The equation of a closed curve in two-dimensional polar coordinates is given by \( r = \frac{2}{\sqrt{\pi}} (1 - \sin \theta) \). The area enclosed by the curve is ___________ (answer in integer).
To find the area enclosed by the curve in polar coordinates, we use the formula for the area of a polar curve: \[ A = \frac{1}{2} \int_{\theta_1}^{\theta_2} r^2 \, d\theta \] Here, \( r = \frac{2}{\sqrt{\pi}} (1 - \sin \theta) \) and the curve is closed, so the limits of integration are from \( \theta = 0 \) to \( \theta = 2\pi \).
Step 1: First, square the function for \( r \): \[ r^2 = \left( \frac{2}{\sqrt{\pi}} (1 - \sin \theta) \right)^2 = \frac{4}{\pi} (1 - \sin \theta)^2 \] Now, substitute this into the area formula: \[ A = \frac{1}{2} \int_0^{2\pi} \frac{4}{\pi} (1 - \sin \theta)^2 \, d\theta \]
Step 2: Simplify the expression: \[ A = \frac{2}{\pi} \int_0^{2\pi} (1 - \sin \theta)^2 \, d\theta \] Expand the integrand: \[ (1 - \sin \theta)^2 = 1 - 2\sin \theta + \sin^2 \theta \] Thus, the integral becomes: \[ A = \frac{2}{\pi} \int_0^{2\pi} (1 - 2\sin \theta + \sin^2 \theta) \, d\theta \]
Step 3: Now, integrate term by term:
The integral of \( 1 \) from 0 to \( 2\pi \) is \( 2\pi \), The integral of \( -2\sin \theta \) from 0 to \( 2\pi \) is 0, The integral of \( \sin^2 \theta \) can be simplified using the identity \( \sin^2 \theta = \frac{1 - \cos(2\theta)}{2} \), and the integral of \( \frac{1 - \cos(2\theta)}{2} \) from 0 to \( 2\pi \) gives \( \pi \). Thus, the total integral is: \[ A = \frac{2}{\pi} \left( 2\pi + 0 + \pi \right) = \frac{2}{\pi} \times 3\pi = 6 \] Therefore, the area enclosed by the curve is: \[ \boxed{6} \]
A single-stage axial compressor, with a 50 % degree of reaction, runs at a mean blade speed of 250 m/s. The overall pressure ratio developed is 1.3. Inlet pressure and temperature are 1 bar and 300 K, respectively. Axial velocity is 200 m/s. Specific heat at constant pressure, \( C_p = 1005 \, {J/kg/K} \) and specific heat ratio, \( \gamma = 1.4 \). The rotor blade angle at the outlet is __________ degrees (rounded off to two decimal places).
An ideal ramjet with an optimally expanded exhaust is travelling at Mach 3. The ambient temperature and pressure are 260 K and 60 kPa, respectively. The inlet air mass flow rate is 50 kg/s. Exit temperature of the exhaust gases is 700 K. Fuel mass flow rate is negligible compared to air mass flow rate. Gas constant is \( R = 287 \, {J/kg/K} \), and specific heat ratio is \( \gamma = 1.4 \). The thrust generated by the engine is __________ kN (rounded off to one decimal place).
A monopropellant liquid rocket engine has 800 injectors of diameter 4 mm each, and with a discharge coefficient of 0.65. The liquid propellant of density 1000 kg/m³ flows through the injectors. There is a pressure difference of 10 bar across the injectors. The specific impulse of the rocket is 1500 m/s. The thrust generated by the rocket is __________ kN (rounded off to one decimal place).
Air at temperature 300 K is compressed isentropically from a pressure of 1 bar to 10 bar in a compressor. Eighty percent of the compressed air is supplied to a combustor. In the combustor, 0.88 MJ of heat is added per kg of air. The specific heat at constant pressure is \( C_p = 1005 \, {J/kg/K} \) and the specific heat ratio is \( \gamma = 1.4 \). The temperature of the air leaving the combustor is _______ K (rounded off to one decimal place).
An ideal turbofan with a bypass ratio of 5 has core mass flow rate, \( \dot{m}_a,c = 100 \, {kg/s} \). The core and the fan exhausts are separate and optimally expanded. The core exhaust speed is 600 m/s and the fan exhaust speed is 120 m/s. If the fuel mass flow rate is negligible in comparison to \( \dot{m}_a,c \), the static specific thrust (\( \frac{T}{\dot{m}_a,c} \)) developed by the engine is _________ Ns/kg (rounded off to the nearest integer).