test_cold_gas_thruster.TestNozzleContour Class Reference

Public Member Functions
	test_contour_shape (self)
	test_contour_starts_converging (self)
	test_contour_ends_at_exit_radius (self)
	test_contour_includes_chamber (self)

Detailed Description

Definition at line 119 of file test_cold_gas_thruster.py.

Member Function Documentation

test_contour_ends_at_exit_radius()

test_cold_gas_thruster.TestNozzleContour.test_contour_ends_at_exit_radius

(

self

)

Last contour point should be near the exit radius.

Definition at line 139 of file test_cold_gas_thruster.py.

References test_cold_gas_thruster._make_config().

test_contour_includes_chamber()

test_cold_gas_thruster.TestNozzleContour.test_contour_includes_chamber

(

self

)

First segment should be at the chamber radius and length.

Definition at line 147 of file test_cold_gas_thruster.py.

References test_cold_gas_thruster._make_config().

test_contour_shape()

test_cold_gas_thruster.TestNozzleContour.test_contour_shape

(

self

)

Definition at line 121 of file test_cold_gas_thruster.py.

References test_cold_gas_thruster._make_config().

test_contour_starts_converging()

test_cold_gas_thruster.TestNozzleContour.test_contour_starts_converging

(

self

)

Nozzle throat should have smaller radius than the chamber.

Definition at line 128 of file test_cold_gas_thruster.py.

References test_cold_gas_thruster._make_config().

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The documentation for this class was generated from the following file:

• EngineDesign/tests/test_cold_gas_thruster.py