Desired capability or behavior.

Aviary computes turbofan engine diameter using Aircraft.Engine.REFERENCE_DIAMETER in GASP based geometry subsystem. GASP never had a variable for reference diameter but was implicitly reflected by WASLS input.

The old GASP algorithm handles the following pre-stored engines:

• GENERAL ELECTRIC CJ610-1
• GARRETT TFE731-2
• UACL JT15D-1
• AVCO/LYC. ALF-502
• GENERAL ELECTRIC CF-34
• GENERAL ELECTRIC TF-34
• GENERAL ELECTRIC T700/F1
• PRATT WHITNEY JT8D-7
• LEWIS MOD FOR G.E. E3
• PRATT WHITNEY J75
• Y97-100 Turbojet

and users can provide their engines too.

Suppose we have Mach array, %corrected engine speed array, corrected thrust array, and fuel flow array. We can compute the specific thrust (SFN) of the engine at sea level. Define WASLS = Thrust/SFN. Then, nacelle diameter, length, and surface area are computed as a function of WASLS, the fan-face Mach (SM1D) and the hub-to-tip ratio (HBTP).

Now, GASP has a different algorithm that is much simpler. The BWB implementation has adopted it. Aviary may modify its algorithm to be consistent with GASP and variable Aircraft.Engine.REFERENCE_DIAMETER should be removed.

Is your feature request related to a problem? Please describe.

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Associated Bug Report

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