测试科学与仪器
測試科學與儀器
측시과학여의기
Journal of Measurement Science and Instrumentation
2015年
3期
270-274
,共5页
带翼刚体%零升阻力系数%升力系数%风洞试验%动力学特性
帶翼剛體%零升阻力繫數%升力繫數%風洞試驗%動力學特性
대익강체%령승조력계수%승력계수%풍동시험%동역학특성
winged rigid body%zero lift drag coefficient%lift coefficient%wind tunnel experiment%dynamic characteristics
对大长径比带翼刚体的零升阻力系数和升力系数的风洞试验数据进行了综合分析，利用风洞试验数据修正了带翼刚体升力系数和零升阻力系数的动力学模型。研究结果表明，大长径比带翼刚体的零升阻力系数和升力系数随马赫数的变化趋势基本相似，数值计算数据与风洞试验数据都验证了修正后的动力学模型对于估算大长径比带翼刚体的升力系数和零升阻力系数是可行的，为同类型带翼刚体的空气动力特性分析提供了技术参考。
對大長徑比帶翼剛體的零升阻力繫數和升力繫數的風洞試驗數據進行瞭綜閤分析，利用風洞試驗數據脩正瞭帶翼剛體升力繫數和零升阻力繫數的動力學模型。研究結果錶明，大長徑比帶翼剛體的零升阻力繫數和升力繫數隨馬赫數的變化趨勢基本相似，數值計算數據與風洞試驗數據都驗證瞭脩正後的動力學模型對于估算大長徑比帶翼剛體的升力繫數和零升阻力繫數是可行的，為同類型帶翼剛體的空氣動力特性分析提供瞭技術參攷。
대대장경비대익강체적령승조력계수화승력계수적풍동시험수거진행료종합분석，이용풍동시험수거수정료대익강체승력계수화령승조력계수적동역학모형。연구결과표명，대장경비대익강체적령승조력계수화승력계수수마혁수적변화추세기본상사，수치계산수거여풍동시험수거도험증료수정후적동역학모형대우고산대장경비대익강체적승력계수화령승조력계수시가행적，위동류형대익강체적공기동력특성분석제공료기술삼고。
Synthetic analysis is conducted to the wind tunnel experiment results of zero lift drag coefficient and lift coefficient for large aspect ratio winged rigid body.By means of wind tunnel experiment data,the dynamics model of the zero lift drag coeffi-cient and lift coefficient for the large aspect ratio winged rigid body is amended.The research indicates that the change trends of zero lift drag coefficient and lift coefficient to Mach number are similar.The calculation result and wind tunnel experiment data all verify the validity of the amended dynamics model by which to estimate the zero lift drag coefficient and lift coefficient for the large aspect ratio winged rigid body,and thus providing some technical reference to aerodynamics character analysis of the same types of winged rigid body.
