[1]. Interview of Joseph Walker by author, NASA Langley Research Center, July 3, 1962.
[2]. Max Scherberg and R.V. Rhode, “Mass Distribution and Performance of Free Flight Models,” NACA TN-268 (1927).
[3]. Ibid.
[4]. C.H. Zimmerman, “Preliminary Tests in the N.A.C.A. Free-Spinning Wind Tunnel,” NACA TR-557 (1935).
[5]. C. Wenzinger and T. Harris, “The Vertical Wind Tunnel of the National Advisory Committee for Aeronautics,” NACA TR-387 (1931). The tunnel’s vertical orientation was to minimize cyclical gravitational loads on the spinning model and apparatus as would have occurred in a horizontal tunnel.
[6]. H.E. Wimperis, “New Methods of Research in Aeronautics,” Journal of the Royal Aeronautical Society (Dec. 1932), p. 985.
[7]. Zimmerman, “Preliminary Tests in the N.A.C.A. Free-Spinning Wind Tunnel.” Zimmerman was a brilliant engineer with a notable career involving the design of dynamic wind tunnels, advanced aircraft configurations, and flying platforms, and he served NASA as a member of aerospace panels.
[8]. Anshal I. Neihouse, Walter J. Klinar, and Stanley H. Scher, “Status of Spin Research for Recent Airplane Designs” NASA TR-R-57 (1962).
[9]. D. Bruce Owens, Jay M. Brandon, Mark A. Croom, Charles M. Fremaux, Eugene H. Heim, and Dan D. Vicroy, “Overview of Dynamic Test Techniques for Flight Dynamics Research at NASA LaRC,” AIAA Paper 2006-3146 (2006).
[10]. Joseph R. Chambers and Mark A. Chambers, Radical Wings and Wind Tunnels (Specialty Press, 2008). Zimmerman was a very proficient model pilot and flew most of the tests in the apparatus.
[11]. John P. Campbell, Jr., was head of the organization at the time of the move. Campbell was one of the youngest research heads ever employed at Langley. In addition to being an expert in flight dynamics, he later became recognized for his expertise in V/STOL aircraft technology.
[12]. Owens, et al., “Overview of Dynamic Test Techniques,” AIAA Paper 2006-3146.
[13]. Alvin Seiff, Carlton S. James, Thomas N. Canning, and Alfred G. Boissevain, “The Ames Supersonic Free-Flight Wind Tunnel,” NACA RM-A52A24 (1952).
[14]. Charles J. Cornelison, “Status Report for the Hypervelocity Free-Flight Aerodynamic Facility,” 48th Aero Ballistic Range Association Meeting, Austin, TX, Nov. 1997.
[15]. Ralph W. Stone, Jr., William G. Garner, and Lawrence J. Gale, “Study of Motion of Model of Personal-Owner or Liaison Airplane Through the Stall and into the Incipient Spin by Means of a Free-Flight Testing Technique,” NACA TN-2923 (1953).
[16]. NASA has, however, used catapulted models for spin entry studies on occasion. See James S. Bowman, Jr., “Spin-Entry Characteristics of a Delta-Wing Airplane as Determined by a Dynamic Model,” NASA TN-D-2656 (1965).
[17]. Charles E. Libby and Sanger M. Burk, Jr., “A Technique Utilizing Free-Flying Radio-Controlled Models to Study the Incipient-and Developed-Spin Characteristics of Airplanes,” NASA Memo 2-6-59L (1959).
[18]. In addition to specific requests from DOD, Langley conducted fundamental research on spin entry, such as the impact of automatic spin prevention.
[19]. David J. Fratello, Mark A. Croom, Luat T. Nguyen, and Christopher S. Domack, “Use of the Updated NASA Langley Radio-Controlled Drop-Model Technique for High-Alpha Studies of the X-29A Configuration,” AIAA Paper 1987-2559 (1987).
[20]. Mark A. Croom, Holly M. Kenney, and Daniel G. Murri, “Research on the F/A-18E/F Using a 22%-Dynamically-Scaled Drop Model,” AIAA Paper 2000-3913 (2000).
[21]. R. Dale Reed, Wingless Flight: The Lifting Body Story, NASA SP-4220 (1997).
[22]. Euclid C. Holleman, “Summary of Flight Tests to Determine the Spin and Controllability Characteristics of a Remotely Piloted, Large-Scale (3/8) Fighter Airplane Model,” NASA TN-D-8052 (1976).
[23]. Michael J. Hirschberg and David M. Hart, “A Summary of a Half-Century of Oblique Wing Research,” AIAA Paper 2007-150 (2007).
[24]. Joseph A. Shortal, A New Dimension. Wallops Island Flight Test Range: The First Fifteen Years, NASA RP-1028 (1978).
[25]. Campbell, “Free and Semi-Free Model Flight-Testing Techniques Used in Low-Speed Studies of Dynamic Stability and Control,” NATO Advisory Group for Aeronautical Research and Development AGARDograph 76 (1963).
[26]. This topic is discussed for military applications in another case study in this volume by the same author.
[27]. Joseph A. Shortal and Clayton J. Osterhout, “Preliminary Stability and Control Tests in the NACA Free-Flight Tunnel and Correlation with Flight Tests,” NACA TN-810 (1941).
[28]. Charles L. Seacord, Jr., and Herman O. Ankenbruck, “Determination of the Stability and Control Characteristics of a Straight-Wing, Tailless Fighter-Airplane Model in the Langley Free-Flight Tunnel,” NACA Wartime Report ACR L5K05 (1946).
[29]. M.O. McKinney, “Experimental Determination of the Effects of Dihedral, Vertical Tail Area, and Lift Coefficient on Lateral Stability and Control Characteristics,” NACA TN-1094 (1946).
[30]. Campbell and Seacord, “The Effect of Mass Distribution on the Lateral Stability and Control Characteristics of an Airplane as Determined by Tests of a Model in the Free-Flight Tunnel,” NACA TR-769 (1943).
[31]. Robert O. Schade and James L. Hassell, Jr., “The Effects on Dynamic Lateral Stability and Control of Large Artificial Variations in the Rotary Stability Derivatives,” NACA TN-2781 (1953).
[32]. Carl A. Sandahl, “Free-Flight Investigation at Transonic and Supersonic Speeds of a Wing-Aileron Configuration Simulating the D558-2 Airplane,” NACA RM-L8E28 (1948); and Sandahl, “Free-Flight Investigation at Transonic and Supersonic Speeds of the Rolling Effectiveness for a 42.7° Sweptback Wing Having Partial-Span Ailerons,” NACA RM-L8E25 (1948).
[33]. Examples include James H. Parks and Jesse L. Mitchell, “Longitudinal Trim and Drag Characteristics of Rocket-Propelled Models Representing Two Airplane Configurations,” NACA RM-L9L22 (1949); and James L. Edmondson and E. Claude Sanders, Jr., “A Free-Flight Technique for Measuring Damping in Roll by Use of Rocket-Powered Models and Some Initial Results for Rectangular Wings,” NACA RM-L9101 (1949).
[34]. Parks, “Experimental Evidence of Sustained Coupled Longitudinal and Lateral Oscillations From Rocket-Propelled Model of a 35° Swept-Wing Airplane Configuration,” NACA RM-L54D15 (1954).
[35]. Maurice L. Rasmussen, “Determination of Nonlinear Pitching-Moment Characteristics of Axially Symmetric Models From Free-Flight Data,” NASA TN-D-144 (1960).
[36]. Alfred G. Boissevain and Peter F. Intrieri, “Determination of Stability Derivatives from Ballistic Range Tests of Rolling Aircraft Models,” NASA TM-X-399 (1961).
[37]. Chambers, Radical Wings and Wind Tunnels.
[38]. William R. Bates, Powell M. Lovell, Jr., and Charles C. Smith, Jr., “Dynamic Stability and Control Characteristics of a Vertically Rising Airplane Model in Hovering Flight,” NACA RM-L50J16 (1951).
[39]. Hovering and transition tests included: Lovell, Smith, and R.H. Kirby, “Stability and Control Flight Tests of a 0.13-Scale Model of the Consolidated Vultee XFY-1 Airplane in Take-Offs, Landings, and Hovering Flight,” NACA RM-SL52I26 (1952); and Lovell, Smith, and Kirby, “Flight Investigation of the Stability and Control Characteristics of a 0.13-Scale Model of the Convair XFY-1 Vertically Rising Airplane During Constant-Altitude Transitions,” NACA RM-SL53E18 (1953).
[40]. Smith, “Flight Tests of a 1/6-Scale Model of the Hawker P.1127 Jet VTOL Airplane,” NASA TM-SX-531 (1961).
[41]. Lovell and Lysle P. Parlett, “Hovering-Flight Tests of a Model of a Transport Vertical Take-Off Airplane with Tilting Wing and Propellers,” NACA TN-3630 (1956); Lovell and Parlett, “Flight Tests of a Model of a High-Wing Transport Vertical-Take-Off Airplane With Tilting Wing and Propellers and With Jet Controls at the Rear of the Fuselage for Pitch and Yaw Control,” NACA TN-3912 (1957).
[42]. Louis P. Tosti, “Flight Investigation of Stability and Control Characteristics of a 1/8-Scale Model of a Tilt-Wing Vertical-Take-Off-And-Landing Airplane,” NASA TN-D-45 (1960); Tosti, “Longitudinal Stability and Control of a Tilt-Wing VTOL Aircraft Model with Rigid and Flapping Propeller Blades,” NASA TN-D-1365 (1962); William A. Newsom and Robert H. Kirby, “Flight Investigation of Stability and Control Characteristics of a 1/9-Scale Model of a Four-Propeller Tilt-Wing V/STOL Transport,” NASA TN-D-2443 (1964).
[43]. Campbell and Joseph L. Johnson, Jr., “Wind-Tunnel Investigation of an External-Flow Jet-Augmented Slotted Flap Suitable for Applications to Airplanes with Pod-Mounted Jet Engines,” NACA TN-3898 (1956).
[44]. Parlett, “Free-Flight Wind-Tunnel Investigation of a Four-Engine Sweptwing Upper-Surface Blown Transport Configuration,” NASA TM-X-71932 (1974).
[45]. Parlett, “Free-Flight Investigation of the Stability and Control Characteristics of a STOL Model with an Externally Blown Jet Flap,” NASA TN-D-7411 (1974); Chambers, Radical Wings and Wind Tunnels.
[46]. Campbell originally conceived the EBF concept and was awarded a patent for his invention.
[47]. Chambers, Radical Wings and Wind Tunnels. Langley researchers Polhamus and William J. Alford were awarded a patent for the outboard pivot concept.
[48]. Polhamus and Thomas A. Toll, “Research Related to Variable Sweep Aircraft Development,” NASA TM-83121 (1981).
[49]. Campbell and Hubert M. Drake, “Investigation of Stability and Control Characteristics of an Airplane Model with Skewed Wing in the Langley Free-Flight Tunnel,” NACA TN-1208 (1947).
[50]. Polhamus and Toll, “Variable Sweep Aircraft Development,” NASA TM-83121.
[51]. Michael J. Hirschberg and David M. Hart, “A Summary of a Half-Century of Oblique Wing Research,” AIAA Paper 2007-150 (2007).
[52]. Weneth D. Painter, “AD-1 Oblique Wing Research Aircraft Pilot Evaluation Program,” AIAA Paper 1983-2509 (1983).
[53]. James S. Bowman, Jr., “Dynamic Model Tests at Low Subsonic Speeds of Project Mercury Capsule Configurations With and Without Drogue Parachutes,” NASA TM-X-459 (1961); Henry A. Lee, Peter S. Costigan, and Bowman, “Dynamic Model Investigation of a 1/20-Scale Gemini Spacecraft in the Langley Spin Tunnel,” NASA TN-D-2191 (1964); Henry A. Lee and Sanger M. Burk, “Low-Speed Dynamic Model Investigation of Apollo Command Module Configuration in the Langley Spin Tunnel,” NASA TN-D-3888 (1967).
[54]. Costigan, “Dynamic-Model Study of Planetary-Entry Configurations in the Langley Spin Tunnel,” NASA TN-D-3499 (1966).
[55]. David E. Hahne and Charles M. Fremaux, “Low-Speed Dynamic Tests and Analysis of the Orion Crew Module Drogue Parachute System,” AIAA Paper 2008-09-05 (2008).
[56]. Peter C. Boisseau, “Investigation of the Low-Speed Stability and Control Characteristics of a 1/7-Scale Model of the North American X-15 Airplane,” NACA RM-L57D09 (1957); Donald E. Hewes and James L. Hassell, Jr., “Subsonic Flight Tests of a 1/7-Scale Radio-Controlled Model of the North American X-15 Airplane With Particular Reference to High Angle-of-Attack Conditions,” NASA TM-X-283 (1960).
[57]. Dennis R. Jenkins and Tony R. Landis, Hypersonic-The Story of the North American X-15 (Specialty Press, 2008).
[58]. Reed, Wingless Flight, NASA SP-4220.
[59]. George M. Ware, “Investigation of the Flight Characteristics of a Model of the HL-10 Manned Lifting Entry Vehicle,” NASA TM-X-1307 (1967).
[60]. Reed, Wingless Flight.
[61]. Linwood W. McKinney and Polhamus, “A Summary of NASA Data Relative to External-Store Separation Characteristics,” NASA TN-D-3582 (1966).
[62]. Alford and Robert T. Taylor, “Aerodynamic Characteristics of the X-15/B-52 Combination,” NASA Memo-8-59L (1958).
[63]. Shortal, A New Dimension.
[64]. Chambers, Radical Wings and Wind Tunnels; Chambers, Innovation in Flight: Research of the Langley Research Center on Revolutionary Advanced Concepts for Aeronautics, NASA SP-4539 (2005).
[65]. Dan D. Vicroy, “Blended-Wing-Body Low-Speed Flight Dynamics: Summary of Ground Tests and Sample Results,” AIAA Invited Paper presented at the 47th AIAA Aerospace Sciences Meeting and Exhibit, Jan. 2009.
[66]. Laurence A. Walker, “Flight Testing the X-36-The Test Pilot’s Perspective,” NASA CR-198058 (1997).
[67]. Zimmerman, “N.A.C.A. Free-Spinning Wind Tunnel,” NACA TR-557.
[68]. Oscar Seidman and Anshal I. Neihouse, “Free-Spinning Wind-Tunnel Tests on a Low-Wing Monoplane with Systematic Changes in Wings and Tails III. Mass Distributed Along the Wings,” NACA TN-664 (1938).
[69]. Seidman and Charles J. Donlan, “An Approximate Spin Design Criteria for Monoplanes,” NACA TN-711 (1939).
[70]. Walter J. Klinar, Henry A. Lee, and L. Faye Wilkes, “Free-Spinning-Tunnel Investigation of a 1/25-Scale Model of the Chance Vought XF8U-1 Airplane,” NACA RM-SL56L31b (1956).
[71]. M.H. Clarkson, “Autorotation of Fuselages,” Aeronautical Engineering Review, vol. 17 (Feb. 1958); Polhamus, “Effect of Flow Incidence and Reynolds Number on Low-Speed Aerodynamic Characteristics of Several Noncircular Cylinders with Applications to Directional Stability and Spinning,” NACA TN-4176 (1958).
[72]. D.N. Petroff, S.H. Scher, and L.E. Cohen, “Low Speed Aerodynamic Characteristics of an 0.075-Scale F-15 Airplane Model at High Angles of Attack and Sideslip,” NASA TM-X-62360 (1974); Petroff, Scher, and C.E. Sutton, “Low-Speed Aerodynamic Characteristics of a 0.08-Scale YF-17 Airplane Model at High Angles of Attack and Sideslip,” NASA TM-78438 (1978); Raymond D. Whipple and J.L. Ricket, “Low-Speed Aerodynamic Characteristics of a 1/8-scale X-29A Airplane Model at High Angles of Attack and Sideslip,” NASA TM-87722 (1986).
[73]. Stanley H. Scher and William L. White, “Spin-Tunnel Investigation of the Northrop F-5E Airplane,” NASA TM-SX-3556 (1977); C. Michael Fremaux, “Wind-Tunnel Parametric Investigation of Forebody Devices for Correcting Low Reynolds Number Aerodynamic Characteristics at Spinning Attitudes,” NASA CR-198321 (1996).
[74]. A discussion of the powerful effects of asymmetric mass loadings for the F-15 fighter is presented in an accompanying case study in this volume by the same author.
[75]. Scher, “Wind-Tunnel Investigation of the Behavior of Parachutes in Close Proximity to One Another,” NACA RM-L53G07 (1953); Scher and John W. Draper, “The Effects of Stability of Spin-Recovery Tail Parachutes on the Behavior of Airplanes in Gliding Flight and in Spins,” NACA TN-2098 (1950); Sanger M. Burk, Jr., “Summary of Design Considerations for Airplane Spin-Recovery Parachute Systems,” NASA TN-D-6866 (1972); H. Paul Stough, III, “A Summary of Spin-Recovery Parachute Experience on Light Airplanes,” AIAA Paper 90-1317 (1990).
[76]. James S. Bowman, Jr., and Burk, “Stall/Spin Studies Relating to Light General-Aviation Aircraft,” SAE Paper presented at the Society of Automotive Engineers Business Aircraft Meeting, Wichita, KS, Apr. 1973.
[77]. Burk, Bowman, and White, “Spin-Tunnel Investigation of the Spinning Characteristics of Typical Single-Engine General Aviation Airplane Designs: Part I-Low-Wing Model A.: Effects of Tail Configurations,” NASA TP-1009 (1977).
[78]. Stough, “A Summary of Spin-Recovery Parachute Experience on Light Air