To respond to your question LTF85199. Shock waves form perpenducular to the leading edge of the wing at the critical mach number for the wing. So if the wing is swept back and the airflow is M0.8, only the component of that perpendicular to the wing leading edge will count and will be less than M0.8. This means that if the aircraft can travel faster before shockwaves form and affect the aircraft.
Scan, do you know if it worked? Also i have a question for you, you know the swept wing design on commercial aircraft, what is its proporse, I know it cruise around M .8. So it it reducting the shock formed on top of the wing? or the shock wave created at the nose?
To respond to your question LTF85199. Shock waves form perpenducular to the leading edge of the wing at the critical mach number for the wing. So if the wing is swept back and the airflow is M0.8, only the component of that perpendicular to the wing leading edge will count and will be less than M0.8. This means that if the aircraft can travel faster before shockwaves form and affect the aircraft.
flyinkiwi01 3 years ago
Scan, do you know if it worked? Also i have a question for you, you know the swept wing design on commercial aircraft, what is its proporse, I know it cruise around M .8. So it it reducting the shock formed on top of the wing? or the shock wave created at the nose?
LTF85199 3 years ago