Aerodynamic stall happens when aeroplanes' angle of attack increases beyond a certain point, then lift begins to decrease. No matter what speed the aeroplane is flying at, when the critical angle of attack is exceeded, the aeroplane will be at the risk of stalling, because of the breakdown of the smooth airflow.

Let be the mean critical angle of attack (in degrees) for the average airfoil used on general aviation aeroplanes. The research and development team at Aves Air is interested in finding out whether aeroplanes' mean critical angle of attack has changed over time.

Let X denote the critical angle of attack of a randomly selected general aviation aeroplane. A random sample of aeroplanes' critical angle of attack from n=28 aeroplanes is taken from the population of general aviation aeroplanes. The data is stored in the file stall.txt. Assuming each observation is independent and identically distributed N(,2), complete the exercises below.

stall.txt data is

17.566 18.25 17.306 18.742 16.554 17.749 19.369 16.037 16.833 18.677 16.847 18.419 17.627 18.181 17.353 16.626 16.566 18.978 16.579 18.369 15.916 17.148 18.524 16.592 17.172 15.907 17.22 18.582

Can u make code for R studio for calculate those question

Compute the value of the test statistic for this hypothesis test.

Compute the P-Value for this hypothesis test.

Compute the absolute value of the critical value for a two-sided 95% CI for .

Compute the lower and upper bounds for a two-sided 95% CI for .

Compute the absolute value of the critical value for a two-sided 88% CI for .

Compute the lower and upper bounds for a two-sided 88% CI for .