Answer:
An investigation is made to determine the performance of simple thin airfoils in the slightly supersonic flow region with the aid of the nonlinear transonic theory first developed by von Kármán[1]. Expressions for the pressure coefficient across an oblique shock and a Prandtl-Meyer expansion are developed in terms of a transonic similarity parameter. Aerodynamic coefficients are calculated in similarity form for the flat plate and asymmetric wedge airfoils, and curves are plotted. Sample curves for a flat plate and a specific asymmetric wedge are plotted on the usual coordinate grid of Cl, Cd,andCmc/4versus angle of attack and Cl versus Mach Number to illustrate the apparent features of nonlinear flow.
Explanation:
Explanation:
63 kg ice skater finishes her performance and crossed the finish line with a speed of 10.8 m/s
D. The flow of energy,heat, and work
Answer:
4.2 x 10⁷N
Explanation:
Given parameters:
Charge on ball:
q₁ = 3C
q₂ = 14C
Distance between balls = 9000m
Unknown:
Force acting on the two balls
Solution:
The force experienced by the two charges is given by coulombs law. It is mathematically expressed as;
F = 
where k = 9 x 10⁹Nm²/C²
q is the charges
r is the distance
Input the variables and solve;
F = 
= 4.2 x 10⁷N
Less than because a mile is 1600 meters
