Similarly shaped airfoils to HQ 1.0/10
New! Bulk download of polars in Excel format: hq1010.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (0) | Similarly shaped airfoils
Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Basic Data: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl | Curve fits | Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Roughness Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Plain Flap Effects: cl,max vs flap deflection: all flap chords | 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cl vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cm vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cd vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
2. NACA64-210
3. NACA63-210 a=0.8
4. NACA1410
5. Ritz 1-30-10
6. NACA64-210 a=0.8
7. NACA63A210
8. NACA63-210 a=0.6
9. NACA63-210 a=0.0
10. NACA63-210 a=0.2
11. NACA63-210 a=0.5
12. NACA64-210 a=0.0
13. NACA64-210 a=0.6
14. NACA64-210 a=0.2
15. NACA64-210 a=0.5
16. NACA64A210
17. NACA63-211
18. TP28-4
19. NACA65-210
20. HM10011
21. NACA64-211