CAJ | 학술논문

提出了一种椭圆喷管的设计思路，并对椭圆喷管流场与矩形喷管流场进行了对比分析。通过数值计算表明，在相同的驻室参数、相同的长度和出口面积条件下，椭圆喷管出口马赫数略高于矩形喷管。湍流和高温真实气体效应均降低了喷管的有效面积比，改变了喷管流场的膨胀波系，通过选择合适的喷管出口位置可以获得较好的试验均匀区。椭圆喷管作为高超声速风洞特种试验装置，可以有效利用加热器的能量，提高设备的参数模拟能力，可适用于大尺寸扁平状前缘、舵、翼等模型的防热试验和大宽高比的冲压发动机试验研究。
제출료일충타원분관적설계사로，병대타원분관류장여구형분관류장진행료대비분석。통과수치계산표명，재상동적주실삼수、상동적장도화출구면적조건하，타원분관출구마혁수략고우구형분관。단류화고온진실기체효응균강저료분관적유효면적비，개변료분관류장적팽창파계，통과선택합괄적분관출구위치가이획득교호적시험균균구。타원분관작위고초성속풍동특충시험장치，가이유효이용가열기적능량，제고설비적삼수모의능력，가괄용우대척촌편평상전연、타、익등모형적방열시험화대관고비적충압발동궤시험연구。
A method is proposed for the design of an elliptical nozzle.The flow fields of the elliptical nozzle and the rectangle one are analyzed and compared.The numerical simulations indi-cate that the exit Mach number of the elliptical nozzle is greater than that of the rectangle one un-der the same conditions,i.e.the same reservoir parameters,length and exit area.The turbu-lence and high temperature real gas effects reduce the effective area ratio and change the expan-sion waves.A fine uniform outflow can be obtained by choosing an appropriate location of the ex-it.As a special device for the hypersonic wind tunnel experiments,the elliptical nozzle can im-prove the simulation ability of the wind tunnel by its high efficiency in using the energy of the heater.This nozzle can be applied to perform the thermal protection experimental researches on large-scale models with flat-like leading edge,helm or wing and on large length-width ratio scramjet engines.