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comparison, these calculations were also done using the Aerodynamic Preliminary
Analysis System (APAS)8 and the APAS-results are included in Figs. 3.60 and 3.61.
The APAS is an interactive, graphic user interface program for preliminary
aerodynamic analyses of airplane-type configurations.lt uses slender body theory
for subsonic/supersonic modeling of the fuselage. The surface singularity/panel
methods are used for wing and tail surfaces at subsonic/supersonic speeds. The
interference effects between fuselage ancl wing and between fuselage and tail
surfaces are modeled using a cylindricalinterference shell enveloping the fuselage.
The analysis for subsonic/supersonic Mach numbers is performed by the unified
distributed panel (UDP) program. For hypersoruc Mach numbers, APAS uses the
hypersonic arbitrary body program (HABP).
Fig. 3.60 Variahon oflif:t-curve slope of the generic taiUess airplane.
STATIC'STABILITY AND CONTROL
@
-O.Ol
OES -0.02
-0.03
-0.04
I I . . . I -+~+-*-+
┏━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━━┓
┃ . . . -+-._+_ ---?-- ┃
┃ . . _sz-.t-r: ┃
┃ esent Calculation ┃
┃-.. 'o' ....' ":. .. . ... :;;;1;;:, 7rA~sAfS:;.. . . . . . . . .' . . . . . . . .. . - ┃
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