## Calculation of Three-dimensional, Inviscid Supersonic, Steady FlowsNational Aeronautics and Space Administration, Scientific and Technical Information Office, 1982 - Aerodynamics, Supersonic |

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### Contents

Equations of motion | 9 |

Characteristic equation for body and shock points | 17 |

General outline of one integration step | 26 |

7 other sections not shown

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### Common terms and phrases

accuracy airplane angle of attack attached shock body and shock body geometry body points bY/b calculation cambered wing characteristic equations circular cone circumferential intervals computational grid conformal mapping conical flow constant corrector stage cross-section defined derivatives determined elliptic cone entropy equations of motion Euler's equations evaluated follows fuselage fuselage-arrow wing combinations g-plane geometry subroutine grid points Hm ZDm hollow intake imbedded shocks input value integration intervals are doubled isobar plots leeward side mapping function non-dimensional Note obtained Pandolfi predictor stage procedure radial intervals Rankine-Hugoniot equations respectively results on fuselage-arrow Round-off errors scheme shock and body shock layer shown in Fig stagnation point step stream Mach number stretching parameter supersonic t-derivatives tion Trailing edge unit vector updated upwind value of cT velocity component windward windward and leeward wing combinations RUN wwwm zero ZJ+1