An airplane is flying at 6 km. Two gauges on the plane read G1 49.3 kPa,abs and G2 = 43.5 kPa,abs. G1 Istagnation pressure and G2 is on the wing. Determine the following: a) The velocity of the airplane. b) The Mach number of the airplane. c) Dynamic pressure of the test condition. d) The velocity at the edge of the boundary layer for G2. TABLE 1.2A U.S. Standard Atmosphere, 1976 SI Units Geometric Altitude (km) Pressure (N/m) Temperature Density (kg/m Viscosity (kg/m-s) 1.0133E+05 288.150 1.2250 E+00 1.7894 E-05 1 8.9875E-04 281.651 1.1117E+00 1.7579 E-05 7.9501 E 04 275.154 1.0066E+00 1.7260 F-05 7,0121E+04 268.659 9.0926E-01 1.6938 E-05 6.1669E-04 262.166 8.1934 E-01 1.6612E-05 5.4048 E 04 255.676 7.3643E-01 1.7885E-05 6.251 4.7217 E + 04 209.187 6.6012-01 1.5949-05 127 4.1105-04 242.700 5.9002 E-01 1.5612 E-05 3.5651 +04 236.215 5.2578-01 1.5271 E-05 9 3.0800E+04 229.733 4.6707 E-01 1.4926 E-05 10 2.6500E+04 223.252 4.1351 E-01 1.4577 E-05