Flight conditions

Since the airflow rate induced into the air-intake is dependent on the flight speed and altitude of the projectile, the mixture ratio of air and fuel gas must be adjusted accordingly. In some cases, the mixture may be too air-rich or too fuel-rich to bum in the ramburner, falling outside of the flammability limit (see Section 3.4.3), and no ignition occurs (see Section 3.4.1). In order to optimize the combustion in the ramburner under various flight conditions, a variable flow-rate system is attached to the gas flow control system. 

Boron particles are incorporated into GAP pyrolants in order to increase their specific impulse.[8-i2] xhe adiabatic flame temperature and specific impulse of GAP pyrolants are shown as a function of air-to-fuel ratio in Fig. 15.10 and Fig. 15.11, respectively. In the performance calculation, a mixture of the combustion products of the pyrolant with air is assumed as the reactant. The enthalpy of the air varies according to the velocity of the vehicle (or the relative velocity of the air) and the flight altitude. The flight conditions are assumed to be a velocity of Mach 2.0 at sea level. An air enthalpy of 218.2 kj kg is then assumed. 

The FJ test is similar to an aerodynamic wind-turmel test used for supersonic aircraft, except for the airflow condition. A ducted rocket projectile is mounted on a thrust stand and the projectile and thmst stand are placed in a test chamber. A supersonic airflow simulating the flight conditions is suppHed to the projectile through a supersonic nozzle attached to the front-end of the test chamber. The pressure and temperature in the test chamber are kept equivalent to the flight alHtude conditions. The aerodynamic drag on the projectile and the thmst generated by the ducted rocket are measured directly by the FJ test. The airflow surrounding the projectile and the combustion gas expelled from the ramburner flow out from the exhaust pipe attached to the rear-end of the test chamber. 

MPa) under conditions of sea-level flight However, if no boron combustion occurs, the temperature decreases to 1550 K under the same flight conditions. The combustion efficiency of boron particles is an important parameter for obtaining high specific impulse of ducted rockets. 

Although several flowering populations were finally found during the winter of 1983-84, at no time was a legitimate pollinator observed visiting flowers. While poor flight conditions for Hymenoptera often prevailed, pollinators were also conspicuously absent during... 

The crux of testing will be suitability of the coating system under actual flight conditions. The coating system when applied to a vertical surface must maintain its integrity under operating vibration in the puffed or insulating form. 

Studies on the precopulatory behavior of males, at close range, have been reported and a basal level of male-to-male homosexual activity has been described (31). This work, however, will have to be re-examined under free-flight conditions especially in light of the possibile involvement of "short-range" pheromone components. 

The MIDAS model of the controller was developed using the rules of current and free-flight operation. Estimates and measured times for controllers performance on these tasks was input into the task descriptions. Here the interest was in how stable the system was to emergency conditions under current and free-flight conditions. The control scenario was focused on the handoff between... 

Perkins, R., Kaufman, L. and Nesor, H. Stability Characterization of Refractory Materials Under Velocity Atmospheric Flight Conditions, Experimental Results of High Velocity Cold Gas/Hot Wall Test, Part HI Vol. II, AFML-TR-68-84, ManLabs Inc., Cambridge, MA, (1969). 

Flight conditions <0 g No accepted standard data AMC25.1309 (Amdl, App 4) ... 

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