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描述了有类似Ｅｒｉｃｋｓｏｎ前体的非常规机身的初步流动显示研究结果，包括测力、表面油流和激光片光流动显示结果和用层流Ｎ－Ｓ方程进行数值模拟的结果。计算和试验的参数范围：α＝０°～５０°，β＝０°～２０°，虽然计算与试验所用的外形在后部有一些不同，但是两者在涡的位置方面显示了良好的一致性。同时研究也表明，大攻角的流动特性可以通过改变机身前体形状进行控制。通过研究还表明，这类前体在改善大攻角横侧方向安定性方面具有很大的潜力。
The results of initial flow studies on unconventional airframes with similar Erickson precursors are described, including results of force measurement, surface oil flow, and laser light flow and numerical simulations using laminar flow N-S equations. The calculated and experimental parameters range: α = 0 ° to 50 ° and β = 0 ° to 20 °, although the calculated and experimental profiles are somewhat different at the back but both show good agreement in the vortex position Sex. At the same time, research also shows that the flow characteristics at high angles of attack can be controlled by changing the shape of the fuselage precursor. Studies have also shown that such precursors have great potential for improving lateral stability at high angles of attack.