Span Load Distributions Resulting from Angle of Attack, Rolling, and Pitching for Tapered Sweptback Wings with Streamwise Tips PDF Download
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Author: John C. Martin Publisher: ISBN: Category : Airplanes Languages : en Pages : 143
Book Description
On the basis of the linearized supersonic-flow theory the span load distributions resulting from constant angle of attack, from steady rolling, and from steady pitching were calculated for a series of thin sweptback tapered wings with streamwise tips and with supersonic leading and trailing edges. The results are valid for the Mach number range for which the Mach line from either wing tip does not intersect the remote half-wing. The results of this analysis are presented as a series of design charts. Some illustrative variations of the spanwise distributions of circulation with the various design parameters are also presented.
Author: John C. Martin Publisher: ISBN: Category : Airplanes Languages : en Pages : 143
Book Description
On the basis of the linearized supersonic-flow theory the span load distributions resulting from constant angle of attack, from steady rolling, and from steady pitching were calculated for a series of thin sweptback tapered wings with streamwise tips and with supersonic leading and trailing edges. The results are valid for the Mach number range for which the Mach line from either wing tip does not intersect the remote half-wing. The results of this analysis are presented as a series of design charts. Some illustrative variations of the spanwise distributions of circulation with the various design parameters are also presented.
Author: John C. Martin Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 143
Book Description
On the basis of the linearized supersonic-flow theory the span load distributions resulting from constsnt angle of attack, from steady rolling and from steady pitching were calculated for a series of thin sweptback tempered wings with streamwise tips and with supersonic leading and trailing edges. The results are valid for the Mach number range for which the Mach line from either wing tip does not intersect the remote half-wing. The results of the analysis are presented as a series of design charts. Some illustrative variations of the spanwise distribution of circulation with the various design parameters are also presented.
Author: Publisher: ISBN: Category : Languages : en Pages : 224
Book Description
On the basis of linearized supersonic-flow theory, the theoretical spanwise distributions of circulation (which are proportional to the span load distributions) resulting from constant angle of attack, steady rolling velocity, steady pitching velocity, and constant vertical acceleration were calculated for a series of thin, sweptback, tapered wings with streamwise tips. The analysis is valid at those speeds for which the wing is wholly contained between the Mach cones springing from the wing apex and the trailing edge of the root section, that is, subsonic leading edges and supersonic trailing edges. An added restriction is that the Mach cones emanating from the leading edges of the wing tips must not intersect on the wing. Formulas for the spanwise distributions of circulation are given in closed form. Numerical results are presented as a series of design charts from which the desired loading may be obtained for given values of aspect ratio, taper ratio, Mach number, and leading-edge sweepback. The axis of pitch is taken at the wing apex although, by use of the calculated results and a simple transformation, span load distributions for steady pitching velocity may be readily obtained for arbitrary location of the pitch axis. Variations of the spanwise distributions of circulation with the various plan-form parameters, Mach number, and axis-of-pitch location are also presented for illustrative purposes.
Author: Publisher: ISBN: Category : Languages : en Pages : 0
Book Description
On the basis of linearized supersonic-flow theory, the theoretical spanwise distributions of circulation (which are proportional to the span load distributions) resulting from constant angle of attack, steady rolling velocity, steady pitching velocity, and constant vertical acceleration were calculated for a series of thin, sweptback, tapered wings with streamwise tips. The analysis is valid at those speeds for which the wing is wholly contained between the Mach cones springing from the wing apex and the trailing edge of the root section, that is, subsonic leading edges and supersonic trailing edges. An added restriction is that the Mach cones emanating from the leading edges of the wing tips must not intersect on the wing. Formulas for the spanwise distributions of circulation are given in closed form. Numerical results are presented as a series of design charts from which the desired loading may be obtained for given values of aspect ratio, taper ratio, Mach number, and leading-edge sweepback. The axis of pitch is taken at the wing apex although, by use of the calculated results and a simple transformation, span load distributions for steady pitching velocity may be readily obtained for arbitrary location of the pitch axis. Variations of the spanwise distributions of circulation with the various plan-form parameters, Mach number, and axis-of-pitch location are also presented for illustrative purposes.
Author: Richard H. MacNeal Publisher: ISBN: Category : Airplanes Languages : en Pages : 786
Book Description
Deflections and all internal forces have been calculated for concentrated static loads. Vibration modes are also presented. The effects of neglecting shearing strains in the ribs and spars and also of assuming the ribs to be rigid have been investigated by modifying the electric circuits to correspond to these simplifications.
Author: Frankie Gale Moore Publisher: ISBN: Category : Aerodynamic heating Languages : en Pages : 168
Book Description
New and improved version of the Naval Surface Warfare Center, Dahlgren Division aeroprediction code (AP93) has been developed. The new code contains new technology that allows planar aerodynamics of axisymmetric solid rocket-type weapons to be computed with engineering accurately over the entire Mach number range and for angles of attack to 30 deg. New technology developed and included in the AP93 includes; A new engineering method to compute aeroheating information at a high Mach number; Extension of the second-order shock-expansion theory to include real-gas effects, including several new pressure prediction techniques; An improved body-alone nonlinear normal-force method; New methods for computing nonlinear aerodynamics of wing alone, wing body, and body wing due to angle of attack, and wing body due to control deflection; and a new base-dmg database and improved empirical base-drag estimation technique. ... Aeroprediction code (AP93), Planar aerodynamics, High mach number.
Author: John C. Martin
Author: John C. Martin
Author: John C. Martin
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Author: United States. National Advisory Committee for Aeronautics
Author: Richard H. MacNeal
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Author: Frankie Gale Moore
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