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Solve the following problem using Python, implementing the functions described below, one line at a time
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Description:
 def prof_altitude(pressure, p_coef=(-0.028389, -0.0493698, 0.485718, 0.278656, -17.5703, 48.0926)):
 """ Return altitude for given pressure. This function evaluates a polynomial at log10(pressure) values. Parameters pressure : array-like pressure values [hPa]. p_coef : array-like coefficients of the polynomial (default values are for the US Standard Atmosphere). Returns ------- altitude : array-like altitude values [km] (same shape than the pressure input array). See Also -------- prof_pressure : Returns pressure for given altitude. prof_temperature : Returns air temperature for given altitude. Notes ----- Default coefficient values represent a 5th degree polynomial which had been fitted to USSA data from 0-100 km. Accuracy is on the order of 1% for 0-100 km and 0.5% below 30 km. This function, with default values, may thus produce bad results with pressure less than about 3e-4 hPa. Examples -------- array([ 0.1065092 , 1.95627858, 4.2060627 ]) """

    pressure = np.asarray(pressure)
    altitude = np.polyval(p_coef, np.log10(pressure.flatten()))
    return altitude.reshape(pressure.shape)