Variable mach number test method in supersonic free jet
A test method and Mach number technology, which is applied in the aerospace field, can solve the problems of higher requirements for the incoming flow speed, deceleration, speed reduction and airspace limit simulation ability of the hypersonic aircraft test, so as to prevent the complex optimization design platform from consuming a lot of calculation. Computing power, satisfying experimental requirements, and avoiding the effect of converging on local optimal solutions or singular solutions
Active Publication Date: 2022-08-09
NORTHWESTERN POLYTECHNICAL UNIV +1
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Problems solved by technology
However, the existence of the converging section of the wind tunnel nozzle leads to severe deceleration during the flow process, and re-acceleration in the expansion section, which reduces the speed and the limit simulation capability of the airspace, and at the same time requires higher flow velocity for hypersonic vehicle tests
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Embodiment 1
[0054]The invention provides a variable Mach number test method in a supersonic free jet, comprising the following steps:
[0055] Step 1. Select a double-wall rotary Mach number test device containing only the expansion section, and place the test piece at the axis of the test section of the double-wall rotary Mach number test device;
[0056] Step 2. Set the size of the free jet area, the size of the core area of the flow field and the length of the expansion section of the double-wall rotary variable Mach number test device;
[0057] Step 3. Based on the size of the core area of the flow field as 2 / 3 of the flow field area of the test section, obtain the width of the test section, that is, the outlet width of the expansion section of the intake port;
[0058] Step 4. Based on the simulation target parameters, select design variables to flow velocity Ma s and the target flight altitude H t , the area expansion ratio of the flow channel is obtained. Since the real fl...
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The invention discloses a variable Mach number test method in supersonic free jet, relates to the technical field of aerospace, and the designed test device can realize wide-range, continuous and rapid change of the Mach number of a uniform region of a flow field and meet the test requirements of a supersonic aircraft. Meanwhile, adjustment is easy, and no new wave system or wake flow disturbance is generated in the adjustment process. The design of the device only comprising the expansion section improves the utilization efficiency of the incoming flow of the free jet flow, and improves the speed of the variable Mach number test device and the limit simulation capability of the airspace at the same time. On the premise that basic parameters are selected, a direct optimization algorithm can be adopted to calculate the optimized device inner profile, it is prevented that a large amount of calculation power is consumed for calculation of a complex optimization design platform of the variable Mach number adjustable wind tunnel nozzle profile, and meanwhile it is avoided that multiple design variables are converged to a local optimal solution or a singular solution in the optimization process.
Description
technical field [0001] The invention relates to the technical field of aerospace, in particular to a variable Mach number test method in a supersonic free jet. Background technique [0002] With the rapid development of the aerospace field, the speed of various aircraft such as rockets and airplanes has increased rapidly, which has brought new challenges to the test link in the development process. The commonly used aerodynamic tests mainly include wind tunnel tests and free flight tests. The wind tunnel test can control the experimental conditions more accurately, and its equipment is easy to install and operate, with high precision and low cost, and has been widely used; the free flight test can simulate the flight process more realistically and obtain the dynamic parameters of the test. [0003] However, due to the rapid development of the aircraft and the corresponding propulsion system in the continuous change of Mach number, the problems have gradually been exposed, a...
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IPC IPC(8): G01M9/04G01M9/06G06F30/20
CPCG01M9/04G01M9/067G06F30/20Y02T90/00
Inventor 魏然陈载成谢波涛李露张晨辉张传侠孙林刘旸惠卫华鲍福廷
Owner NORTHWESTERN POLYTECHNICAL UNIV