Transonic Wind Tunnel Test of the NASA CRM: Volume 1

A wind tunnel test of a 80% scale copy of the NASA Common Research Model (CRM) was performed in the 2m × 2m transonic wind tunnel of the Japan Aerospace Exploration Agency (JAXA). JAXA consulted with NASA Langley Research Center and committee members of the Drag Prediction Workshop during the wind tunnel model fabrication. The test was conducted at the relatively low Reynolds number of 2.27 × 106 due to limitations in the tunnel’s capability, and boundary layer transition was simulated with optimized trip dots. Static pressure distributions and aerodynamic forces were successfully acquired from the test campaign, and the data were compared with those from the NASA National Transonic Facility. Numerical data acquired by JAXA are presented in this paper. This volume includes the results from wind tunnel tests conducted in 2012. Nomenclature b = wing span c = wing mean aerodynamic cord CD = drag coefficient CDac = drag coefficient corrected for angle of attack difference CDbc = drag coefficient corrected for buoyancy CDc0 = drag coefficient corrected for test section Mach number difference CDmc = drag coefficient corrected for Mach number difference CD_buoyancy = sum of buoyancy correction amount to be subtracted from drag coefficient CD_buoyancy_probe = clear tunnel buoyancy correction amount CD_buoyancy_probe_mc = clear tunnel buoyancy correction amount corrected for Mach number difference CD_buoyancy_wall = buoyancy correction amount derived from wall interference correction CD_buoyancy_wall_mc = buoyancy correction amount derived from wall interference correction corrected for Mach number difference CL = lift coefficient * Received 19 December 2013 *1 Institute of Aeronautical Technology, Wind Tunnel Technology Center, JAXA This document is provided by JAXA. 2 JAXA Research and Development Memorandum JAXA-RM-13-017E CLac = lift coefficient corrected for angle of attack difference CLc0 = lift coefficient corrected for test section Mach number difference CLmc = lift coefficient corrected for Mach number difference Cm = pitching moment coefficient Cmmc = pitching moment coefficient corrected for Mach number difference Cp = pressure coefficient Cp_center = pressure coefficient along the centerline in the wind tunnel measured by the short centerline probe Mpc = plenum chamber Mach number Mc = corrected Mach number Mc0 = Mach number corrected for test section Mach number difference P0 = stagnation pressure Pc = static pressure corrected for Mach number difference Pc0 = static pressure corrected for test section Mach number difference Ppc = plenum chamber pressure Q = dynamic pressure Qc = dynamic pressure corrected for Mach number difference Qc0 = dynamic pressure corrected for test section Mach number difference Rec = Reynolds number based on aerodynamic cord SModel = model cross sectional area Sref = model reference area T0 = stagnation temperature X = model station Xnose = model nose station Xtail = model tail station α = angle of attack αc = corrected angle of attack η = fraction of wing semi-span ΔM = sum of Mach number correction amount ΔMd = Mach number difference between plenum chamber Mach number and model center ΔMwall = Mach number correction amount derived from wall interference correction Δα = sum of angle of attack correction amount Δαwall = angle of attack correction amount derived from wall interference correction Δαupflow = upflow angle This document is provided by JAXA. JAXA Transonic Wind Tunnel Test of the NASA CRM (Volume 1) 3

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