SUMMARY
The shock wave cone half-angle for a supersonic airplane flying at Mach 2.30 is calculated using the formula sin(theta) = 1/M, where M represents the Mach number. For Mach 2.30, the half-angle is determined to be approximately 12.9 degrees. The calculation involves taking the inverse sine of the reciprocal of the Mach number, eliminating the need to divide by 2. This method provides a direct and accurate measurement of the shock wave cone half-angle.
PREREQUISITES
- Understanding of Mach number and supersonic flight
- Basic knowledge of trigonometric functions, particularly sine and inverse sine
- Familiarity with shock wave theory in aerodynamics
- Ability to perform calculations involving angles and ratios
NEXT STEPS
- Research the implications of shock wave cone angles on aircraft design
- Learn about the effects of different Mach numbers on shock wave behavior
- Explore advanced topics in supersonic aerodynamics
- Study the mathematical derivation of shock wave equations
USEFUL FOR
Aerospace engineers, aerodynamics researchers, and students studying supersonic flight dynamics will benefit from this discussion.