In the present study, an experimental platform is developed to study the behavior of the injected jet in a gas cross-flow applicable to different categories of fluid mechanics such as combustion. In all tests, water and air are used as jet and cross-flow gas, respectively. The main target of this work is to cover the higher range of momentum ratios and Weber numbers for the presentation of a more accurate equation for jet trajectory. To achieve a desirable scale of experiments, the range of momentum ratio is considered from 5 to 211 and the Weber number of gasses in all tests is between 1.1–19.1. For data mining and measurements, the shadowgraph method is used. It is shown that by increasing the momentum ratio (about 84%), the breakup point height is increased (about 94%). Three different types of breakups were observed in the tests. It observed that as the Weber number increases, the type of jet column mechanism changes. It also revealed that the type of breakup mechanism would not have a significant effect on the jet trajectory. In addition, it demonstrated that the momentum ratio parameter would have a decisive role in the direction of jet motion, and as the momentum ratio increases, the jet column height increases. Finally, an equation for the trajectory of jet flight under all test conditions is presented.

在本研究中，开发了一个实验平台来研究气体横流中喷射射流的行为，适用于燃烧等不同类别的流体力学。在所有测试中，水和空气分别用作喷射气体和错流气体。这项工作的主要目标是涵盖更高范围的动量比和韦伯数，以呈现更准确的射流轨迹方程。为了达到理想的实验规模，动量比的范围被认为是5到211，所有测试中气体的韦伯数在1.1到19.1之间。对于数据挖掘和测量，使用阴影图方法。结果表明，通过增加动量比（约 84%），破裂点高度会增加（约 94%）。在测试中观察到三种不同类型的分手。观察到随着韦伯数的增加，射流柱机构的类型发生变化。它还表明，破碎机制的类型不会对射流轨迹产生重大影响。此外，还证明了动量比参数对射流运动方向具有决定性作用，并且随着动量比的增加，射流柱高度增加。最后，给出了所有测试条件下喷气式飞机飞行轨迹的方程。喷射柱高度增加。最后，给出了所有测试条件下喷气式飞机飞行轨迹的方程。喷射柱高度增加。最后，给出了所有测试条件下喷气式飞机飞行轨迹的方程。