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  • 1
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    Unknown
    Geometries for roughness shapes in laminar flow (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A passive interface mechanism between upper and lower skin structures, and a leading edge structure of a laminar flow airfoil is described. The interface mechanism takes many shapes. All are designed to be different than the sharp orthogonal arrangement prevalent in the prior art. The shapes of the interface structures are generally of two types: steps away from the centerline of the airfoil with a sloping surface directed toward the trailing edge and, the other design has a gap before the sloping surface. By properly shaping the step, the critical step height is increased by more than 50% over the orthogonal edged step.
    Keywords: AERODYNAMICS
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    A study of altitude-constrained supersonic cruise transport concepts (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The effect of restricting maximum cruise altitude on the mission performance of two supersonic transport concepts across a selection of cruise Mach numbers is studied. Results indicate that a trapezoidal wing concept can be competitive with an arrow wing depending on the altitude and Mach number constraints imposed. The higher wing loading of trapezoidal wing configurations gives them an appreciably lower average cruise altitude than the lower wing loading of the arrow wing configurations, and this advantage increases as the maximum allowable cruise altitude is reduced.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 92-1027
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    The influence of subsonic mission segments on the use of variable-sweep wings for high speed civil transport configurations (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A Mach-3.0, 250-passenger, 6500-n. mi. range SST configuration's alternative use of fixed-planform or variable-sweep wings is presently evaluated, with a view to effects on aerodynamics, mission performance, and sizing. After preliminary design, the fixed and variable-wing configurations were resized to perform missions incorporating subsonic cruise segments of as much as 4000 n. mi.; the effect of subsonic segment length on design gross weight and block time was then ascertained. Due to the reduced supersonic efficiency of the variable-sweep aircraft, over one-half of the 6500-n. mi. mission would have to be flown subsonically for its sizing to reach a lower ramp weight than that of its fixed-geometry counterpart.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 88-4470
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Concept development of a Mach 3.0 high-speed civil transport (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A baseline concept for a Mach 3.0 high-speed civil transport concept was developed as part of a national program with the goal that concepts and technologies be developed which will enable an effective long-range high-speed civil transport system. The Mach 3.0 concept reported represents an aggressive application of advanced technology to achieve the design goals. The level of technology is generally considered to be that which could have a demonstrated availability date of 1995 to 2000. The results indicate that aircraft are technically feasible that could carry 250 passengers at Mach 3.0 cruise for a 6500 nautical mile range at a size, weight and performance level that allows it to fit into the existing world airport structure. The details of the configuration development, aerodynamic design, propulsion system design and integration, mass properties, mission performance, and sizing are presented.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-4058 , L-16445 , NAS 1.15:4058
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    A comparison of arrow, trapezoidal and M wing concepts using a Mach 2 supersonic cruise transport mission (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The present analytic study of the potential performance of SST configurations radically differing from arrow-winged designs in lifting surface planform geometry gives attention to trapezoidal-wing and M-wing configurations; the trapezoidal wing is used as the baseline in the performance comparisons. The design mission was all-supersonic (Mach 2), carrying 248 passengers over a 5500 nautical-mile range. Design constraints encompassed approach speed, TO&L field length, and engine-out second-segment climb and missed-approach performance. Techniques for improving these configurations are discussed.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-3102
    Format: text
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