SplineCloud | AlinaNeh / Airfoil database C-list

AlinaNeh : Airfoil database C-list

About

The main aerodynamic characteristics of airfoils that starts with C letter and developed by different organizations.

Add a short description of your repository

aircraft airplane airfoils wings stabilizers

Files

API link

Use this link to access this curve in your code:

You can find out how to fetch and reuse repository data in your code here

Download

CAP 21 (TraCFoil) (cap21c-il)
- cap21c.dat
  empty
- xf-cap21c-il-100000.csv
  empty
- xf-cap21c-il-1000000.csv
  empty
- xf-cap21c-il-200000.csv
  empty
- xf-cap21c-il-50000.csv
  empty
- xf-cap21c-il-500000.csv
  empty
CAST 10-2_DOA 2 AIRFOIL (cast102-il)
- cast102.dat
  empty
- xf-cast102-il-100000.csv
  empty
- xf-cast102-il-1000000.csv
  empty
- xf-cast102-il-200000.csv
  empty
- xf-cast102-il-50000.csv
  empty
- xf-cast102-il-500000.csv
  empty
CH10 (smoothed) (ch10sm-il)
- ch10sm.dat
  empty
- xf-ch10sm-il-100000.csv
  empty
- xf-ch10sm-il-1000000.csv
  empty
- xf-ch10sm-il-200000.csv
  empty
- xf-ch10sm-il-50000.csv
  empty
- xf-ch10sm-il-500000.csv
  empty
CHEN AIRFOIL (chen-il)
- chen.dat
  empty
- xf-chen-il-100000.csv
  empty
- xf-chen-il-1000000.csv
  empty
- xf-chen-il-200000.csv
  empty
- xf-chen-il-50000.csv
  empty
- xf-chen-il-500000.csv
  empty
CLARK K AIRFOIL (clarkk-il)
- clarkk.dat
  empty
- xf-clarkk-il-100000.csv
  empty
- xf-clarkk-il-1000000.csv
  empty
- xf-clarkk-il-200000.csv
  empty
- xf-clarkk-il-50000.csv
  empty
- xf-clarkk-il-500000.csv
  empty
CLARK V AIRFOIL (clarkv-il)
- clarkv.dat
  empty
- xf-clarkv-il-100000.csv
  empty
- xf-clarkv-il-1000000.csv
  empty
- xf-clarkv-il-200000.csv
  empty
- xf-clarkv-il-50000.csv
  empty
- xf-clarkv-il-500000.csv
  empty
CLARK W AIRFOIL (clarkw-il)
- clarkw.dat
  empty
- xf-clarkw-il-100000.csv
  empty
- xf-clarkw-il-1000000.csv
  empty
- xf-clarkw-il-200000.csv
  empty
- xf-clarkw-il-50000.csv
  empty
- xf-clarkw-il-500000.csv
  empty
CLARK X AIRFOIL (clarkx-il)
- clarkx.dat
  empty
- xf-clarkx-il-100000.csv
  empty
- xf-clarkx-il-1000000.csv
  empty
- xf-clarkx-il-200000.csv
  empty
- xf-clarkx-il-50000.csv
  empty
- xf-clarkx-il-500000.csv
  empty
CLARK Y AIRFOIL (clarky-il)
- clarky.dat
  empty
- xf-clarky-il-100000.csv
  empty
- xf-clarky-il-1000000.csv
  empty
- xf-clarky-il-200000.csv
  empty
- xf-clarky-il-50000.csv
  empty
- xf-clarky-il-500000.csv
  empty
CLARK YH AIRFOIL (clarkyh-il)
- clarkyh.dat
  empty
- xf-clarkyh-il-100000.csv
  empty
- xf-clarkyh-il-1000000.csv
  empty
- xf-clarkyh-il-200000.csv
  empty
- xf-clarkyh-il-50000.csv
  empty
- xf-clarkyh-il-500000.csv
  empty
CLARK YM-15 AIRFOIL (clarym15-il)
- clarym15.dat
  empty
- xf-clarym15-il-100000.csv
  empty
- xf-clarym15-il-1000000.csv
  empty
- xf-clarym15-il-200000.csv
  empty
- xf-clarym15-il-50000.csv
  empty
- xf-clarym15-il-500000.csv
  empty
CLARK YM-18 AIRFOIL (clarym18-il)
- clarym18.dat
  empty
- xf-clarym18-il-100000.csv
  empty
- xf-clarym18-il-1000000.csv
  empty
- xf-clarym18-il-200000.csv
  empty
- xf-clarym18-il-50000.csv
  empty
- xf-clarym18-il-500000.csv
  empty
CLARK YS AIRFOIL (clarkys-il)
- clarkys.dat
  empty
- xf-clarkys-il-100000.csv
  empty
- xf-clarkys-il-1000000.csv
  empty
- xf-clarkys-il-200000.csv
  empty
- xf-clarkys-il-50000.csv
  empty
- xf-clarkys-il-500000.csv
  empty
CLARK Z AIRFOIL (clarkz-il)
- clarkz.dat
  empty
- xf-clarkz-il-100000.csv
  empty
- xf-clarkz-il-1000000.csv
  empty
- xf-clarkz-il-200000.csv
  empty
- xf-clarkz-il-50000.csv
  empty
- xf-clarkz-il-500000.csv
  empty
CLARK-Y 11.7% smoothed (clarkysm-il)
- clarkysm.dat
  empty
- xf-clarkysm-il-100000.csv
  empty
- xf-clarkysm-il-1000000.csv
  empty
- xf-clarkysm-il-200000.csv
  empty
- xf-clarkysm-il-50000.csv
  empty
- xf-clarkysm-il-500000.csv
  empty
CURTISS CR-1 AIRFOIL (cr1-il)
- cr1.dat
  empty
- xf-cr1-il-100000.csv
  empty
- xf-cr1-il-1000000.csv
  empty
- xf-cr1-il-200000.csv
  empty
- xf-cr1-il-50000.csv
  empty
- xf-cr1-il-500000.csv
  empty
Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn)
- cp-100-050-gn.dat
  empty
- xf-cp-100-050-gn-100000.csv
  empty
- xf-cp-100-050-gn-1000000.csv
  empty
- xf-cp-100-050-gn-200000.csv
  empty
- xf-cp-100-050-gn-50000.csv
  empty
- xf-cp-100-050-gn-500000.csv
  empty
Cambered plate C=12% T=5% R=1.1 (cp-120-050-gn)
- cp-120-050-gn.dat
  empty
- xf-cp-120-050-gn-100000.csv
  empty
- xf-cp-120-050-gn-1000000.csv
  empty
- xf-cp-120-050-gn-200000.csv
  empty
- xf-cp-120-050-gn-50000.csv
  empty
- xf-cp-120-050-gn-500000.csv
  empty
Cambered plate C=14% T=5% R=0.96 (cp-140-050-gn)
- cp-140-050-gn.dat
  empty
- xf-cp-140-050-gn-100000.csv
  empty
- xf-cp-140-050-gn-1000000.csv
  empty
- xf-cp-140-050-gn-200000.csv
  empty
- xf-cp-140-050-gn-50000.csv
  empty
- xf-cp-140-050-gn-500000.csv
  empty
Cambered plate C=16% T=5% R=0.86 (cp-160-050-gn)
- cp-160-050-gn.dat
  empty
- xf-cp-160-050-gn-100000.csv
  empty
- xf-cp-160-050-gn-1000000.csv
  empty
- xf-cp-160-050-gn-200000.csv
  empty
- xf-cp-160-050-gn-50000.csv
  empty
- xf-cp-160-050-gn-500000.csv
  empty
Cambered plate C=18% T=5% R=0.78 (cp-180-050-gn)
- cp-180-050-gn.dat
  empty
- xf-cp-180-050-gn-100000.csv
  empty
- xf-cp-180-050-gn-1000000.csv
  empty
- xf-cp-180-050-gn-200000.csv
  empty
- xf-cp-180-050-gn-50000.csv
  empty
- xf-cp-180-050-gn-500000.csv
  empty
Cambered plate C=6% T=5% R=2.11 (cp-060-050-gn)
- cp-060-050-gn.dat
  empty
- xf-cp-060-050-gn-100000.csv
  empty
- xf-cp-060-050-gn-1000000.csv
  empty
- xf-cp-060-050-gn-200000.csv
  empty
- xf-cp-060-050-gn-50000.csv
  empty
- xf-cp-060-050-gn-500000.csv
  empty
Cambered plate C=8% T=5% R=1.6 (cp-080-050-gn)
- cp-080-050-gn.dat
  empty
- xf-cp-080-050-gn-100000.csv
  empty
- xf-cp-080-050-gn-1000000.csv
  empty
- xf-cp-080-050-gn-200000.csv
  empty
- xf-cp-080-050-gn-50000.csv
  empty
- xf-cp-080-050-gn-500000.csv
  empty
Coanda 1 (coanda1-il)
- coanda1.dat
  empty
- xf-coanda1-il-100000.csv
  empty
- xf-coanda1-il-1000000.csv
  empty
- xf-coanda1-il-200000.csv
  empty
- xf-coanda1-il-50000.csv
  empty
- xf-coanda1-il-500000.csv
  empty
Coanda 2 (coanda2-il)
- coanda2.dat
  empty
- xf-coanda2-il-100000.csv
  empty
- xf-coanda2-il-1000000.csv
  empty
- xf-coanda2-il-200000.csv
  empty
- xf-coanda2-il-50000.csv
  empty
- xf-coanda2-il-500000.csv
  empty
Coanda 3 (coanda3-il)
- coanda3.dat
  empty
- xf-coanda3-il-100000.csv
  empty
- xf-coanda3-il-1000000.csv
  empty
- xf-coanda3-il-200000.csv
  empty
- xf-coanda3-il-50000.csv
  empty
- xf-coanda3-il-500000.csv
  empty
Curtis C-72 (curtisc72-il)
- curtisc72.dat
  empty
- xf-curtisc72-il-100000.csv
  empty
- xf-curtisc72-il-1000000.csv
  empty
- xf-curtisc72-il-200000.csv
  empty
- xf-curtisc72-il-50000.csv
  empty
- xf-curtisc72-il-500000.csv
  empty
LOCKHEED C-141 BL0 AIRFOIL (c141a-il)
- c141a.dat
  empty
- xf-c141a-il-100000.csv
  empty
- xf-c141a-il-1000000.csv
  empty
- xf-c141a-il-200000.csv
  empty
- xf-c141a-il-50000.csv
  empty
- xf-c141a-il-500000.csv
  empty
LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il)
- c141b.dat
  empty
- xf-c141b-il-100000.csv
  empty
- xf-c141b-il-1000000.csv
  empty
- xf-c141b-il-200000.csv
  empty
- xf-c141b-il-50000.csv
  empty
- xf-c141b-il-500000.csv
  empty
LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il)
- c141c.dat
  empty
- xf-c141c-il-100000.csv
  empty
- xf-c141c-il-1000000.csv
  empty
- xf-c141c-il-200000.csv
  empty
- xf-c141c-il-50000.csv
  empty
- xf-c141c-il-500000.csv
  empty
LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il)
- c141d.dat
  empty
- xf-c141d-il-100000.csv
  empty
- xf-c141d-il-1000000.csv
  empty
- xf-c141d-il-200000.csv
  empty
- xf-c141d-il-50000.csv
  empty
- xf-c141d-il-500000.csv
  empty
LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il)
- c141e.dat
  empty
- xf-c141e-il-100000.csv
  empty
- xf-c141e-il-1000000.csv
  empty
- xf-c141e-il-200000.csv
  empty
- xf-c141e-il-50000.csv
  empty
- xf-c141e-il-500000.csv
  empty
LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il)
- c141f.dat
  empty
- xf-c141f-il-100000.csv
  empty
- xf-c141f-il-1000000.csv
  empty
- xf-c141f-il-200000.csv
  empty
- xf-c141f-il-50000.csv
  empty
- xf-c141f-il-500000.csv
  empty
LOCKHEED C-5A BL0 AIRFOIL (c5a-il)
- c5a.dat
  empty
- xf-c5a-il-100000.csv
  empty
- xf-c5a-il-1000000.csv
  empty
- xf-c5a-il-200000.csv
  empty
- xf-c5a-il-50000.csv
  empty
- xf-c5a-il-500000.csv
  empty
LOCKHEED C-5A BL1256 AIRFOIL (c5e-il)
- c5e.dat
  empty
- xf-c5e-il-100000.csv
  empty
- xf-c5e-il-1000000.csv
  empty
- xf-c5e-il-200000.csv
  empty
- xf-c5e-il-50000.csv
  empty
- xf-c5e-il-500000.csv
  empty
LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il)
- c5b.dat
  empty
- xf-c5b-il-100000.csv
  empty
- xf-c5b-il-1000000.csv
  empty
- xf-c5b-il-200000.csv
  empty
- xf-c5b-il-50000.csv
  empty
- xf-c5b-il-500000.csv
  empty
LOCKHEED C-5A BL576 AIRFOIL (c5c-il)
- c5c.dat
  empty
- xf-c5c-il-100000.csv
  empty
- xf-c5c-il-1000000.csv
  empty
- xf-c5c-il-200000.csv
  empty
- xf-c5c-il-50000.csv
  empty
- xf-c5c-il-500000.csv
  empty
LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il)
- c5d.dat
  empty
- xf-c5d-il-100000.csv
  empty
- xf-c5d-il-1000000.csv
  empty
- xf-c5d-il-200000.csv
  empty
- xf-c5d-il-50000.csv
  empty
- xf-c5d-il-500000.csv
  empty
WACO COOTIE AIRFOIL (cootie-il)
- cootie.dat
  empty
- xf-cootie-il-100000.csv
  empty
- xf-cootie-il-1000000.csv
  empty
- xf-cootie-il-200000.csv
  empty
- xf-cootie-il-50000.csv
  empty
- xf-cootie-il-500000.csv
  empty
cr001sm (cr001sm-il)
- cr001sm.dat
  empty
- xf-cr001sm-il-100000.csv
  empty
- xf-cr001sm-il-1000000.csv
  empty
- xf-cr001sm-il-200000.csv
  empty
- xf-cr001sm-il-50000.csv
  empty
- xf-cr001sm-il-500000.csv
  empty
empty

Wiki

This repository contains basic data on the airfoils, which are developed by different organizations and whose names start with C. The data contains profile coordinates and performance data, including lift coefficients, drag coefficients, and pitching moment coefficients for various Reynolds numbers. For each coefficient distribution by the attack angle, corresponding relations are constructed and can be used in design calculations via SplineCloud API.

Additional Options Used

The Reynolds number is a dimensionless value that measures the ratio of inertial forces to viscous forces and descibes the degree of laminar or turbulent flow. Systems that operate at the same Reynolds number will have the same flow characteristics even if the fluid, speed and characteristic lengths vary.

Reynolds number range from 50,000 to 1,000,000 in approximatly logarithmic steps.

Ncrit value is used to model of the turbulence of the fluid or roughness of the airfoil.

Current repository contains data for average wind tunnel with Ncrit=9

Mach number has been left at the default value of zero.

References

http://airfoiltools.com/