http://swrc.ontoware.org/ontology#TechnicalReport
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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榊原 盛三
高島 一明
三輪 等
小国 保男
佐藤 衛
神田 宏
SAKAKIBARA Seizo
TAKASHIMA Kazuaki
MIWA Hitoshi
OGUNI Yasuo
SATO Mamoru
KANDA Hiroshi
航空宇宙技術研究所
National Aerospace Laboratory(NAL)
Technical Report of National Aerospace Laboratory TR-693
693
1982-01
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.
0389-4010
資料番号: NALTR0693000
レポート番号: NAL TR-693