Space particulate radiation is reviewed, the damage mechanisms are discussed, and estimates are made of the hazardous nature of the various radiation zones. The existing capability for reproducing the space environment in ground test facilities is evaluated. It is concluded that the duplication of the complete space environment is not possible but that useful testing can be accomplished with existing techniques. Research programs are proposed for the evaluation of ground test requirements.

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

An examination was made of the utilization of the effective moment parameter, that has been used for many years, in relation to a recently devised procedure that involves the concept of an effective angle of attack for the nonlinear motion history being analyzed. This procedure provides an approximate direct relationship between an effective moment parameter measurement and its parent nonlinear moment curve, for a large family of nonlinearities. Both the additional use of the effective moment...

Topics: DTIC Archive, Welsh, C J, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

A program was conducted at the Arnold Engineering Development Center (AEDC) to design, fabricate, and test new full-scale angle-of-attack and sideslip vanes for the newly developed flight path accelerometer (FPA) to alleviate the dynamic stability problem of the previous vanes. The investigation was conducted in the von Karman Gas Dynamics Facility (VKF) Supersonic Wind Tunnel (A) and in the Propulsion Wind Tunnel Facility (PWT) Aerodynamic Wind Tunnel (4T). From dynamic stability tests of...

Topics: DTIC Archive, Uselton, James C, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

An analytical study was made of the feasibility of using an MHD- augmented arc as the primary component of a large reentry vehicle test facility. Computer studies of the performance of MHD accelerator channels were made for systems having channel input power of 50 MW to 1,700 MW. It was determined that complete simulation of reentry conditions is not possible in a single extended- flow facility. The studies showed, however, that very large increases in performance over existing arc facilities...

Topics: DTIC Archive, Whitehead, G L, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

A review of the assumptions made in the theory of the classical integrating sphere is given. The validity of these assumptions as applied to a modified integrating sphere is discussed in terms of a computer analysis and experimental data. The results of the analysis indicate that a possible error of 15 percent may be introduced into the absolute reflectance determinations. This can occur when the classical theory is applied to a modified integrating sphere using the angular-hemispherical...

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *REFLECTOMETERS, *SPHERES,...

At electron densities greater than 10 to the 12th power/ cc, ionization and recombination proceed predominantly by sequential transitions between adjacent energy levels induced by collisions with free electrons. Similar models for this process have been developed by various investigators. This report develops closed-form expressions for ionization and recombination of effective one-electron atoms by modifying the Byron model and determining analytically the critical energy level in equilibrium...

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *RECOMBINATION REACTIONS,...

A simple numerical algorithm is presented for the computation of the equilibrium composition of complex gas mixtures based upon the equilibrium constant approach. The algorithm uses a little-known form of the quadratic root extraction formula to solve for the equilibrium composition using a successive substitution with iteration to convergence technique. Experience with the algorithm for various complex gas mixtures has revealed excellent stability/convergence properties. Its application in...

Topics: DTIC Archive, Adams, Jr, John C, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

A method is presented for numerically integrating a system of stiff, first-order differential equations. This method is based on transforming the set of dependent variables so that the resulting system will not be stiff; the transformed system is then integrated by the Runge-Kutta method. The resulting procedure is often appreciably faster than classical methods in that a much larger step size is allowable with nominal increase in step computation time. Applications and results are discussed...

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *NUMERICAL INTEGRATION,...

Studies of the trapping of hydrogen and helium by condensing Freon C- 318 (C4F8) on a 77K surface have indicated that no pumping of the gases occurred. Freon was added to a predominately hydrogen atmosphere at rates from 1.52 x 10 to the -3rd to 0.73 torr-liters/sec with no change recorded in the partial pressure of hydrogen. A similar experiment was made with helium and no pumping was noted. It was observed that the mass spectrometer indicated a significant reduction in the partial pressure of...

Topics: DTIC Archive, Dawbarn, Ronald, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *CYCLOBUTANES,...

Unstructured methods for region discretization have become common in computational fluid dynamics (CFD) analysis because of certain benefits they have over structured meshes (where the discretization of the domain reflects some type of consistent geometrical regularity). Unstructured meshes are powerful tools for efficiently defining complex geometries and also lend themselves to analysis techniques such as adaptive mesh refinement (AMR) where the properties of the mesh adapt to the properties...

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *EQUATIONS, *MESH, ADAPTIVE...

A partial altitude military qualification test of the TF37-GE-1 turbofan engine was conducted in accordance with the procedures outlined in MIL- E-5009B dated January 1958. Steady-state and/or transient data were obtained at flight conditions in the altitude range from sea level to 36,000 ft and in the Mach number range from 0 to 1.0 with standard, hot, and cold atmospheres. The steady-state engine performance in terms of net thrust and specific fuel consumption was equal to or better than the...

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *TURBOFAN ENGINES, ALTITUDE,...

Topics: DTIC Archive, RITTENHOUSE, L E, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *TRANSONIC...

A Mollier diagram for air, including the effects of dissociation and ionization, as well as of intermolecular potentials to the second virial correction, is presented. The range of temperatures extends from the saturation line to 15,000 K and the range odensities, from 10 to the -7th power to approximately 200 amagats.

Topics: DTIC Archive, Little, Wanda J, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *AIR, DENSITY,...

The thrust produced by a d-c arc-jet plasma generator operating with argon was measured and used to determine the division of the energy added to the gas between that which produced excitation and ionization and that which served to increase the translational energy of the gas. Energy division predicted by the Rayleigh heat addition theory was compared with the experimental determination and was found to be in fair agreement (15 to 30 percent). The plasma generator was operated at electrical...

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *ARC JET ENGINES, ARGON,...

The results from an experimental study of an expansion tube conducted at the von Karman Gas Dynamics Facility (VKF) are presented and discussed. The research was conducted in two facilities: (1) a 6.75-in.-diam Modified Expansion Tube (MET) which utilizes a partially steady and partially unsteady expansion process, and (2) a 4-in.-diam (constant diameter) High Density Shock Tube (HDST) operated in an expansion tube mode for a completely unsteady expansion of the shock-heated gas to the final...

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *HYPERSONIC FLOW, *SHOCK,...

A summary of the work in holography at AEDC is presented. The work includes basic and applied research with emphasis on the applications of holography to aerodynamic testing.

Topics: DTIC Archive, Trolinger, J D, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *AERODYNAMICS,...

Analysis of experimental pressure distributions and force and moment coefficients for a 9-deg half-angle spherically blunted cone is presented based on an ideal gas (y = 1.4) three-dimensional characteristics solution developed by General Applied Sciences Laboratory (GASL). Comparisons are also made with predictions based on modified Newtonian theory.

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *ANGLE OF ATTACK, *PRESSURE,...

Calibration of the shock tunnel component of the Counterflow Range (I) operating with a new nozzle throat designed to yield Mach 7.5 is reported. Transverse pitot-pressure profiles and heat-transfer rates on a hemisphere-cylinder model in the test section were measured at four flow conditions. A single probe was traversed along the nozzle centerline to determine the streamwise pitot-pressure gradient. Shock detachment distances for a hemisphere-cylinder were measured to determine when helium...

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *HYPERSONIC VELOCITY, *SHOCK...

Interactions of model rocket plumes and the free stream at varying simulated altitudes have been investigated in an altitude simulation chamber. Free-stream variables were Mach number, gas, total temperature, and total pressure. Model rocket parameter variables were exhaust gas, area ratio, chamber total pressure and total temperature, and the orientation of the model relative to the free stream. In addition to pitot probe measurements, plume photographs and density measurements were obtained...

Topics: DTIC Archive, Smithson, H K, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *EXHAUST FLAMES,...

The general problem of the interaction between a monatomic gas and a solid surface is investigated from a mathematical point of view by the use of a scattering kernel. This general scattering kernel must fulfill the obvious conditions of normalization and non-negativity and has recently been shown to also satisfy the condition of detailed balancing or reciprocity. It is shown that calculated parameters are related to a tangential and a normal thermal accommodation coefficient. The scattering...

Topics: DTIC Archive, Kinslow, Max, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *SURFACES, ARGON,...

Force and moment coefficients were obtained on three models of a proposed lenticular rocket shape at Mach numbers 3, 4, and 5 for angles of attack from -5 to +15 deg and a constant Reynolds number of 1.5 million. The variation of the zero-lift drag coefficient with Reynolds number was also obtained for each Mach number over a Reynolds number range from 0.2 to 3.7 million. Visual flow patterns obtained on each model by the china-clay technique showed regions of flow separation at all Mach...

Topics: DTIC Archive, Anderson, A, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *RIVETED JOINTS,...

Many aerodynamic configurations are too complex to be represented by a single computational mesh. A multiple-mesh domain decomposition method called chimera has been developed to allow complex aerodynamic configurations to be modeled by a system of individually generated meshes, each representing a component of the overall configuration. The chimera approach requires the use of two computer codes, PEGSUS and a flow solver. PEGSUS calculates the interactions among the meshes and produces a file...

Topics: DTIC Archive, Suhs, N E, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *COMPUTER PROGRAMS,...

A brief investigation was conducted in the PWT Transonic Model Tunnel to check the validity of previous calibration results for two commonly used test section configurations. Static pressure measurements were made along the tunnel centerline and along the centerline of the top wall of the test section; simultaneous measurements of stilling chamber and plenum chamber pressures were obtained. The results of this investigation showed that the previous calibration results for a test section having...

Topics: DTIC Archive, NICHOLS, J H, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *TRANSONIC WIND...

Topics: DTIC Archive, ANDERSON, A, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *AERODYNAMIC...

A model study was made on rocket tailoff, using both annular-type and centerbody-type auxiliary ejectors. The investigation was conducted in the T- 5BR1 Altitude Test Cell with steam and air as the driving fluids for both the simulated rocket and annular or centerbody-type ejector. Performance was obtained for the simulated rocket and ejector running individually as a diffuser ejector and for both the simulated rocket and ejector operating in tandem. The ejector was used to evacuate the test...

Topics: DTIC Archive, HALE, JAMES W, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *DIFFUSERS,...

Topics: DTIC Archive, ANDERSON, ADRIAN, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *GUIDED...

A mixing chamber employing upstream injection of the secondary airflow was designed and tested in conjunction with a Mach 4.0 nozzle. Mixing chamber configurations with total length to maximum diameter ratios of 1.7 and 2.3 were investigated. The mixer was designed for a secondary to primary mass flow ratio of 2.57 and a primary to stilling chamber pressure ratio of 4.78. A uniform temperature profile with not more than 5 percent variation at the exit of the Mach 4.0 nozzle was required. The...

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *SUPERSONIC FLOW, AIR,...

Rules of similarity analysis are applied to develop criteria for deducing from model experiments steady-state and transient temperature distributions for a typical space vehicle element exposed to space conditions. The specific purpose is to determine if useful information can be obtained on models in space environment chambers. Thermal similarity criteria are deduced from expressions for transient conduction with radiation boundary conditions. Based on these criteria, a prototype and nominally...

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *SPACECRAFT, *SPACECRAFT...

A theoretical real-gas analysis of the expansion tunnel is presented. A digital computer program, developed for this investigation, is discussed and Fortran listings and flow charts are included. Tunnel performance, test gas slug length, and 'working' parameters are given for several expansion area ratios. Driver temperature and energy requirements are given for specific cases.

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *TEST FACILITIES, AERODYNAMICS,...

Some fundamental concepts of units, dimensions, and physical measurements are discussed, and illustrations of the misunderstandings that exist in the literature concerning these concepts are given. The differences between measure and physical equations are outlined, and a simple example is considered. The choice of how many and which units to use as basic is shown to be completely arbitrary, and the choice is usually made to produce maximum accuracy and convenience. Various mechanical, thermal,...

Topics: DTIC Archive, Kinslow, Max, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *BIBLIOGRAPHIES,...

Wind tunnel tests were conducted in the Arnold Engineering Development Center (AEDC) Aerodynamic Wind Tunnel (4T) on a 0.06-scale model of the Minuteman Instrumented Payload Delivery System (MIPDS). Pressure distributions and force and moment data were obtained over a Mach number range from 0.5 to 1.3, at angles of attack from -6 to 24 deg, and at angles of roll from -180 to 165 deg.

Topics: DTIC Archive, Cahill, David M, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN,...

Pressure, heat transfer, drag, and shock detachment data were obtained for a hemisphere-cylinder model in the GDF Hotshot I hypervelocity wind tunnel.

Topics: DTIC Archive, BOISON, J C, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *BODIES OF...

Solutions for isothermal, isentropic, and constant Mach number (at a specified location) flows with constant acceleration are obtained. It is shown that in application to high-speed guns, these solutions necessitate variable gun geometry or heating of the propellant; both requirements are considered at present impractical. Numerical solutions which give constant projectile acceleration in a fixed geometry gun are computed for ideal and real hydrogen propellant. Using the latter, and the...

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *GAS FLOW, *LIGHT GAS GUNS,...

Equilibrium thermodynamic data are presented for argon from a log P of -6.9 to 4.2 and from a temperature of 300 to 35,000K, where P is pressure in atmospheres. These data are tabulated at constant pressure with temperature incremented. The dependent parameters are log H/R, log rho, Z, S/R, H/RT, and Z*. Several sources were used in assembling the data.

Topics: DTIC Archive, Brahinsky, Herbert S, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *ARGON,...

Specific heat and speed of sound data were computed for imperfect air. The thermodynamic data included the effects of two-body intermolecular forces, and the results were obtained by numerical interpolation and differentiation of the recent data of Hilsenrath and Klein (AD416040). Comparisons with previous perfect gas calculations showed small effects in the isentropic exponent gamma sub E and dimensionless speed of sound a/a sub a below one amagat and negligible effects on the specific heat...

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *AIR, MOLECULAR PROPERTIES,...

The state-of-the-art of cryosorption of hydrogen (H2) and helium by cold cryodeposited frost is reviewed and summarized in some detail, and the results of additional measurements of the sorption of H2 by carbon dioxide (CO2) frosts are reported. It is shown that the sorption capacity of the frost depends upon the conditions at which the frost was formed and upon its temperature history. Frosts formed in a manner to make them porous or disordered are shown to possess greater sorption capacities....

Topics: DTIC Archive, Templemeyer, K E, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *CRYOPUMPING,...

This report summarizes the instrumentation development effort that was initiated at the Arnold Engineering Development Center to effect plasma diagnostics during the long-term testing of electrical propulsion systems. Two different ion beam sources were instrumented to obtain the basic properties of the plasma, such as the electron temperature, electron and ion densities, and the space charge potentials. The basic in strumentation required to effect preliminary diagnostics are the ''plasma...

Topics: DTIC Archive, Whited, James B, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *DIAGNOSTIC...

An experimental investigation was conducted to determine the discharge coefficient of a venturi airflow meter with various diameter centerbodies installed. A critical flow venturi for which a theoretical discharge coefficient had been experimentally verified was used as the calibration standard. The discharge coefficients for the test venturi without centerbody and with centerbodies of two different diameters were determined over a range of venturi throat Reynolds numbers from 320,000 to...

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *FLOWMETERS, CALIBRATION,...

Static pressure and boundary-layer data were obtained over a rigid pressure shell at Mach numbers from 1.20 to 1.50 and Reynolds numbers from 1.04 to 4.20 x 10 to the 6th/ft in the 16-ft transonic tunnel. These data were obtained with and without addition of air into the boundary layer through a circular slot upstream of the test shell. Flutter characteristics of thin cylindrical shells were obtained at Mach numbers of 1.20 and 1.50 with and without boundary-layer blowing and shell axial...

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *AEROELASTICITY, *CYLINDRICAL...

To gather the required performance test data at the AEDC, a complex network of test instrumentation and data gathering equipment must operate as a system. Reliable test data depend upon the reliability of each individual unit of the system; therefore, known standards must be established to meet specific requirements. In addition, various research groups are engaged in special projects often requiring some accuracy level in the measurement of physical variables. In today's technology of the...

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *CALIBRATION, ELECTRICAL...

Equilibrium thermodynamic data are presented for argon from a temperature of 300 to 35,000K and from a log rho of -7.0 to 2.4, where rho is density in amagats. These data are tabulated at constant temperature with density incremented. The dependent parameters are Z, E/RT, H/RT, S/R, log P, and Z*. Several sources were used in assembling the data.

Topics: DTIC Archive, Brahinsky, Herbert S, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *ARGON,...

Topics: DTIC Archive, WARD, T R, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *AFTERBURNERS,...

Bidirectional distribution measurements were made of the plane- polarized radiant flux transmitted through roughened glass samples having various surface roughnesses. These monochromatic measurements were made in the plane of incidence as a function of the irradiance zenith angle. For an irradiance angle of 0 deg, it is found that as the surface roughness-to- wavelength ratio increases the relative binormal transmittance of the glass decreases and the bidirectional transmission distributions...

Topics: DTIC Archive, Smith, A M, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *LIGHT TRANSMISSION,...

An aerodynamic molecular beam and phase-sensitive detection system were used to investigate the spatial distributions of argon atoms reflected from solid argon for incident energies of from 0.30 (beam temperature of 1400K) to 0. 54 ev (beam temperature of 2500K), incident angles from 0 to 70 deg, and solid argon temperatures of 15K. Both in-plane and out-of-plane spatial distribution measurements were made, and highly nondiffuse supraspecular spatial flux distributions were observed for the...

Topics: DTIC Archive, Busby, M R, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *ARGON, *MOLECULAR...

Wind tunnel tests were conducted at Mach number 10 on a 9-deg half- angle cone model using a unique dynamic stability balance having three angular degrees of freedom. Data obtained at Re = 1,970,000 on models having different types of compound asymmetries revealed vast differences in the developed motion. A model with a center-of-gravity offset and a small, out-of-plane nose slice as the second asymmetry was found to have a totally unexpected type of instability. The instability was the rapid...

Topics: DTIC Archive, Ward, Jr , L K, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *CONICAL BODIES,...

The principal mechanisms of energy and momentum transfer between gas atoms and solid surfaces are considered for the range of impact energies encountered in high-speed flight (e.g., up to 10 ev). Included within are (1) introductory discussions of the nature of surfaces, intermolecular potentials, adsorption, and basic gas -surface interaction processes, (2) a critical survey of the definitions of energy and momentum accommodation coefficients, (3) summaries of existing theoretical and...

Topics: DTIC Archive, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *ENERGY, *GASES, *MOMENTUM,...

Experimental plume impingement pressure and heat-transfer-rate distributions on a flat plate with and without an external Mach number 18 stream are described. The plume was generated by expanding helium through a 1.61 area ratio nozzle, which simulated the initial shape of a rocket exhaust plume produced by a nozzle with an area ratio of 25 operating at an altitude of 262, 000 ft. Although the plume generator nozzle conditions were not varied, the quiescent environment conditions and external...

Topics: DTIC Archive, Strike, Jr, W T, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *EXHAUST...

The rapidly growing body of literature on turbine combustor modelling is reviewed. The analytical models are presented and discussed with particular emphasis placed on their ability to predict gross operating characteristics as well as pollutant emission levels. Comparison is made between theory and engine and laboratory experiments showing the general inaccuracies of current models. A suggestion for improvement of the best available model is made, and areas for fundamental research are pointed...

Topics: DTIC Archive, Osgerby, I T, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *EMISSION,...

The report presents the results of an experimental evaluation of a constant-area ejector-diffuser and three configurations of a variable-area ejector-diffuser at secondary-to-primary mass flow ratios of 0, 5, 10, and 15 percent.

Topics: DTIC Archive, Taylor, Delbert, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *DIFFUSERS,...

Static-force and moment and surface pressure data were obtained on a 0.06-scale representation of the Minuteman Instrumented Payload Delivery System (MIPDS) launch vehicle. The test was conducted at Mach numbers from 1.6 to 5.0 at free-stream Reynolds numbers, based on model length, from 28.4 to 23.6 million, respectively. The angle-of-attack range was from -12 to 12 deg, and the roll angle was from -180 to 180 deg. Results are presented to illustrate typical effects of variations in vehicle...

Topics: DTIC Archive, Lindsay, E E, ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN, *AERODYNAMIC...