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Aircraft Operations. Volume II - Construction of Visual and Instrument ...

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Appendix to Chapter 1<br />

CONVERSION TABLE FOR IAS TO TAS CALCULATIONS<br />

1. This appendix provides conversion factors for the conversion <strong>of</strong> indicated airspeed to true airspeed for altitudes<br />

from0to7500m(0to24000ft)<strong>and</strong>attemperaturesfromISA–30°CtoISA+30°C.<br />

2. To find true airspeed, simply multiply the indicated airspeed by the conversion factor at the given altitude <strong>and</strong><br />

temperature. For example:<br />

a) assume an altitude <strong>of</strong> 4 500 m, an indicated airspeed <strong>of</strong> 400 km/h <strong>and</strong> a temperature <strong>of</strong> ISA + 20°C. Then<br />

TAS = 400 × 1.3034 = 521 km/h.<br />

b) assume an altitude <strong>of</strong> 10 000 ft, an indicated airspeed <strong>of</strong> 220 kt <strong>and</strong> a temperature <strong>of</strong> ISA + 10°C. Then<br />

TAS = 220 × 1.1852 = 261 kt.<br />

3. For altitudes <strong>and</strong> temperatures not listed in Tables I-2-1-App-1 <strong>and</strong> Tables I-2-1-App-2, the formula presented<br />

beneath each table can be used to determine true airspeed.<br />

4. Because compressibility was not considered in these tables, the speeds to which the conversion factors may be<br />

applied should be limited to those listed in Tables I-4-1-1 <strong>and</strong> I-4-1-2.<br />

I-2-1-App-1 23/11/06

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