CARDC8米×6米风洞直升机旋翼机身组合模型试验台研制

本文简要介绍了气动中心低速所新近研制成功的8米×6米风洞直升机旋翼机身组合模型试验台的概况、主要分系统调试结果、BO-105直升机旋翼动力相似模型地面悬停试验及风洞试验结果。结果表明:试验台及各分系统的性能已达到设计要求;试验台振动水平低;工作可靠;风洞试验数据的重复性好;与西德宇航院飞行力学研究所在 DNW8米×6米风洞中的试验结果有良好的一致性。经地面试验及风洞试验的考核,试验台已具备交付验收和使用的条件。试验台的研制成功,为我国大型低速风洞开展直升机旋翼模型风洞试验奠定了坚实的基础。

DEVELOPMENT OF HELICOPTER ROTOR/FUSELAGE COMBINATION MODEL TEST STAND FOR CARDC 8m BY 6m WIND TUNNEL

This paper brief introduces a survey of the helicopterrotor/fuselage combination model test stand for CARDC 8m by 6m windtunnel,which has been newly successfully developed in CARDC LowSpeed Aerodynamics Research institute.And the results of calibrationsof main subsystems,ground tests and wind tunnel experiments withBO-105 helicopter model rotor dynamically scaled down are also pres-ented in it.The results show that the performance of the test stand andits subsystems meets the design requirements and it works reliably withlower vibration level.The data from wind tunnel experiments havegood repeatability and are coincident with those obtained by DLR/FMin DNW 8m by 6m wind tunnel.Having been checked via ground tests and wind tunnel experiments,the test stand is ready for acceptance and application.With the testapparatus successfully established,it makes it possible to perform heli-copter model rotor tests in the large low speed wind tunnel.