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  • 1
    Electronic Resource
    Electronic Resource
    Interaction of a jet with a plane boundary located normal to the jet axis (1972)
    Springer
    Journal of engineering physics and thermophysics 22 (1972), S. 34-40 
    Details
    ISSN: 1573-871X
    Source: Springer Online Journal Archives 1860-2000
    Topics: Physics
    Notes: Abstract The interaction of plane and axiosymmetric subsonic jets with a plane boundary located normal to the jet axis is studied. A numerical solution for the equations of motion and energy is obtained, assuming stationary flow and constancy of liquid properties.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00838376
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Estimation of aerodynamic forces and moments on a steadily spinning airplane (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A semiempirical method is presented for the estimation of aerodynamic forces and moments on a steadily rotating airplane model in a spin tunnel. The approach is based on the application of strip theory to determine a part of the aerodynamic coefficient (including rotational velocity) and then estimation of increments to these coefficients because of rotational flow over the stalled airplane. The theory is applied to a light, single-engine, general aviation airplane and the results are compared with the corresponding spin tunnel rotary balance test data.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Journal of Aircraft (ISSN 0021-8669); 21; 943-954
    Format: text
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  • 3
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    On the impingement of supersonic jet on a normal flat surface (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: An improved method, based on one strip approximation of the method of integral relations which was reported originally by Belov, Ginzburg and Shub (1973), is presented for the calculation of flow parameters in the impingement region of a supersonic, underexpanded jet striking a normal surface located within the first cell. The results are presented for two impingement conditions and found to be in good agreement with the experimental data.
    Keywords: AERODYNAMICS
    Type: Aeronautical Quarterly; 33; Aug. 198
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Forebody drag reduction (1981)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: It is shown that the mechanisms of forebody drag reduction by means of either a spike or a forward-facing jet are similar, with the maximum achievable drag reduction being of the same order. Because the jet may be a relatively cool gas, however, the forward facing jet has the additional capability of reducing the aerodynamic heating that is so severe at high Mach numbers. By means of the correlation presented, jet ejection parameters may be chosen to achieve maximum permissible forebody drag reduction. The correlation method uses a momentum coefficient that characterizes jet efflux and freestream conditions.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Oct. 198
    Format: text
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  • 5
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    Estimation of parameters involved in high angle-of-attack aerodynamic theory using spin flight test data (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The difficulty in applying parameter estimation techniques to spinning airplanes is due in part to the unwieldy number of possible combinations of terms in the equations of motion, when the model structure is unknown. The combination of high angle of attack and high rotation rate results in aerodynamic functions which are quite complex. For wing dominated configurations it is advantageous to use aerodynamic theory to generate the model structure. In this way, the number of unknown parameters is reduced and the model accuracy may be increased. Under conditions for which the theory is inadequate, however, model accuracy may be reduced. Strip theory, for example, is incapable of predicting autorotative rolling moments indicated by wind tunnel tests at angles of attack exceeding 40 degrees. An improved aerodynamic theory would be necessary to successfully apply the technique advanced for such regions.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 83-2086
    Format: text
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  • 6
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    An evaluation of aerodynamics modeling of spinning light airplanes (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper extends the application of the modified strip theory for wing body combination of a spinning light airplane reported earlier. In addition, to account for the contribution of the tail plane, the shielding effect on vertical tail under steady state spin condition is modeled from basic aerodynamic considerations. The results of this combined analysis, presented for some light airplane configurations, are shown to be in good agreement with spin tunnel rotary balance test data.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 83-0368 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 10, 1983 - Jan 13, 1983; Reno, NV
    Format: text
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  • 7
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    On the prediction of auto-rotational characteristics of light airplane fuselages (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A semi-empirical theory is presented for the estimation of aerodynamic forces and moments acting on a steadily rotating (spinning) airplane fuselage, with a particular emphasis on the prediction of its auto-rotational behavior. This approach is based on an extension of the available analytical methods for high angle of attack and side-slip and then coupling this procedure with strip theory for application to a rotating airplane fuselage. The analysis is applied to the fuselage of a light general aviation airplane and the results are shown to be in fair agreement with experimental data.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 84-2112
    Format: text
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  • 8
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    An estimation of aerodynamic forces and moments on an airplane model under steady state spin conditions (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The problem of estimating the aerodynamic characteristics of a wing body configuration of a spinning airplane at extreme angles of attack and spin rates is approached by the application of strip theory. Semiempirical methods are used to estimate the aerodynamic force distributions over each component using static, nonrotational wind-tunnel test data. To these predictions, corrections are applied to account for the primary rotational flow effects which are significant at large spin rates. The results of this modified strip theory are shown to be in good agreement with spin tunnel rotary balance test data.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 82-1311 , Atmospheric Flight Mechanics Conference; Aug 09, 1982 - Aug 11, 1982; San Diego, CA
    Format: text
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