2.4 m暂冲型跨声速风洞大飞机试验技术及数据修正方法  

Test techniques and data correction method for large airplanes in a 2.4 m intermittent transonic wind tunnel

作　　者：许新[1] 李强[1] 彭鑫[1] 蒋鸿[1] 刘大伟[1] 吴军强[1] XU Xin;LI Qiang;PENG Xin;JIANG Hong;LIU Dawei;WU Junqiang(High Speed Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心高速空气动力研究所,绵阳621000

出　　处：《空气动力学学报》2023年第12期95-106,共12页Acta Aerodynamica Sinica

基　　金：智强基金项目资助。

摘　　要：风洞试验是获取飞行器气动特性、评估分析气动设计效果、预测飞行性能的基本手段,对于“四性”指标要求严格的大型飞机而言,风洞试验的精准度(精度和准度)尤为重要。风洞试验的精准度既取决于试验测试技术,也严重受制于试验数据修正方法。本文详细介绍了2.4 m暂冲型跨声速风洞大飞机精细化气动力/气动载荷试验技术及其洞壁干扰、支撑干扰、模型变形影响等数据修正方法的最新进展,对比分析了大飞机试验数据的精度与准度。结果表明2.4 m风洞大飞机试验模拟能力与数据修正方法满足型号研制需求,试验数据精准度较高,具备精确获取大飞机高速气动特性的能力。相关研究成果对推动我国大飞机气动试验研究能力高水平自主可控具有重要支撑作用。Wind tunnel testing is a fundamental means of obtaining aircraft aerodynamic characteristics,evaluating and analyzing the performance of aerodynamic design,and predicting flight performance.The reliability of wind tunnel tests,regarding accuracy and precision,depends not only on the testing techniques but also on the data correcting method,which is particularly crucial for large airplanes.This paper first summarizes the research progress of the aerodynamic force and load testing techniques for large airplanes in a 2.4-meter transonic wind tunnel.Then,it introduces the advancement of methods for correcting wall interference,support interference,and deformation effects.The accuracy and precision of the test data of a large airplane are quite good,indicating that the test techniques and data correction method for large airplanes in the 2.4-meter wind tunnel meet the testing requirements and thus are capable of obtaining the aerodynamic characteristics of highspeed large airplanes.The results are essential in promoting the development of China's large airplane aerodynamic testing capabilities.

关 键 词：大飞机 风洞试验 数据修正 精度 准度 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]