Polar data can be downloaded here (.xml): CSR 01 Polar
(the polar data format is based on: http://http://www.mh-aerotools.de/airfoils/xml_polar_format.htm)
The LIFTING_LINE output data file can be downloaded here (.xml): CalculatePolar LL
It includes full aircraft drag polars for different configurations and Mach numbers.
| Parameter | Symbol | Unit | Value |
|---|---|---|---|
| Design cruise conditions | |||
| Mach number | MaCr | - | 0.78 |
| Flight altitude | HCr | ft | 35000 |
| Reynolds number | ReCr | - | 25.6 ⋅ 106 |
| Aerodynamic coefficients (trimmed* @ design cruise point and optimum L/D) |
|||
| Optimum lift-to-drag ratio | L/Dopt | - | 17.43 |
| Lift coefficient | CL,opt | - | 0.54 |
| + wing | CL,wing | - | 0.55 |
| + stabilizer | CL,stab | - | -0.01 |
| Total drag coefficient | CD,total | - | 0.03092 |
| Induced drag coefficent | CD,ind | - | 0.01106 (=35.8%) |
| Viscous drag coefficent | CD,visc | - | 0.01884 (=60.9%) |
| Wave drag coefficent | CD,wave | - | 0.00102 (=3.3%) |
| Pitching moment coefficent | CM | - | 0.00041 |
| CM reference point | % MAC | 28.6 | |
| Maximum lift coefficients | |||
| Max. lift coeff. take-off | CL,max,t/o | - | 2.2 |
| Max. lift coeff. landing | CL,max,ldg | - | 2.8 |
* Polars are trimmed at cruise conditions using all-movable stabilizer (trim incidence angle istab,trim = -0.1°) such that CM=0 at CL,cruise.
(No additional trim deflections are used. The pitch up influence of engine thrust on CM is neglected.)