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  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (6)
  • 1
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    SEEB-MINIMIZATION OF SONIC-BOOM PARAMETERS IN REAL AND ISOTHERMAL ATMOSPHERES (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: For prescribed aircraft flight conditions of weight, length, Mach number and altitude, and front area balance point this program calculates the Whitman F function and the corresponding equivalent area distribution that minimize over pressure or minimum shock pressure signature utilizing the method of Seebass and George (Cornell University). The solution procedure is based upon equations for (1) the total area growth necessary for flight conditions, (2) location of the front area balancing point, (3) location of the rear area balancing point, (4) ratio of the front to rear shock, and (5) the intersection of the F function with the rear area balancing line at the rear balancing point. These five equations reduce to nonlinear equations in two unknowns which are solved iteratively using the Newton-Raphson method and a combination of the secant and bisection methods. The program is written in CDC FORTRAN IV (Version 2.3) and has been implemented on a CDC 6600 computer under the SCOPE operating system with a memory requirement of approximately 110K (octal) of 60 bit words.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: LAR-11979
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Comparison of sonic boom minimization results in real and isothermal atmospheres (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The method of Seebass and George (1972, 1974) for minimizing certain features of the pressure signature and yielding the corresponding F function and equivalent area distribution A in an isothermal atmosphere is modified to provide the same capability for a real atmosphere. The appropriate equations of George and Plotkin (1969) describing horizontal advance, ray tube area, and signature propagation are used.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft; 12; May 1975
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Wing design with attainable leading-edge thrust considerations (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft (ISSN 0021-8669); 22; 244-248
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Wing design with attainable thrust considerations (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A CAD process that includes leading-edge thrust considerations for wings with high aerodynamic efficiencies is outlined. Rectangular grids are used for evaluation of both subsonic and supersonic pressure loadings. Account is taken of the Mach number, Re, the wing planform, the presence of camber, the airfoil geometry and the locations and forces induced by shed vortices. Optimization techniques are applied to the candidate surfaces in order to consider the attainable thrust. Inclusion of the optimization techniques permits analyses of mission-adaptive wings and various flap systems and the elimination of singularities in the flight envelope.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 84-2194
    Format: text
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  • 5
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    Minimization of sonic-boom parameters in real and isothermal atmospheres (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The procedure for sonic-boom minimization introduced by Seebass and George for an isothermal atmosphere was converted for use in the real atmosphere by means of the appropriate equations for sonic-boom pressure signature advance, ray-tube area, and acoustic impedance. Results of calculations using both atmospheres indicate that except for low Mach numbers or high altitudes, the isothermal atmosphere with a scale height of 7620 m (25 000 ft) gives a reasonable estimate of the values of overpressure, impulse, and characteristic overpressure obtained by using the real atmosphere. The results also show that for aircraft design studies, propagation of a known F-function, or minimization studies at low supersonic Mach numbers, the isothermal approximation is not adequate.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TN-D-7842 , L-9810
    Format: application/pdf
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  • 6
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    Some effects of applying sonic boom minimization to supersonic cruise aircraft design (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper presents a discussion of an aircraft shaping method to control sonic boom over-pressure levels along with the analysis of wind-tunnel data which validated the method. The results indicate that the sonic boom minimization method can guide the design team choices of aircraft planform and component arrangement toward a low-boom-level configuration while permitting sufficient freedom and flexibility to satisfy other design criteria. Further, it is shown that off-design flight conditions do not drastically change the overpressure sonic boom shape and strength.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 79-0652 , American Institute of Aeronautics and Astronautics, Aeroacoustics Conference; Mar 12, 1979 - Mar 14, 1979; Seattle, WA
    Format: text
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    NASA TECHNICAL REPORTS
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