Flow Quality of NAL Two-Dimensional Transonic Wind Tunnel Part I Mach Number Distributions,Flow Angularities and Preliminary Study of Side Wall Boundary Layer Suction
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Second Aerodynamics Division, National Aerospace Laboratory(NAL)
Second Aerodynamics Division, National Aerospace Laboratory(NAL)
Second Aerodynamics Division, National Aerospace Laboratory(NAL)
Second Aerodynamics Division, National Aerospace Laboratory(NAL)
Second Aerodynamics Division, National Aerospace Laboratory(NAL)
Second Aerodynamics Division, National Aerospace Laboratory(NAL)
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-693
巻
693
ページ
26
発行年
1982-01
抄録（英）
Experimental data on the flow quality of the NAL two-dimensional transonic wind tunnel are presented. Mach number distributions on the test section axis show good uniformity which is characterised by the two-sigma(standard deviation) values of 0.0003 to 0.001 for a range of Mach numbers from 0.4 to 1.0 Flow angularities, which were measured by using a wing model with a symmetrical cross section, remained within 0.04 degree for Mach numbers from 0.2 to 0.8. Side wall boundary layer suction was applied through a pair of porous plates. The variation of aerodynamic properties of the model due to the suction mass flow rate change is presented with a brief discussion. Two-dimensionality of the flow over the wing span is expected to be improved by applying the appropriate suction rate, which depends on the Mach number, Reynolds number and lift coefficient.
Flow Quality of NAL Two-Dimensional Transonic Wind Tunnel Part I Mach Number Distributions,Flow Angularities and Preliminary Study of Side Wall Boundary Layer Suction
naltr00693.pdf
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