Авторы не указаны. — Основа экспериментальных данных для компьютерной оценки программ. На английском языке. — Report of the Fluid Dynamics Panel AGARD, 1979. 612 р.Introduction and Overview of Configurations
by J.Barche
Limitations of Available Data
by T.W.Binion
Recommendations for Future Testing
by K.G.Winter and L.H.Ohman
Concluding Remarks
by J.Barche
Appendix A - 2-D Configurations
by J .Sloof
NACA 0012 Airfoil
by J.J.Thibert, M.Grandjacques and L.H.Ohman
NLR QE 0.1 1 - 0.75 - 1.375 Airfoil
by NLR and NAE
Supercritical airfoil cast 7 surface pressure, wake and boundary
Layer measurements
by Estanewsky, W.Puffert, R.Muuer and T.E.B.Bateman
NLR 7301 Airfoil
by NLR Amsterdam
Airfoil skf 1 .l. With maneuver flap
by E.Stanewsky and J .J .Thibert
Aerofoil rae 2822 - pressure distributions, and boundary layer
And wake measurements
by P.H.Cook, M.A.McDonald and M.C.P.Firmin
Pressure distrlbutlons for airfoil nae 75-036-113: 2 at Reynolds Numbers from 14 to 30 million
by Naeinrc
Supercritical airfoil mbb-a3-surface pressure distributions,
Wake and boundary condition measurements
by G.Bucciantini. M.S.Oggiano and M.Onorato
Experimental investigation of a 10 percent thick nasa supercritical
Airfoil section
by C.D.Harris
Appendix B - 3-D Configurations
by P.J.Bobbitt
Pressure distributions on the onera-m6-wing at transonic mach Numbers
by V.Schmitt and F.Charpin
Transonic measurements on the 'onera afv d' variable sweep wing in
The 'onera s2 ma' wind tunnel
by F.Manie and J.C. Raynal
MBB.AVA pilot-model with supercritical winc-surface pressure
and force measurements
by H.Korner, W.Lorenz-Meyer, A.Heddergott and A.Eberle
Pressure distrlbution measured in the ra 8ft x 6ft transonic wind tunnel on rae wing "a" in combination with an axi-symmetric body at mach numbers of 0.4,0.8 and 0.9
by D.A.Treadgold, A.F.lones and K.H.Wilson
Pressure distributions measured on an nasa supercritical-wing research airplane model
by C.D.Harris and D.W.Bartlett
Appendix C - Body-Alone Configurations
by T.W.Binion
1.5 d ogive - circular cylinder body, lid = 21.5
by K.Hartmann
MBB- body of revolution n0.3
by W.Lorenz-Meyer and F.Aulehla
Pressure distribution data for a 1ooconecylinder at zero incidence
in the mach number range 0.91 to 1.22
by the High Speed Aerodynamics Laboratory NAE/NRC Onera Calibration Model C5
by X.Vaucheret
