A tube wind-tunnel technique for rocket propulsion testing
Short duration tube wind tunnel supersonic testing, noting Saturn S-1C base heating and solid propellant rocket base burning tests
Hendershot, K. C.↗
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Sonic-boom wind-tunnel testing techniques at high Mach numbers
Sonic boom wind tunnel testing techniques at high Mach numbers, giving sample pressure signatures
Miller, D. S.↗
A hypersonic force and moment test of a 0.006 scale model (466) of the 330.2 inch diameter external tank in the Ames Research Center 3.5 foot hypersonic wind tunnel (TA9F)
Data were obtained in a series of wind tunnel tests on the space shuttle external tank over an angle of attack range from 0 deg to 180 deg at Mach numbers of 5.3 and 10.4. Body roll angles varied from 0 deg to 315 deg for the Mach number 10.4 tests. A constant roll angle of 180 deg was used for all Mach number 5.3 tests. The effects of protuberances and Reynolds number on the force and moment coefficients were investigated.
Ramsey, P. E.↗
Reduction of wind-tunnel wall interference by controlled wall flow
Corrections for wind tunnel wall interferences are applied successfully to high lift models when the model to tunnel size ratio is small. The accuracy of the corrections becomes poorer when larger models are tested. An alternate method of testing was developed in which flow through the porous walls of the tunnel was actively controlled so as to approximate free air conditions in the neighborhood of the model during the test. The amount and distribution of the controlled flow through the walls is computed using a potential flow representation of the model based on the measured lift. Theoretical analysis is presented to prove the convergence of the method to free air conditions and to substantiate the general three dimensional theory of operation when the normal flow distribution is continuous. A two dimensional tunnel was constructed to evaluate the concept. Results show that substantial reduction of wall interference may be achieved with relatively low values of porosity of actively controlled walls.
Bernstein, S.↗
Analytical evaluation of tilting proprotor wind tunnel test requirements
Specific test requirements related to the wind tunnel testing of the XV-15 advanced tilt rotor research aircraft were determined. The following analytical tools were developed: (1) digital simulation of the XV-15, incorporating a simplified tunnel support model, control system loop, measurement lags, gust disturbances, and sensor noise, (2) specialization of existing data analysis programs to the high order XV-15 dynamical model (transfer function program, a time series analysis program, an advanced maximum likelihood parameter identification program), (3) several auxiliary programs to provide estimates of damping from transfer functions as well as calculations of model decomposition of system response. The following results were discussed: (1) modelling of the aircraft, instrumentation, and controls, (2) results of the rotor/cantilever wing model and coupled wing, (3) examples of data prediction with system identification techniques, and (4) detailed conclusions and recommendations.
Hall, W. E., Jr.↗
Toward the correctable-interference transonic wind tunnel
The concept of a correctable-interference transonic wind tunnel combining a capability for wall-interference assessment with a limited capability for wall control is introduced. Recent progress toward achieving the interference assessment capability is described. The feasibility of using experimentally measured data directly as boundary values for the assessment in lieu of more generally formulated but less accurate wall boundary conditions is demonstrated for two-dimensional subsonic flows. Also, a procedure for transonic analysis of wall interference which leads to a rational definition of the wall-induced perturbation field within the context of nonlinear transonic flow computations is outlined in principle.
Kemp, W. B., Jr.↗
The future of wind tunnel technology in Germany
The practical value of a wind tunnel which is not dependent solely on size or achievable Reynolds number was examined. Measurement, interpretative and evaluative procedures developed in small facilities were also studied.
Ewald, B.↗
Development and validation of a hybrid-computer simulator for a transonic cryogenic wind tunnel
A study was undertaken to model the cryogenic wind tunnel process, to validate the model by the use of experimental data from the Langley 0.3 Meter Transonic Cryogenic Tunnel, and to construct an interactive simulator of the cryogenic tunnel using the validated model. Additionally, this model was used for designing closed loop feedback control laws for regulation of temperature and pressure in the 0.3 meter cryogenic tunnel. The global mathematical model of the cryogenic tunnel that were developed consists of coupled, nonlinear differential governing equations based on an energy state concept of the physical cryogenic phenomena. Process equations and comparisons between actual tunnel responses and computer simulation predictions were examined. Also included are the control laws and simulator responses obtained using the feedback schemes for closed loop control of temperature and pressure were also included.
Thibodeaux, J. J.↗
Rod-Wall Sound Shield for Wind Tunnels
Test model is shielded from turbulence radiated from wind tunnel walls. Shield overcomes problems caused by leading-edge configuration and leading edge angle of inclination of previous designs. Has successfully maintained a laminar rather than turbulent boundary layer.
Creel, T. R. J.↗
The development of cryogenic wind tunnels and their application to maneuvering aircraft technology
Cryogenic wind tunnels are considered as a means of studying high Reynolds number (Re) complicated flows encountered by high maneuvering lift and high angles of attack characteristic of modern fighter aircraft. Large decreases in the viscous force while the inertial force remains constant are provided by the use of cryogenic facilities. A 2.5 m square tunnel is nearing completion at the National Transonic Facility (NTF), and will be driven by synchronous motors having a total power of 120,000 hp. The tunnel, using N2 as the cryogenic fluid, will allow large Re sweeps at constant dynamic pressure and dynamic pressure, and aeroelastic sweeps at constant Re; full altitude (air density) and acceleration force simulation will also be possible. Advances in model and strain gage balance technologies for use at the NTF are outlined, and experiments with buffet are described.
Polhamus, E. C.↗
Control of large thermal distortions in a cryogenic wind tunnel
The National Transonic Facility (NTF) is a research wind tunnel capable of operation at temperatures down to 89K (160 R) and pressures up to 900,000 Pa (9 atmospheres) to achieve Reynolds numbers approaching 120,000,000. Wide temperature excursions combined with the precise alignment requirements of the tunnel aerodynamic surfaces imposed constraints on the mechanisms supporting the internal structures of the tunnel. The material selections suitable for this application were also limited. A general design philosophy of utilizing a single fixed point for each linear degree of freedom and guiding the expansion as required was adopted. These support systems allow thermal expansion to take place in a manner that minimizes the development of thermally induced stresses while maintaining structural alignment and resisting high aerodynamic loads. Typical of the support mechanisms are the preload brackets used in the fan shroud system and the Watts linkage used to support the upstream nacelle. The design of these mechanisms along with the basic design requirements and the constraints imposed by the tunnel system are discussed.
Gustafson, J. C.↗
Airloads research study. Volume 2: Airload coefficients derived from wind tunnel data
The development of B-1 aircraft rigid wind tunnel data for use in subsequent tasks of the Airloads Research Study is described. Data from the Rockwell International external structural loads data bank were used to generate coefficients of rigid airload shear, bending moment, and torsion at specific component reference stations or both symmetric and asymmetric loadings. Component stations include the movable wing, horizontal and vertical stabilizers, and forward and aft fuselages. The coefficient data cover a Mach number range from 0.7 to 2.2 for a wing sweep position of 67.5 degree.
Bartlett, M. D.↗
An evaluation of factors affecting the flow quality in wind tunnels
Tests were conducted in a number of NASA wind tunnels to measure disturbance levels and spectra in their respective settling chambers, test sections, and diffusers to determine the sources of these disturbances. Results indicate that properly designed and located second minimum in transonic tunnels prevent fluctuation originating at struts and in diffusers from propagating upstream into the test section. The installation in or upstream of the settling chamber of carefully selected screens, honeycomb, and acoustic baffles could further reduce test section turbulence levels and scales without significant pressure losses. The performance of these modifications is strongly influenced by tunnel geometry and their influence on the mean flow around the circuit.
Owen, F. K.↗
Transonic wind-tunnel investigation of the Galileo Probe parachute configuration
Wind-tunnel tests have been made of 1/4-scale and 1/2-scale models of the Galileo Probe conical ribbon-parachute at flight conditions. For the Galileo mission, the parachute is deployed behind a blunt shape at transonic speed. The investigation was initiated to verify the solutions to the delayed main-parachute opening with squidding that was observed in the 1982 Galileo Probe system balloon drop test. In addition to varying model scale, the forebody shape, angle of attack, dynamic pressure, Mach number, and canopy trailing distance behind the forebody were varied to determine their effect on parachute performance. Both steady-state and deployment tests were conducted. Parachute drag was measured and was seen to degrade severely at canopy trailing distances of 5.5 and 7 forebody diameters. Performance was shown to be good at the trailing distances of 9 and 11 diameters. A second balloon drop test demonstrated the desired parachute performance at the system level.
Corridan, R. E.↗
A voice-actuated wind tunnel model leak checking system
A voice-actuated wind tunnel model leak checking system was developed. The system uses a voice recognition and response unit to interact with the technician along with a graphics terminal to provide the technician with visual feedback while checking a model for leaks.
Larson, W. E.↗
Wall Interference in Two-Dimensional Wind Tunnels
Viscosity and tunnel-wall constraints introduced via boundary conditions. TWINTN4 computer program developed to implement method of posttest assessment of wall interference in two-dimensional wind tunnels. Offers two methods for combining sidewall boundary-layer effects with upper and lower wall interference. In sequential procedure, Sewall method used to define flow free of sidewall effects, then assessed for upper and lower wall effects. In unified procedure, wind-tunnel flow equations altered to incorporate effects from all four walls at once. Program written in FORTRAN IV for batch execution.
Kemp, William B., Jr.↗
The use of NASTRAN in the design of wind tunnel research aircraft
The relationship between NASTRAN and the wind tunnel model design process is discussed. Specific cases illustrating the use of NASTRAN for static, heat transfer, dynamic, and aeroelastic analyses are presented. Advantages and disadvantages of using NASTRAN are summarized.
Cooper, Michael↗
Performance characteristics from wind-tunnel tests of a low-Reynolds-number airfoil
Wind tunnel lift and pitching-moment data have been obtained from pressure measurements, and drag data from wake surveys, for an Eppler 387 low Reynolds number airfoil over the Re range of 60,000 to 460,000; oil flow visualizations were also used to determine laminar separation and turbulent reattachment locations. Airfoil performance is found to be dominated by laminar separation bubbles below Re 200,000, and two flow regimes, namely laminar separations with and without turbulent reattachment, were observed at the same angle-of-attack for an Re of 60,000.
Mcghee, Robert J.↗