Experimental Data Base for Computer Program Assessment

Description

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 Configurationsby J.BarcheLimitations of Available Databy T.W.BinionRecommendations for Future Testingby K.G.Winter and L.H.OhmanConcluding Remarksby J.BarcheAppendix A - 2-D Configurationsby J .SloofNACA 0012 Airfoilby J.J.Thibert, M.Grandjacques and L.H.OhmanNLR QE 0.1 1 - 0.75 - 1.375 Airfoilby NLR and NAESupercritical airfoil cast 7 surface pressure, wake and boundaryLayer measurementsby Estanewsky, W.Puffert, R.Muuer and T.E.B.Bateman NLR 7301 Airfoilby NLR AmsterdamAirfoil skf 1 .l. With maneuver flapby E.Stanewsky and J .J .ThibertAerofoil rae 2822 - pressure distributions, and boundary layerAnd wake measurementsby P.H.Cook, M.A.McDonald and M.C.P.FirminPressure distrlbutlons for airfoil nae 75-036-113: 2 at Reynolds Numbers from 14 to 30 millionby NaeinrcSupercritical airfoil mbb-a3-surface pressure distributions,Wake and boundary condition measurementsby G.Bucciantini. M.S.Oggiano and M.OnoratoExperimental investigation of a 10 percent thick nasa supercriticalAirfoil sectionby C.D.HarrisAppendix B - 3-D Configurationsby P.J.BobbittPressure distributions on the onera-m6-wing at transonic mach Numbersby V.Schmitt and F.CharpinTransonic measurements on the 'onera afv d' variable sweep wing in The 'onera s2 ma' wind tunnelby F.Manie and J.C. Raynal MBB.AVA pilot-model with supercritical winc-surface pressureand force measurementsby H.Korner, W.Lorenz-Meyer, A.Heddergott and A.EberlePressure 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 0.9by D.A.Treadgold, A.F.lones and K.H.Wilson Pressure distributions measured on an nasa supercritical-wing research airplane modelby C.D.Harris and D.W.BartlettAppendix C - Body-Alone Configurationsby T.W.Binion1.5 d ogive - circular cylinder body, lid = 21.5by K.HartmannMBB- body of revolution n0.3by W.Lorenz-Meyer and F.AulehlaPressure distribution data for a 1ooconecylinder at zero incidencein the mach number range 0.91 to 1.22by the High Speed Aerodynamics Laboratory NAE/NRC Onera Calibration Model C5by X.Vaucheret