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Quantitative, kiloherz-rate measurement of carbon monoxide mole fractions by femtosecond two-photon, laser-induced fluorescence (TP-LIF) was demonstrated in high-pressure, luminous flames over a range of fuel-air ratios. Femtosecond excitation at 230.1 nm was used to pump CO two-photon rovibrational X1Σ+→B1Σ+ transitions in the Hopfield–Birge system and avoid photolytic interferences with excitation irradiance ∼1.7×1010 W/cm2. The effects of excitation wavelength, detection scheme, and potential sources of de-excitation were also assessed to optimize the signal-to-background and signal-to-noise ratios and achieve excellent agreement with theoretically predicted CO mole fractions at low and high pressure.

In this report we have obtained the drag and lift forces using CFD which can also be determined through experiments using wind tunnel testing. In experimental setup, the design model has to be placed in the test section. This process is quite laborious & (surely) cost more than CFD techniques cost for the same. Thus we have gone through analytical method then it can be validated by experimental testing. The analysis of the two dimensional subsonic flow over a NACA 0012 airfoil at various angles of attack and operating at a Reynolds number of 3×E+06 is presented. The CFD simulation results show close agreement with those of the experiments, thus suggesting a reliable alternative to experimental method in determining drag and lift.

CFD is a branch of Fluid Mechanics which rely on numerical methods and algorithms to solve and analyze problem that involves fluid flow. CFD analysis has been conducted to analyze flow pattern of supersonic rocket nozzle at various degree of divergent angle by using two dimensional axis-symmetric model, which solves governing equation by a control volume method. Variation in parameters like velocity, static pressure, turbulence intensity and temperature are being analyzed. Objective of this research is to is to investigate best suited divergent angle. The phenomena of oblique shock is visualized and it was found that at 15 degree of divergent angle it is completely eliminated from nozzle. Also intensity of velocity is found to have an increasing trend with increment in divergent angle thereby obtaining an optimum divergent angle which would eliminates instabilities due to shock and satisfy the thrust requirement from the nozzle.