The functional significance of nectridean tabular horns (Amphibia: Lepospondyli)

1980 ◽  
Vol 209 (1177) ◽  
pp. 513-537 ◽  

The order Nectridea of the subclass Lepospondyli is of Palaeozoic age. Within this order, later members of the Keraterpetontidae developed hyper-extended tabular horns, so that in plan view the skull is boomerang­ shaped. Many unsuccessful attempts have been made to explain this shape in functional terms. The two genera that show the greatest development of these horns, Diplocaulus Cope and Diploceraspis Romer, are analysed experimentally in a low-speed wind-tunnel. Differences between the two genera include that of size: the former is about twice the size of the latter genus and it has a prominent, ventrally directed flange on the quadratojugal-squamosal region not seen to the same extent in Diploceraspis . In Diplocaulus the otic notch, which has come to lie on the ventral side of the skull, is large and extends proportionally further towards the tip of the horn than in Diploceraspis . The otic notches may have supported pharyngeal pouches, developed as accessory respiratory organs. A full-scale model of the Diplocaulus skull was made from information obtained from published illustrations and casts. It was mounted in the wind-tunnel so that angles of incidence varying from -10 to +25° were possible, and a fixed body was modelled so as to account for interference effects. The Diploceraspis condition was simulated by removing the prominent quadratojugal flange. Four conditions were investigated: (1) the Diplocaulus model; (2) the Diploceraspis model; (3) the investigation of the effect of roughness of the surface of the model, to simulate the labyrinthodont condition of the dermal bones; and (4) an investigation of the effect of mouth-opening on the behaviour of the model. In addition, a flow-visualization test was carried out. All the experiments were carried out at a speed corresponding to the animal moving at 1.65 m/s in water. Coefficients of lift, drag and pitching moment were measured, over the range -10 to +25°, at two degree intervals. The significance of the results lies in the behaviour of the lift and pitching moment coefficient curves. The position of the centre of pressure does not move with the change of these two parameters and therefore the point of action of the centre of lift is fixed with respect to the occipital condyles. Forces exerted on the head are proportional to the deflexion of the head. Small but significant differences are seen when the curves for the two genera are compared. In Diplocaulus the lift and pitching moment curves cross the zero-line very close to the origin, but in the other genus they cross considerably to the left of the origin. Roughening of the surface in two stages causes lift coefficients to be diminished and drag increased. It is concluded that the surface of the living animals was smooth or almost so. With the smooth model, it was noted that when the mouth was opened that neither lift nor drag coeffi­cient was significantly altered. It is concluded that when taking prey these animals must have suffered little deceleration. The flow visualization tests show that two flow regimes operated on the upper surface of the Diplocaulus model. To begin with, the flow was streamlined and parallel to the midline over all the head area, but after a critical angle of incidence the central region of the head stalled and the flow over the horns became stabilized as laterally directed vortices. From all of the results it is believed that the Keraterpetontidae were active midwater feeders preying on small fish, larval amphibia, aquatic arthropods and gastropods. They used the unique physical properties of the head to effect steep climbing ascents from the lake or stream bed to attack their prey, before returning to the bottom. The differences between the two genera are related to their contrasting environments and the possible course of evolution giving rise to these extreme adaptations is considered. Dorso-ventral flattening is seen as an aid to an active mode of life in the two genera under discussion here, and the same possibly applies to the Labyrinthodontia as a whole.

2011 ◽  
Vol 115 (1167) ◽  
pp. 315-322 ◽  
Author(s):  
G. Gibertini ◽  
F. Auteri ◽  
G. Campanardi ◽  
C. Macchi ◽  
A. Zanotti ◽  
...  

Abstract A wide aerodynamic test campaign has been carried out on the tiltrotor aircraft ERICA at the Large Wind Tunnel of Politecnico di Milano by means of a modular 1:8 scale model in order to produce a dataset necessary to better understand the aerodynamic behaviour of the aircraft and to state its definitive design. The target of the tests was the measurement of the aerodynamic forces and moments in several different configurations and different attitudes. The test program included some conditions at very high incidence and sideslip angles that typically belong to the helicopter-mode flight envelope and measurements of forces on the tail and on the tilting wings. A large amount of data has been collected that will be very useful to refine the aircraft design. In general the aircraft aerodynamics do not present any critical problems, but further optimisation is still possible. From the viewpoint of drag in the cruise configuration, the sponsons of the landing gear seem to be worth some further design refinement since they are responsible for a 20% drag increase with respect to the pure fuselage configuration. On the contrary, the wing fairing has proved to work well when the aircraft longitudinal axis is aligned with the wind, providing just a slight drag increase. Two other interesting aspects are the quite nonlinear behaviour of the side force for the intermediate sideslip angles as well as the noticeable hysteresis in the moment coefficient at very high incidence angles.


Proceedings ◽  
2020 ◽  
Vol 49 (1) ◽  
pp. 104
Author(s):  
Kenichi Nakagawa ◽  
Hiroaki Hasegawa ◽  
Masahide Murakami

The purpose of this study is to investigate the difference in aerodynamic properties between the feather shuttlecock and the synthetic shuttlecock. In particular, we focus on the aerodynamic stability of the two types of shuttlecock during impulsive change of an angle of attack (flip movement). Wind tunnel experiments are performed by using two types of the badminton shuttlecock (feather and synthetic shuttlecocks) to measure the fluid forces, and to visualize the flow fields around the shuttlecock. It is confirmed that the pitching moment coefficient at a near-zero angle-of-attack for feather shuttlecock is larger than that for synthetic shuttlecock. The results indicate that the feather shuttlecock demonstrates high stability in response to the flip phenomenon.


2013 ◽  
Vol 391 ◽  
pp. 143-149
Author(s):  
Yan Hua Zhang ◽  
Hua Xing Li ◽  
Deng Cheng Zhang ◽  
Liang Qu

In this paper, the aerodynamic characteristics of the rocket model that might be used in a cabin air-launched system have been studied through experiments in low speed wind tunnel. The angle of incidence range is 0-80°, and the speed is 17m/s or 25m/s, including typical flight conditions prior to engine ignition. Forces and moments were measured through six-component balance. It is found that vortex asymmetry appears under certain condition with zero side slip. Asymmetrical phenomenon leads to larger side force and yaw moment, which can affect the trajectory of the rocket and put the carrier aircraft at risk. In addition, changes in regulation of the pitching moment with angle of attack are important to longitudinal stability, so the model with convergent-expanded afterbody was designed to improve stability. The effects of nose bluntness and forebody strakes on side force and yaw moment were presented, and the differences of aerodynamic characteristics with pointed and blunt nose, with and without forebody strakes were described. Results show that nose bluntness delays the appearance of asymmetric vortex, and the maximum side force is reduced by at least 50%. The forebody strakes reduce side force and yaw moment by weakening the asymmetric vortical interactions. The results can provide some references for designing the cabin air-launched rocket.


Fluids ◽  
2021 ◽  
Vol 6 (12) ◽  
pp. 451
Author(s):  
Karpovich Elena ◽  
Gueraiche Djahid ◽  
Sergeeva Natalya ◽  
Kuznetsov Alexander

In this paper, we addressed the flow patterns over a light boxplane scale model to explain the previously discovered disagreement between its predicted and experimental aerodynamic characteristics. By tuft flow and CFD visualization, we explored the causes yielding a large zero lift pitching moment coefficient, lateral divergence, difference in fore and aft elevator lift, and poor high lift performance of the aircraft. The investigation revealed that the discrepancy in the pitching moment coefficient and lateral stability derivatives can be attributed to insufficient accuracy of the used predictive methods. The difference in fore and aft elevator lift and poor high lift performance of the aircraft may occur due to the low local Reynolds number, which causes the early flow separation over the elevators and flaperons when deflected downward at angles exceeding 10°. Additionally, some airframe changes are suggested to alleviate the lateral divergence of the model.


2021 ◽  
Vol 11 (8) ◽  
pp. 3315
Author(s):  
Fabio Rizzo

Experimental wind tunnel test results are affected by acquisition times because extreme pressure peak statistics depend on the length of acquisition records. This is also true for dynamic tests on aeroelastic models where the structural response of the scale model is affected by aerodynamic damping and by random vortex shedding. This paper investigates the acquisition time dependence of linear transformation through singular value decomposition (SVD) and its correlation with floor accelerometric signals acquired during wind tunnel aeroelastic testing of a scale model high-rise building. Particular attention was given to the variability of eigenvectors, singular values and the correlation coefficient for two wind angles and thirteen different wind velocities. The cumulative distribution function of empirical magnitudes was fitted with numerical cumulative density function (CDF). Kolmogorov–Smirnov test results are also discussed.


Author(s):  
Kun Chen ◽  
Zhiwei Shi ◽  
Shengxiang Tong ◽  
Yizhang Dong ◽  
Jie Chen

There is an obvious aerodynamic interference problem that occurs for a quad tilt rotor in near-ground hovering or in the conversion operating condition. This paper presents an aerodynamic interference test of the quad tilt rotor in a wind tunnel. A 1:35 scale model of the quad tilt rotor is used in this test. To substitute for the ground, a moveable platform is designed in a low-speed open-loop wind tunnel to simulate different flight altitudes of the quad tilt rotor in hovering or forward flight. A rod six-component force balance is used to measure the loads on the aircraft, and the flow field below the airframe is captured using particle image velocimetry. The experimental results show that the ground effect is significant when the hover height above the ground is less than the rotor diameter of the quad tilt rotor aircraft, and the maximum upload of the airframe is approximately 12% of the total vertical thrust with the appearance of obvious fountain flow. During the conversion operating condition, the upload of the airframe is reduced compared with that in the hovering state, which is affected by rotor wake and incoming flow. The aerodynamic interference test results of the quad tilt rotor aircraft have important reference value in power system selection, control system design, and carrying capacity improvement with the advantage of ground effect.


AIAA Journal ◽  
10.2514/2.841 ◽  
2000 ◽  
Vol 38 (10) ◽  
pp. 1879-1888 ◽  
Author(s):  
R. Yano ◽  
V. Contini ◽  
E. Plonjes ◽  
P. Palm ◽  
S. Merriman ◽  
...  

2013 ◽  
Vol 115 (2) ◽  
pp. 211-219 ◽  
Author(s):  
Merlijn De Paepe ◽  
Jan G. Pieters ◽  
Wim M. Cornelis ◽  
Donald Gabriels ◽  
Bart Merci ◽  
...  

1999 ◽  
Author(s):  
W. Beaulieu ◽  
V. Bityurin ◽  
A. Klimov ◽  
S. Leonov ◽  
A. Pashina ◽  
...  

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