IHS ESDU Low-speed drag coefficient increment at zero lift due to full-span split flaps. 74010

Description
ESDU 74010 gives curves of drag increment at zero lift as a function of wing thickness/chord ratio and flap deflection for various flap chord/wing chord ratios between 0.1 and 0.4. The curves are based on a correlation of experimental data from 10 sources, and are accurate to within 10 per cent for rectangular wings and within 20 per cent for straight-tapered swept and unswept wings. To correct the data for application to part-span flaps, ESDU Aero F.02.01.07 is used.
  • Low-speed drag coefficient increment at zero lift due to full-span split flaps. - 74010 - IHS ESDU
    IHS ESDU
Description
ESDU 74010 gives curves of drag increment at zero lift as a function of wing thickness/chord ratio and flap deflection for various flap chord/wing chord ratios between 0.1 and 0.4. The curves are based on a correlation of experimental data from 10 sources, and are accurate to within 10 per cent for rectangular wings and within 20 per cent for straight-tapered swept and unswept wings. To correct the data for application to part-span flaps, ESDU Aero F.02.01.07 is used.

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Low-speed drag coefficient increment at zero lift due to full-span split flaps. - 74010 - IHS ESDU
IHS ESDU
London, United Kingdom
Low-speed drag coefficient increment at zero lift due to full-span split flaps.
74010
Low-speed drag coefficient increment at zero lift due to full-span split flaps. 74010
ESDU 74010 gives curves of drag increment at zero lift as a function of wing thickness/chord ratio and flap deflection for various flap chord/wing chord ratios between 0.1 and 0.4. The curves are based on a correlation of experimental data from 10 sources, and are accurate to within 10 per cent for rectangular wings and within 20 per cent for straight-tapered swept and unswept wings. To correct the data for application to part-span flaps, ESDU Aero F.02.01.07 is used.

ESDU 74010 gives curves of drag increment at zero lift as a function of wing thickness/chord ratio and flap deflection for various flap chord/wing chord ratios between 0.1 and 0.4. The curves are based on a correlation of experimental data from 10 sources, and are accurate to within 10 per cent for rectangular wings and within 20 per cent for straight-tapered swept and unswept wings. To correct the data for application to part-span flaps, ESDU Aero F.02.01.07 is used.

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Technical Specifications

  IHS ESDU
Product Category Standards and Technical Documents
Product Number 74010
Product Name Low-speed drag coefficient increment at zero lift due to full-span split flaps.
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