Field elevation: 5,673 feet MSL
Wind: 280 @ 5 miles
Temperature: 5 degrees Celsius
Dewpoint: -3 degrees Celsius
Humidity: 56%
Altimeter: 30.39 (airport 29.92)
1) Find the pressure altitude
2) Find the pressure ratio
3) Find the temperature ratio
4) Find the density ratio
5) Find the density altitude
6) Find the Calibrated Lift-Off Speed [KCAS] using the chart below, which is a typical example of an aircraft position error correction chart. (Consider that the gear would obviously still be in the down position at lift-off).
7) Find the Equivalent Lift-Off Speed [KEAS] using your Calibrated Airspeed from #1 above and the Pressure Altitude for your selected airfield (from A). (Compressibility Correction Chart see Flight Theory and Aerodynamics, Fig 2.10). Comment on your findings. Why was/wasnt the Compressibility Effect in your case negligible?
8) Find the True Lift-Off Speed [KTAS] (use the Density Ratio in question #7 of the Airspeed Exercise Part 1 document).
9) Calculate the Dynamic Pressure q [lb/ft2], based on the TAS above. (Dynamic Pressure definition and formula can be reviewed in Flight Theory and Aerodynamics page 22 (EQ 2.1); make sure to use a formula consistent with a Lift-Off Speed in kts
***Please answer 1 through 5***
20 ATMOSPHERE AND AIRSPEED MEASUREMENT Table 2.1. Standard Atmosphere Table Altitude (ft) Density Ratio, a Pressure Ratio, 8 Temper aturo (F) Temper. ature Ratio, e Speed of Sound (knots) Kinematic Viscosity, (f/sec) O 1.000 2.000 3.000 4,000 5.000 6,000 7.000 8,000 9,000 10,000 15.000 20,000 25.000 30,000 35.000 36,089 40.000 45.000 50.000 1.0000 0.9711 0.9428 0.9151 0.8881 0.8617 0.8359 0.8106 0.7860 0.7620 0.7385 0.6292 0.5328 0.4481 0.3741 0.3099 0.2971 0.2462 0.1936 0.1522 1.0000 0.9854 0.9710 0.9566 0.9424 0.9283 0.9143 0.9004 0.8866 0.8729 0.8593 0.7932 0.7299 0.6694 0.6117 0.5567 0.5450 0.4962 0.4400 0.3002 1.0000 0.9644 0.9298 0.8962 0.8637 0.8320 0.8014 0.7716 0.7428 0.7148 0.6877 0.5643 0.4595 0.3711 0.2970 0.2353 0.2234 0.1851 0.1455 0.1145 59.00 55.43 51.87 48.30 44.74 41.17 37.60 34,04 30.47 26.90 23.34 5.51 12.32 -30.15 47.98 65.82 69.70 -69.70 -69.70 -69.70 1.0000 0.9931 0.9862 0.9794 0.9725 0.9656 0.9587 0.9519 0.9450 0.9381 0.9312 0.8969 0.8625 0.8281 0.7937 0.7594 0.7519 0.7519 0.7519 0.7519 661.7 659.5 657.2 654.9 652.6 650.3 647.9 645.6 643.3 6-10.9 638.6 626.7 614.6 602.2 589.5 576.6 573.8 573.8 573.8 573.8 .000158 .000161 .000165 .000169 .000174 ,000178 .000182 .000187 .000192 .000197 .000202 .000229 000262 .000302 .000349 .000-105 .000419 .000506 .000643 .000818 "The tropopause. TYPICAL POSITION ERROR CORRECTION LANDING CONFIGURATION +5 AIRSPEED POSITION ERROR CORRECTION AVi, KNOTS CLEAN CONFIGURATION CAS = IAS + Avi -10 BMT 100 200 300 400 500 INDICATED AIRSPEED, KNOTS 20 ATMOSPHERE AND AIRSPEED MEASUREMENT Table 2.1. Standard Atmosphere Table Altitude (ft) Density Ratio, a Pressure Ratio, 8 Temper aturo (F) Temper. ature Ratio, e Speed of Sound (knots) Kinematic Viscosity, (f/sec) O 1.000 2.000 3.000 4,000 5.000 6,000 7.000 8,000 9,000 10,000 15.000 20,000 25.000 30,000 35.000 36,089 40.000 45.000 50.000 1.0000 0.9711 0.9428 0.9151 0.8881 0.8617 0.8359 0.8106 0.7860 0.7620 0.7385 0.6292 0.5328 0.4481 0.3741 0.3099 0.2971 0.2462 0.1936 0.1522 1.0000 0.9854 0.9710 0.9566 0.9424 0.9283 0.9143 0.9004 0.8866 0.8729 0.8593 0.7932 0.7299 0.6694 0.6117 0.5567 0.5450 0.4962 0.4400 0.3002 1.0000 0.9644 0.9298 0.8962 0.8637 0.8320 0.8014 0.7716 0.7428 0.7148 0.6877 0.5643 0.4595 0.3711 0.2970 0.2353 0.2234 0.1851 0.1455 0.1145 59.00 55.43 51.87 48.30 44.74 41.17 37.60 34,04 30.47 26.90 23.34 5.51 12.32 -30.15 47.98 65.82 69.70 -69.70 -69.70 -69.70 1.0000 0.9931 0.9862 0.9794 0.9725 0.9656 0.9587 0.9519 0.9450 0.9381 0.9312 0.8969 0.8625 0.8281 0.7937 0.7594 0.7519 0.7519 0.7519 0.7519 661.7 659.5 657.2 654.9 652.6 650.3 647.9 645.6 643.3 6-10.9 638.6 626.7 614.6 602.2 589.5 576.6 573.8 573.8 573.8 573.8 .000158 .000161 .000165 .000169 .000174 ,000178 .000182 .000187 .000192 .000197 .000202 .000229 000262 .000302 .000349 .000-105 .000419 .000506 .000643 .000818 "The tropopause. TYPICAL POSITION ERROR CORRECTION LANDING CONFIGURATION +5 AIRSPEED POSITION ERROR CORRECTION AVi, KNOTS CLEAN CONFIGURATION CAS = IAS + Avi -10 BMT 100 200 300 400 500 INDICATED AIRSPEED, KNOTS
