Airspeed data for performance calculations.
Abstract:ESDU 69026 presents means of obtaining airspeed and kinetic pressure information which are needed for performance estimation or reduction purposes. These data apply to pressure heights from -2000 to 105 000 ft. The Mach number range is from 0 to 3.0 and the ranges of equivalent and calibrated airspeeds extend up to l000 kn. The data are presented in two alternative and independent forms. The first form is graphical while the second is semigraphical and requires the user to make a number of simple calculations. The first form is the faster to use but the true airspeed data are restricted to the standard atmosphere. The second form is more general and permits more accurate results to be obtained.
- Aircraft Performance Analysis
- Calibrated Airspeed
- Equivalent Airspeed
- Impact Pressure
- Kinetic Pressure
- Mach Number
- One-Dimensional Flow
- Pitot Pressure
- Shock Waves
- Stagnation Conditions
- Static Pressure
- Total Pressure
- Total Temperature
|Data Item ESDU 69026|
|Toolbox ISA Run||
The graphs listed below are available only to subscribers.
|Figure 1a - Part 1|
|Figure 1a - Part 2|
|Figure 2a||Relationship between pressure height, mach number and calibrated airspeed|
|Figure 2b||Relationship between pressure height, mach number and calibrated airspeed|
|Figure 3a||Scale-altitude correction|
|Figure 3b||Scale-altitude correction|