NASA/TP-2004-213247 (August 2004). Printed pp. 7–9: hot-wire probes, mean/fluctuating signal channels, calibration and data analysis; Figure 20: sensitivity to retained bandwidth. Summary and flow-quality survey compare positions and operating conditions.

NACA-TR-669 (1939), NTRS abstract: support interference inflated published drag coefficients and their apparent increase with section thickness; corrected data and correction methods are supplied.

Pitch axis and final control-surface discussion: nose-up/nose-down rotation and torques produced by forces displaced from a reference.

Variation in Pressure and Definitions of Lift and Drag: distributed pressure, local surface normals, integration and flow-relative force components.

Originating MIT Unified Engineering teaching notes, hosted by MIT OpenCourseWare. No personal byline is established from the four-page PDF. Page 2 defines the camber-slope Fourier coefficients; p. 3 derives section lift and the zero-lift incidence; p. 4 explains angle-independent quarter-chord moment within thin-airfoil theory. The chord-to-angle substitution integrates over the angular interval from zero to pi; numerical examples in the concept articles are original calculations, not experimental results.

Sections Fuselage and Weight describe the central body, its connection of aircraft components, accommodation of payload and resistance to applied torques. This is an originating NASA explanatory page; the cylinder-stress example in the concept article is a separate ideal calculation.

Simulation Driven Design: virtual aircraft prototypes, computational credibility and rapid-turnaround multidisciplinary design.

NACA-RM-L6J01a,14 February 1947. Abstract: no sweep, ±30 degrees and ±45 degrees; Mach numbers 0.60–0.96; pressure measurements and wake surveys compare shock-associated changes.

NACA-TR-563 (1937). NTRS abstract: 54 pressure orifices, a 5-by-30-inch model, 17 angles from −20 to 30 degrees, Reynolds number approximately 3 million; comparison with potential-flow calculations.

NACA-TN-365 (1931), printed pp.2–5, Apparatus and Tests and Discussion of Results. A 5-by-30-inch Göttingen 387 model, 20-atmosphere tunnel pressure, Reynolds number 3.4 million, and comparisons of wing alone, attached struts and separate strut drag. Download: ntrs.nasa.gov/api/citations/19930081164/downloads/19930081164.pdf

Additional verified locator: Table I, printed p. 9, lists Göttingen 387 upper/lower ordinates in separate specified and measured columns; all dimensions are in percent of chord. ntrs.nasa.gov/api/citations/19930081164/downloads/19930081164.pdf

Air Pressure of a Wing and Induced Drag Coefficient: wingtip flow, aspect ratio and the span-efficiency form of the induced-drag equation.

Flight Path and Tangent Angle: steady descent geometry, horizontal distance and height loss.

Sections Weight, Lift, Drag and Thrust: force directions and distinctions between aerodynamic and propulsive forces.

Journal of Fluid Mechanics 35(4), 721–735 (10 March 1969). Exact publisher bylines B. J. Bellhouse and L. Talbot, Department of Engineering Science, Oxford University. Abstract: a rigid-walled valve model in a pulsatile water tunnel exhibited a sinus stagnation point and trapped vortex, with most closure occurring while net flow was still forward. The 2006 publisher date is online publication of the historical article, not the experimental year.

Publisher Author details additionally gives L. Talbot a permanent address at the University of California, Berkeley, while listing the Oxford Department of Engineering Science affiliation. The primary author names remain B. J. Bellhouse and L. Talbot; no full initials expansion or individual division of experimental work is inferred.

NACA Report 460, originally published November 1933; primary PDF: ntrs.nasa.gov/api/citations/19930091108/downloads/19930091108.pdf . Apparatus and Methods describes duralumin models, dimensions, Reynolds number, tank pressure and measured forces/moments. The introduction and profile derivation explain systematic variation of thickness and mean-line form.

Manufacturer-hosted primary manual. Cover gives Front-end Signal Conditioners, Owner’s Guide; imprint p. ii gives document U-FE/OG-35G and issue 08/18. No individual byline is asserted. Chapter 10, printed p. 149, Using the Spirometer, describes a fine mesh flow head, pressure taps and a differential pressure transducer, with proportional flow response within stated limits. Printed pp. 151–152, Calibrating the Flow Head, describes a known-volume syringe injection and time integration of the output. Printed p. 153, Reducing Drift, explains zeroing the no-flow signal to prevent steady drift of integrated volume. PDF page indices are 156, 158–159 and 160 respectively.

Virginia Tech open textbook, 2026; author William H. Mason, editor Pradeep Raj. The publisher landing page identifies the author and design-oriented scope. Appendix A.4 treats planform analysis; the Preface documents the posthumous editing of Mason’s course notes. Official departmental identity confirmation: www.aoe.vt.edu/about-us/news/mason-memorial-distinguished-lecture/mason-configuration-aerodynamics.html .

Author-hosted Virginia Tech course notes. Appendix A, Geometry for Aerodynamicists, archive.aoe.vt.edu/mason/Mason_f/CAtxtAppA.pdf , is dated 23 October 1997: pp. A-3–A-4 give the four-digit thickness polynomial and nose radius; pp. A-27–A-29 define wing area, mean aerodynamic chord and trapezoidal-planform quantities.

Additional cited passage: Appendix A, p. A-1, equations (A-1)–(A-3), upper and lower surface construction by offsets normal to the mean camber line. The following paragraph notes that neglecting the camber-line slope simplifies the inverse extraction of thickness and mean-line geometry. ^[ref]

Additional exact sweep locators: Appendix A, p. A-29, equations (A-97)–(A-101), leading- and trailing-edge coordinates, linear chord distribution and conversion between sweep at different fixed chord fractions. Equation (A-100) relates tangents of sweep angles rather than the angle differences. ^[ref]

Originating NASA geometry definitions, especially Airfoil Geometry and Wing Geometry. Defines the straight chord between leading and trailing edges, distinguishes it from camber and the curved surfaces, and explains spanwise variation of chord in a finite wing. The numerical geometry and trapezoidal-area calculations in the concept article are independent examples.

Official Drake C++ class reference. Detailed Description specifies a torque/force pair, its application point and expressed-in frame, noting that the six stored values do not retain that metadata. Shift and ShiftInPlace document the offset direction and moment-translation cross product; forces and offsets must use the same expressed-in frame.