A Prospective Open Labelled Phase-II Non Randomized Clinical Trial On “Karunjchirakam Chooranam” for Raktha Soorai Vaayu (Poly Cystic Ovarian Syndrome)

Siddha system of medicine is one among the traditional medical systems originated in India which has its foundations from superior wisdom of Siddhars. They are responsible for the Tamil medicine of the present day and also for many other sciences of public utility. Raktha soorai vayu mentioned in siddha literatures may be co-related with poly cystic ovarian syndrome in modern medical science. Poly Cystic Ovarian Syndrome (PCOS) is one of the most common reproductive health problems suffering of women .It is considering as a problem of anovulation and infertility along with the symptoms of irregular menses, obesity, insulin resistance, hirsuitism, acne, androgenic alopecia and recurrent miscarriage. Treatment of PCOS may be enhanced in all aspects of syndrome including short term problems like acne & infertility as well as long term problems such as obesity. Reviewing the modern science and Siddha literatures regarding PCOS, better understanding of symptoms, pathogenesis of PCOS and its proper line of Siddha treatment can be obtained. Various pre – clinical studies such as bio-chemical, phytochemical, anti –microbial, hypoglycemic, hypolipidemic and toxicity studies were carried out for Karunjchirakam Chooranam and relevant results were obtained. By this study, I planned to identify the PCOS syndrome early so as to encourage young women to seek timely treatment and prevent its long term complications. In most of the cases treated with Karunjchirakam Chooranam, better results were visible. All the concerned results were statistically analysed and found to be significant

Self-Activated Movable Flaps on Low Aspect Ratio Wings at Low Reynolds Numbers

Effectiveness of self-adaptive flaps in delaying flow separation on low aspect ratio wings of three different planforms were ascertained experimentally in a low speed wind tunnel at a Reynolds number of 105 based on their root chord. Flap widths between 0.08c and 0.15c; placement location between 0.4 x/c and 0.8 x/c were investigated. The flapped configurations exhibit good stall margin and higher CLmax in most cases. The chordwise placement location of adaptive flap for better lift enhancement varies with planform. Adaptive flaps placed at the maximum span location on a varying span planform exhibit better lift characteristics than flaps placed at other chordwise location. However, for a constant span planform like rectangle, chordwise location close to trailing edge seems to be optimal for flap placement. Full span flaps were efficient in obstructing the forward progression of reverse flow from stall vortex than part span flaps. The lift enhancing capabilities of double adaptive flapped configuration was relatively low compared to single adaptive flapped configuration. No detrimental effects were observed in the drag characteristics of the single flapped configurations of rectangular and inverse Zimmerman planform. However, significant drag increase was observed for the flapped configurations of Zimmerman model and double flapped configurations. The temporal behavior of the adaptive flap is aperiodic. Spectral analysis of the adaptive flap oscillation shows that it oscillates at multiple frequencies and the wing planform only influence the mean angle and magnitude of oscillation, while frequency of the oscillation seems to be flow dependent

Self-adaptive flaps on low aspect ratio wings at low Reynolds numbers

Self-adaptive flap is a bio-inspired passive flow control device which emulates the covert feathers of birds in a most rudimentary form. An exploratory study to ascertain the effectiveness of these self-adaptive flaps in delaying flow separation on low aspect ratio wings of three different planforms were carried out in a low speed wind tunnel at a Reynolds number of 105 based on their root chord. Flap widths between 0.08c and 0.15c; placement location between 0.4x/c and 0.8x/c were investigated. The flapped configurations exhibit good stall margin and higher CLmax in most cases. The chordwise placement location of adaptive flap for better lift enhancement varies with planform. Adaptive flap placed at the maximum span location on varying span planform exhibits better lift characteristics than flap placed at other chordwise location. However, for a constant span planform like rectangle, chordwise location close to trailing edge seems to be optimal for flap placement. No detrimental effects are observed in the drag characteristics of the single flapped configurations of rectangular and inverse Zimmerman planform. However, significant drag increase is observed for the flapped configurations of Zimmerman model and double flapped configurations. The temporal behavior of the adaptive flap is aperiodic. Spectral analysis of the flap oscillation shows multiple dominant frequencies between 10 Hz and 50 Hz for different angles of attack for both rectangular and inverse Zimmerman planform. The peaks occur at same frequencies for most angles of attack irrespective of planform. Skin friction pattern obtained from oil flow visualization experiments shows that the separation bubble which extends the entire chord for clean model at post-stall angles of attack, is contained upstream of the flap which leads to better post-stall lift characteristics

Experimental studies of propeller induced flow over typical micro air vehicle - AIAA 2013-0060

An experimental study has been carried out to explore the effect of propeller induced slipstream on the flow field of a fixed wing micro air vehicle (MAV). Tests were conducted at freestream velocity of 10m/s, corresponding to Reynolds number based on root chord of about 160000. Flow pattern on the surface of MAV planform with propeller-on and off condition was captured using oil flow visualization at four angles of incidence. Mean flow field on the MAV planform at four chordwise planes with propeller-on and off condition were measured using stereo PIV technique at angle of incidence of 24°. Little difference has been seen on the oil flow pattern at 10° and 15° angle of incidence between propeller-off and on condition. Small asymmetry in the flow topology was observe at 20° angle of incidence. Significant difference in flow field was observed at 24° between propeller-on and off condition. The induced slipstream from the propeller makes the flow well attached over the wing planform

Rudimentary emulation of covert feathers on low-ar wings for poststall lift enhancement.

Covert feathers, a group of feathers on the upper surface of bird wings, are one of birds’ features that aid them in flight at high angles of attack, making them more maneuverable. In a previous study, the authors found that a rudimentary emulation of this feature (termed a self-adaptive flap) enhances the poststall lift characteristics of low-aspect-ratio flat-plate wings at Re � 100;000. This enhancement, however, was found to vary with the different chordwise locations of the flap and across different planforms. In a continued effort to understand this further, two-dimensional particle image velocimetry investigation was carried out in the midspan plane of the low-aspect-ratio wings. For the varying-span elliptical wings, the results reveal that the flap/shear layer interaction promotes reattachment of the separated shear layer via increased entrainment. This reattachment location varies for the different chordwise location of the flap, resulting in a different extent of the separation bubble and bubble-induced camber, which in turn is responsible for different poststall lift enhancement. On the other hand, for the rectangular wing, the flap promotes large-scale vortex formation. The formation and shedding cycle of large-scale vortices has a significant impact on the mean-body forces because of which the time-averaged poststall lift is enhanced

PIV investigation of self-adaptive flap on low aspect ratio wings

Self-adaptive flap is a bio-inspired passive flow control device which emulates the covert feathers of birds in a most rudimentary form to delay flow separation. In a previous study, it was found that the use of self-adaptive flap on low aspect ratio wings at low Reynolds numbers increased the CLmaxand stall margin by more than 30%. In an effort to gain insight on the flow-field changes the self-adaptive flap effects on the suction surface of the wing with respect to its placement location, oil flow visualization and a two-dimensional particle image velocimetry (PIV) investigation werecarried out on low aspect ratio flat plate wings of rectangular, Zimmerman, and inverse Zimmerman planform at a Reynolds number of 105. The 2D-PIV investigations werecarried out on the mid span plane of the models. This paper reports the some of the pertinent results obtained from the investigation

Pressure measurement on NASA 0416 and NAL 7025 airfoils in the 1.5m wind tunnel

Experiments are being conducted in the 1.5m low speed wind tunnel to provide the required data for the design of the NAL Regional Transport Aircraft (RTA). In the first phase, pressure measurements have been conducted in the velocity range of 25-45 m/s and incidence angle range of -4 to 16 deg on the reference airfoil NASA 0416 and on the airfoil NAL 7025, designed for the RTA wing. The results show that our measurements compare well with those from NASA. The coefficients of pressure and lift show that the NAL 7025 airfoil has promise for being adapted for the RTA

Preliminary wind tunnel studies on Micro-Air Vehicles

A preliminary wind tunnel studies were carried out in the 0.55m low speed tunnel on the Micro Air Vehicle configurations which have been test flown. The flown MAV's vary both in planform and airfoil geometry. A 3-component internal strain gage balance was used to measure the aerodynamic data. The tests were carried out at a freestream velocity of 12 m/s and at angle of attack varying from -4 deg to 24 deg in 4 deg steps. A comparison of the aerodynamic characteristics of the airframe (wing and fuselage) was made in terms of lift slope, stall angle, minimum drag, aerodynamic efficiency (L/D) and the pitching momebt stability. Error ananlysis was made and the results were discussed. Detailed 6-component measurements, control surface effects, propelled model tests are planned in the second phase

Antioxidant Activity of Some Wild Mushrooms From Southern Western Ghats, India

Objective: To investigate the antioxidant activities of crude methanol extracts of 10 southern Western Ghats wild mushrooms. Methods: Crude methanol extracts from 10 mushrooms from southern Western Ghats, India were evaluated for their antioxidant activity by Nitric Oxide scavenging assay and DPPH scavenging assay. Results: The methanol extract of Trametes versicolor recorded maximum percentage of NO activity of 94% followed by Tricholoma equestre 92% at the concentration 50 µg/ml. However, the extract of Gymnopilus junonius (80.33%) and Tricholoma equestre (79%) tested against DPPH stable radicals reveals that the radical scavenging activity of wild mushrooms possessed excellent antioxidant capacity which increased with the increasing concentration of the extract. Conclusions: Gymnopilus junonius, Tricholoma equestre and Trametes versicolor have higher antioxidant activity showed both in Nitric Oxide scavenging assay and DPPH scavenging assay