24 research outputs found
Effect of Boundary-layer Control and Inlet Lip Shape on the Performance of a Twin-scoop Air-induction System at Mach Numbers from 0 to 1.9
Effects of Leading-edge Chord Extensions and an All-movable Horizontal Tail on the Aerodynamic Characteristics of a Wing-body Combination Employing a Triangular Wing of Aspect Ratio 3 Mounted in a High Position at Subsonic and Supersonic Speeds
An Experimental Investigation at Mach Numbers from 2.1 to 3.0 of Circular-internal-contraction Inlets with Translating Centerbodies
Fuselage Side Inlets : a Study of Some Factors Affecting Their Performance and a Comparison with Nose Inlets
Experimental Investigation at Mach Numbers from 0 to 1.9 of Trapezoidal and Circular Side Inlets for a Fighter-type Airplane
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NACA Research Memorandums
Report presenting the results of an investigation at supersonic speeds to determine the aerodynamic characteristics of a model of the North American MX-770 missile at several designated Mach numbers. No analysis is provided. Information about the longitudinal aerodynamic characteristics with trimmer and elevon deflected and lateral aerodynamic characteristics are described
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NACA Research Memorandums
An experimental investigation was conducted to determine the performance characteristics an underslung nose-scoop air-induction system for a supersonic airplane. Five different nose shapes, three lip shapes, and two internal diffusers were investigated. Tests were made at Mach numbers from 0 to 1.9, angles of attack from 0 deg to approximately l5 deg, and mass-flow ratios from 0 to maximum obtainable. It was found that the underslung nose-scoop inlet was able to operate at Mach numbers from 0.6 to 1.9 over a large positive angle-of-attack range without adverse effects on the pressure recovery. Although there was no one inlet configuration that was markedly superior over the entire range of operating variables, the arrangement having a nose designed to give increased supersonic compression at low angles of attack, and a sharp lip (configuration designated N3L3) showed the most favorable performance characteristics over the supersonic Mach number range. Inlets with sizable lip radii gave satisfactory performance up to a Mach number of 1.5; however, as a result of an increase in drag, the performance of such inlets was markedly inferior to the sharp-lip configuration above Mach numbers of 1.5. Throughout the range of test Mach numbers all inlet configurations evidenced stable air-flow characteristics over the mass-flow range for normal engine operation. Analysis of the inlet performance on the basis of a propulsive thrust parameter showed that a fixed inlet area could be used for Mach numbers up to 1.5 with only a small sacrifice in performance