Drag measurements on a Junkers wing section : application of the Betz Method to the results of comparative tests made on a model and on an airplane in flight (1927)
NASA Technical Reports Server (NTRS) · leaf 51
Figs.9 & 10 N.A.C.A. Technical Memorandum No.428 0.030 a, d- = 8.5° b, a = 4.5° o, ct = 3.1° d, d = 0.8° 21.C| 15.3 Profile Airflow thickness 126 Xi. .. ii Displacement line of I II HI rear Pitot tube Position Fig.9 Distribution of the profile drag along the span. … h, mm Fig.10 Pressure loss behind-the'wing for position I of the Pitot tubes for four different velocities and a = 0.8°.
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