Analysis of sonic boom measurements near shock wave extremities for flight near Mach 1.0 and for airplane accelerations
A method is developed to determine the flow field of a body of revolution in separated flow. The computer was used to integrate various solutions and solution properties of the sub-flow fields which made up the entire flow field without resorting to a finite difference solution to the complete Navier-Stokes equations. The technique entails the use of the unsteady cross flow analogy and a new solution to the two-dimensional unsteady separated flow problem based upon an unsteady, discrete-vorticity wake. Data for the forces and moments on aerodynamic bodies at low speeds and high angle of attack (outside the range of linear inviscid theories) such that the flow is substantially separated are produced which compare well with experimental data. In addition, three dimensional steady separated regions and wake vortex patterns are determined. The computer program developed to perform the numerical calculations is described.
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ANALYSIS OF NEARSONIC FLIGHT TEST DATA
ANALYSIS OF SAFETY FACTOR DURING THRESHOLD MACH NUMBER FLIGHT
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acceleration magnitude airplane acceleration airplane altitude airplane ground speed airplane Mach number analysis APmax atmosphere attached shock waves beneath the airplane BOW SHOCK BREN tower CALCULATED SHOCK FRONTS calculated shock wave caustic intensity caustics produced caustics were produced climb angle DISTANCE FROM TOWER effect of acceleration equation flight path flights at Mach ft/sec given in figure ground reflection increasing lapse rate LOW-ALTITUDE NEAR-SONIC FLIGHT low-magnitude accelerations m/sec MACH NUMBER FLIGHT Machmeter magnitude on caustic maneuver maximum overpressure measured meteorological conditions microphone T-l NASA nondimensionalized Nonlinear Acoustic observed pressure signatures PRESSURE SIGN pressure waves PROFILES FOR PASS pullup rumbles shock Mach number shock propagation speed shock wave extremity shock wave profiles SIGN A TURES sonic boom cutoff speed safety factor supersonic tailwind temperature and wind temperature inversion theoretical safe altitude threshold Mach number tower microphone tower top trailing shocks TURES FOR PASS U-wave un(z uptrack wind gradients wind speed