3.0 over a range of simulated altitudes from 60,500 to 66,500 feet. Information about the maximum combustor efficiency, range of exhaust-nozzle total pressures, lean blow-out, diffuser total-pressure recovery, and internal thrust coefficient is provided.

Report presenting an investigation of the performance of a 20-inch-diameter ram-jet engine at Mach number 3.0 in a free-jet facility over a range of simulated altitudes. Results regarding the diffuser characteristics, combustor performance, thrust output, and operational characteristics are provided.

Report presents the correlation of extensive data obtained relating properties of wrought N-155 alloy under static, combined static and dynamic, and complete reversed dynamic stress conditions. Time period for fracture ranged from 50 to 500 hours at room temperature, 1,000 degrees, 1,200 degrees, and 1,500 degrees F.

Memorandum summarizing the lift and drag characteristics of a series of five low-aspect-ratio triangular-wing or modified triangular-wing airplane models. The series consists of three triangular wings of aspect ratios 2, 3, and 4 and two modified triangular wings of aspect ratio 2 with taper ratios of 0.20 and 0.33. The experimental lift and drag characteristics of the five models are compared with existing theory.

Report presenting pressure distributions, wake measurements, and tuft patterns for wings with 30 and 45 degrees of sweepback in conjunction with a midwing fuselage at Mach numbers to 0.96. The wings have an NACA 65-210 section, a taper ratio of 2.6:1, and aspect ratios of 7.5 and 5.2. The study indicated that when the Mach number reached high subsonic values at low angles of attack, the locations of peak negative pressure coefficients on the upper surfaces of the sections near the wing-fuselage junctures shifted rearward.

Report presenting pressure distributions and wake measurements for wings with 30 and 45 degrees of sweepforward, in conjunction with a midwing fuselage, at Mach numbers up to 0.96. The wings had an NACA 65-210 section, a taper ratio of 0.38, and aspect ratios of 7.5 and 5.2. Results regarding pressure distributions, wake measurements, and corrections are provided.

Report presenting the vibration characteristics of several symmetrical ball-root-type blades simulating the mass and natural frequency of axial-flow-compressor blades under various mounting conditions by subjecting them to controlled periodic excitation and centrifugal loading. Results regarding loose single ball-root mounting, loose-lubricated, single ball-root mounting, double ball-root mounting, and damping measurements are provided.

From Introduction: "Thrust augmentation of an axial-flow-type turbojet engine by burning fuel in the tail pipe is discussed in references 1 to 3. Thrust augmentation of the same turbojet engine by water injection at the compressor inlet is reported in reference 4."

Report presenting the results of pitching-moment, lift, and drag measurements on a model of the D-558-1 with speed reduction brakes and a symmetrical profile wing at a range of Mach numbers. Only a small decrement in Mach number is produced with no nose-inlet flow and the speed-reduction brakes deflected.

"Unsteady-lift functions for wings of finite aspect ratio have been calculated by correcting the aerodynamic inertia and the angle of attack of the infinite wing. The calculations are based on the operational method. The starting lift of the finite wing is found to be only slightly less than that of the infinite wing; whereas the final lift may be considerably less" (p. 1).

"The effect on the take-off performance of a model of the hull of a typical flying boat, Navy PH-1, of fitting spray strips of four different widths, each at three different angles, was determined by model tests in the NACA Tank. Spray strips of widths up to 3 percent of the beam improve the general performance at speeds near the hump and reduce the spray thrown. A downward angle of 30 degrees to 45 degrees in the neighborhood of the step seems most favorable for the reduction of the spray" (p. 523).