Which outcome occurs when using the Bernoulli equation to model airflow over an airplane wing reaches transonic speeds?

💡 Explanation

Shock waves form as airflow locally exceeds the speed of sound and disrupt the pressure balance predicted by Bernoulli's principle. Therefore, lift characteristics change unpredictably due to complex wave interactions, rather than remaining unaffected or predictable viscous forces because viscosity is usually negligible at flight.

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