LI Qiang, LIU Dawei, XU Xin, et al. Experimental study of aerodynamic characterictics of CHN-T1 standard model in 2.4 m transonic wind tunnel[J]. 2019, 37(2): 337-344.
LI Qiang, LIU Dawei, XU Xin, et al. Experimental study of aerodynamic characterictics of CHN-T1 standard model in 2.4 m transonic wind tunnel[J]. 2019, 37(2): 337-344.DOI: 10.7638/kqdlxxb-2018.0099.
Experimental study of aerodynamic characterictics of CHN-T1 standard model in 2.4 m transonic wind tunnel
Large aircraft standard model can used in validating the flow field quality of transonic wind tunnels
checking and improving the experimental data quality. It is important that the outline characteristics and aerodynamic performance of standard model reflect the design of modern large aircraft. A new high-aspect-ratio aircraft model was designed by CARDC
and a validation test was conducted in 2.4 m transonic wind tunnel with test Mach number from 0.40 to 0.9
with the angle of attack ranges from -6° to 15°
side slip angle from -3° to 12°
and Reynolds number from 3.3×10
6
to 7.5×10
6
. The test contents consist of basic char
acteristic test
repeatability test
Reynolds number variation test
transition method comparison test
surface oil flow visualization test
and model deformation test. The results indicate that
the model designed shows good lift-to-drag characteristics
meeting the typical aerodynamic characteristics of modern high-aspect-ratio aircraft
and can be used in the construction of large aircraft data system in 2.4m transonic wind tunnel.
关键词
Keywords
references
CHEN D H, LIN J, GUO D P, et al.Technical ways to solve high speed key aerodynamic problems of large air transporters[J].Experiments and Measurements in Fluid Mechanics, 2003, 18(2):1-5.(in Chinese)
WANG F X, et al.High speed wind tunnel test[M].Beijing:National Defense Industry Press, 2003.(in Chinese)
HUANG Y, DONG L X, ZHAO K C, et al.On the correlation of force test results of a tactical missile calibration model in five different windtunnels[J].Experiments and Measurements in Fluid Mechanics, 2002, 16(2):16-20.(in Chinese)
CHEN D H, LIU D W, XU X, et al.Investigation on factors influencing high speed wind tunnel data for large airplane[C].8th National Fluid Dynamics Conference, 2014.(in Chinese)
FAN J C, CHEN D H, PENG Y, et al.Research on force test technique of UAV model with large aspect ratio in high speed wind tunnel[J].Journal of Experiments in Fluid Mechanics, 2007, 21(3):62-65.(in Chinese)
CHEN D H, YIN L P, WU W H, et al.The test technique for aircraft with high aspect ratio in the 2.4 meter transonic windtunnel[J].Acta Aerodynamica Sinica, 2009, 27(5):542-546.(in Chinese)
WANG R, WU J, GUO Q, et al.Research on the affecting factors of test quality and improvement methods in 2.4 m transonic wind tunnel[J].Journal of Experiments in Fluid Mechanics, 2012, 26(1):37-41.(in Chinese)
GREGORY M G, MELISSA B R, SCOTT L G, et al.Experimental Investigation of the DLR-F6 Transport Configuration in the National Transonic Facility[C].26th AIAA Applied Aerodynamics Conference, 2008.
MELISSA B R, CRAIG A H, GREGORY M G.Support system effects on the DLR-F6 transport configuration in the national transonic facility[C].27th AIAA Applied Aero-dynamics Conference, 2009.
RALF R, MARTIN S, JEAN L G, et al.Experimental investigation of the wing-body juncture flow on the DLR-F6 configuration in the ONERA S2MA facility[C].27th AIAA Applied Aerodynamics Conference, 2009.
ALPHEUS W BURNER, WILLIAM K GOAD, EDWARD A MASSEY, et al.Wing deformation measurements of the DLR-F6 transport configuration in the national transonic facility[C].26th AIAA Applied Aerodynamics Conference, 2008.
THORSTEN L, PHILIPP P G, JEAN L G, et al.Going for experimental and numerical unsteady wake analyses combined with wall interference assessment by using the NASA CRM model in ETW[C].51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2013.
WANG Y T, WANG G X, ZHANG Y L.Drag of DLR-F6 wing-body configuration[J].Chinese Journal of Computational Physics, 2008, 25(2):145-150.(in Chinese)
ANTONY J S, JOHN C V, NEAL A H, et al.Drag prediction for the DLR-F6 wing body and DPW wing using CFL3D and OVERFLOW on an Overset Mesh[C].45th AIAA Aerospace Sciences Meeting and Exhibit, 2007.
CHEN D H, WANG W X, WANG J J, et al.Investigation on flow-field debugging for 2.4 m transonic wind tunnel[J].Acta Aerodynamica Sinica, 2004, 22(3):279-282.(in Chinese)
ZHAN P G, LUO Y P.Primary research on the standard system of air vehicle calibration models used in wind tunnel test[J].Standard Science, 2011, 11(2):28-31.(in Chinese)
YU Y G, ZHOU Z, HUANG J T, et al.Aerodynamic design of a standard model CHN-T1 for single-aisle passenger aircraft[J].Acta Aerodynamica Sinica, 2018, 36(03):505-513.(in Chinese)
LI W, MENG D H, WANG Y T, et al.Numerical simulation of CHNG-T1 model with TRIP3.0[J].Acta Aerodynamica Sinica, 2019, 37(2):272-279.(in Chinese)
路波, 等.高速风洞测力试验数据处理方法[D].北京: 国防工业出版社, 2014.
CHENG H M.Interference and correction on wind tunnel testing[M].Beijing:National Defense Industry Press, 2003.(in Chinese)
LI Q, LIU D W, CHEN D H, et al.Study on the support Interference of vane suspension support system in high speed wind tunnels[J].Journal of Experiments in Fluid Mechanics, 2017, 31(1):100-108.(in Chinese)
HE B H, LI W, LIU D W, Technology Research of Complicated Configuration Oil-flow Experimentation of High Speed Wind Tunnel[R].Mianyang: CARDC, 2017.(in Chinese)