Answer:
Hold the tape in place and go down to the end.
Explanation:
Answer:
The lift coefficient is 0.3192 while that of the moment about the leading edge is-0.1306.
Explanation:
The Upper Surface Cp is given as
![Cp_u=-0.8 *0.6 +0.1 \int\limits^1_{0.6} \, dx =-0.8*0.6+0.4*0.1](https://tex.z-dn.net/?f=Cp_u%3D-0.8%20%2A0.6%20%2B0.1%20%5Cint%5Climits%5E1_%7B0.6%7D%20%5C%2C%20dx%20%3D-0.8%2A0.6%2B0.4%2A0.1)
The Lower Surface Cp is given as
![Cp_l=-0.4 *0.6 +0.1 \int\limits^1_{0.6} \, dx =-0.4*0.6+0.4*0.1](https://tex.z-dn.net/?f=Cp_l%3D-0.4%20%2A0.6%20%2B0.1%20%5Cint%5Climits%5E1_%7B0.6%7D%20%5C%2C%20dx%20%3D-0.4%2A0.6%2B0.4%2A0.1)
The difference of the Cp over the airfoil is given as
![\Delta Cp=Cp_l-Cp_u\\\Delta Cp=-0.4*0.6+0.4*0.1-(-0.8*0.6-0.4*0.1)\\\Delta Cp=-0.4*0.6+0.4*0.1+0.8*0.6+0.4*0.1\\\Delta Cp=0.4*0.6+0.4*0.2\\\Delta Cp=0.32](https://tex.z-dn.net/?f=%5CDelta%20Cp%3DCp_l-Cp_u%5C%5C%5CDelta%20Cp%3D-0.4%2A0.6%2B0.4%2A0.1-%28-0.8%2A0.6-0.4%2A0.1%29%5C%5C%5CDelta%20Cp%3D-0.4%2A0.6%2B0.4%2A0.1%2B0.8%2A0.6%2B0.4%2A0.1%5C%5C%5CDelta%20Cp%3D0.4%2A0.6%2B0.4%2A0.2%5C%5C%5CDelta%20Cp%3D0.32)
Now the Lift Coefficient is given as
![C_L=\Delta C_p cos(\alpha_i)\\C_L=0.32\times cos(4*\frac{\pi}{180})\\C_L=0.3192](https://tex.z-dn.net/?f=C_L%3D%5CDelta%20C_p%20cos%28%5Calpha_i%29%5C%5CC_L%3D0.32%5Ctimes%20cos%284%2A%5Cfrac%7B%5Cpi%7D%7B180%7D%29%5C%5CC_L%3D0.3192)
Now the coefficient of moment about the leading edge is given as
![C_M=-0.3*0.4*0.6-(0.6+\dfrac{0.4}{3})*0.2*0.4\\C_M=-0.1306](https://tex.z-dn.net/?f=C_M%3D-0.3%2A0.4%2A0.6-%280.6%2B%5Cdfrac%7B0.4%7D%7B3%7D%29%2A0.2%2A0.4%5C%5CC_M%3D-0.1306)
So the lift coefficient is 0.3192 while that of the moment about the leading edge is-0.1306.
Answer:
Map and avoid high-risk zones.
Build hazard-resistant structures and houses.
Protect and develop hazard buffers (forests, reefs, etc.)
Develop culture of prevention and resilience.
Improve early warning and response systems.
Build institutions, and development policies and plans.
Explanation: