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  • 1
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    An aerodynamic analysis computer program and design notes for low speed wing flap systems (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The expanded capabilities for analysis and design of low speed flap systems afforded by recent modifications of an existing computer program is described. The program provides for the simultaneous analysis of up to 25 pairs of leading-edge and trailing-edge flap deflection schedules. Among other new features of the program are a revised attainable thrust estimation method to provide more accurate predictions for low Mach numbers, and a choice of three options for estimation of leading-edge separation vortex flow effects. Comparison of program results with low speed experimental data for an arrow wing supersonic cruise configuration with leading-edge and trailing-edge flaps showed good agreement over most of the range of flap deflections. Other force data comparisons and an independent study of airfoil and wing pressure distributions indicated that wind-tunnel measurements of the aerodynamic performance of twisted and cambered wings and wings with leading-edge flaps can be very sensitive to Reynolds number effects.
    Keywords: AERONAUTICS (GENERAL)
    Type: NASA-CR-3675 , NAS 1.26:3675
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Numerical methods and a computer program for subsonic and supersonic aerodynamic design and analysis of wings with attainable thrust considerations (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper describes methodology and an associated computer program for the design of wing lifting surfaces with attainable thrust taken into consideration. The approach is based on the determination of an optimum combination of a series of candidate surfaces rather than the more commonly used candidate loadings. Special leading-edge surfaces are selected to provide distributed leading-edge thrust forces which compensate for any failure to achieve the full theoretical leading-edge thrust, and a second series of general candidate surfaces is selected to minimize drag subject to constraints on the lift coefficient and, if desired, on the pitching moment coefficient. A primary purpose of the design approach is the introduction of attainable leading-edge thrust considerations so that relatively mild camber surfaces may be employed in the achievement of aerodynamic efficiencies comparable to those attainable if full theoretical leading-edge thrust could be achieved. The program provides an analysis as well as a design capability and is applicable to both subsonic and supersonic flow.
    Keywords: AERONAUTICS (GENERAL)
    Type: NASA-CR-3808 , NAS 1.26:3808
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Development and analysis of a STOL supersonic cruise fighter concept (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The application of advanced and emerging technologies to a fighter aircraft concept is described. The twin-boom fighter (TBF-1) relies on a two dimensional vectoring/reversing nozzle to provide STOL performance while also achieving efficient long range supersonic cruise. A key feature is that the propulsion package is placed so that the nozzle hinge line is near the aircraft center-of-gravity to allow large vector angles and, thus, provide large values of direct lift while minimizing the moments to be trimmed. The configurations name is derived from the long twin booms extending aft of the engine to the twin vertical tails which have a single horizontal tail mounted atop and between them. Technologies utilized were an advanced engine (1985 state-of-the-art), superplastic formed/diffusion bonded titanium structure, advanced controls/avionics/displays, supersonic wing design, and conformal weapons carriage. The integration of advanced technologies into this concept indicate that large gains in takeoff and landing performance, maneuver, acceleration, supersonic cruise speed, and range can be acieved relative to current fighter concepts.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-85777 , NAS 1.15:85777
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Aerodynamic Analysis of Low-Speed Wing-Flap Systems (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: SUBAERF program developed for aerodynamic analysis and design of lowspeed wing-flap systems. SUBAERF based on linearized theory lifting-surface solution. Low speed aerodynamic analysis method used in SUBAERF provides estimates of wing performance which include effects of attainable leading edge thrust and vortex lift.
    Keywords: MECHANICS
    Type: LAR-13116 , NASA Tech Briefs (ISSN 0145-319X); 8; 3; P. 386
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Manipulation and Display of Panel-Method Geometry (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: GEOM manipulates and displays any geometry data expressed in Hess format. Provides user with capability to manipulate, modify, and view such geometric configurations interactively. GEOM program and the PAGMS data-base management system written in FORTRAN IV.
    Keywords: MATHEMATICS AND INFORMATION SCIENCES
    Type: LAR-13224 , NASA Tech Briefs (ISSN 0145-319X); 9; 2; P. 164
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Design and analysis of a fuel-efficient single-engine, turboprop-powered, business airplane (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The speed, range, payload, and fuel efficiency of a general aviation airplane powered by one turboprop engine was determined and compared to a twin engine turboprop aircraft. An airplane configuration was developed which can carry six people for a noreserve range of 2,408 km at a cruise speed above 154 m/s, and a cruise altitude of about 9,144 m. The cruise speed is comparable to that of the fastest of the current twin turboprop powered airplanes. It is found that the airplane has a cruise specific range greater than all twin turboprop engine airplanes flying in its speed range and most twin piston engine airplanes flying at considerably slower cruise airspeeds.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-165768
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Aerodynamic design and analysis of the AST-204, AST-205, and AST-206 blended wing-fuse large supersonic transport configuration concepts (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The aerodynamic design and analysis of three blended wing-fuselage supersonic cruise configurations providing four, five, and six abreast seating was conducted using a previously designed supersonic cruise configuration as the baseline. The five abreast configuration was optimized for wave drag at a Mach number of 2.7. The four and six abreast configurations were also optimized at Mach 2.7, but with the added constraint that the majority of their structure be common with the five abreast configuration. Analysis of the three configurations indicated an improvement of 6.0, 7.5, and 7.7 percent in cruise lift-to-drag ratio over the baseline configuration for the four, five, and six abreast configurations, respectively.
    Keywords: AERODYNAMICS
    Type: NASA-CR-159223
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Wing Subsonic Aerodynamic Performance Estimates (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Solution by iteration estimates performance of twisted and cambered wings of arbitrary planform. SUBAER based on linearized theory lifting-surface solution provides spanwise distribution of theoretical leading edge thrust, in addition to surface distribution of perturbation velocities. Program written in FORTRAN IV.
    Keywords: MECHANICS
    Type: LAR-12987 , NASA Tech Briefs (ISSN 0145-319X); 7; P. 315
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    A computer program for wing subsonic aerodynamic performance estimates including attainable thrust and vortex lift effects (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Numerical methods incorporated into a computer program to provide estimates of the subsonic aerodynamic performance of twisted and cambered wings of arbitrary planform with attainable thrust and vortex lift considerations are described. The computational system is based on a linearized theory lifting surface solution which provides a spanwise distribution of theoretical leading edge thrust in addition to the surface distribution of perturbation velocities. The approach used relies on a solution by iteration. The method also features a superposition of independent solutions for a cambered and twisted wing and a flat wing of the same planform to provide, at little additional expense, results for a large number of angles of attack or lift coefficients. A previously developed method is employed to assess the portion of the theoretical thrust actually attainable and the portion that is felt as a vortex normal force.
    Keywords: AERONAUTICS (GENERAL)
    Type: NASA-CR-3515
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    A procedure for the determination of the effect of fuselage nose bluntness on the wave drag of supersonic cruise aircraft (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The incremental wave drag penalty due to nose blunting of a fuselage was investigated using a three dimensional finite difference scheme. An aircraft typical of current supersonic cruise concepts was considered. Computational problems with the finite difference scheme as the fuselage afterbody closes were addressed. A linear theory method was employed to compute the afterbody aerodynamics and effectively extends the finite difference scheme to closing afterbodies. Acceptable drag increments for various levels of nose bluntness were demonstrated using this approach.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145306
    Format: application/pdf
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