Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

Airfoil database list (S).

SOKOLOV AIRFOIL to Supermarine 371-II (tip)

Page 9 of 9     1 2 3 4 5 6 7 8 9     Next

(sokolov-il) SOKOLOV AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
SOKOLOV AIRFOILSokolov R/C sailplane airfoil
Max thickness 7.1% at 25% chord
Max camber 6.3% at 50% chord
Source UIUC Airfoil Coordinates Database

(spicasm-il) SPICA 11.73% smoothed

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
SPICA  11.73% smoothedAnderson SPICA R/C sailplane airfoil (smoothed)
Max thickness 11.7% at 30% chord
Max camber 4.7% at 35% chord
Source UIUC Airfoil Coordinates Database

(ssca07-il) SIKORSKY SSC-A07 AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
SIKORSKY SSC-A07 AIRFOILSikorsky/Flemming SSC-A07 transonic rotorcraft airfoil
Max thickness 7% at 37.7% chord
Max camber 0.9% at 17.2% chord
Source UIUC Airfoil Coordinates Database

(ssca09-il) SIKORSKY SSC-A09 AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
SIKORSKY SSC-A09  AIRFOILSikorsky/Flemming SSC-A09 transonic rotorcraft airfoil
Max thickness 9% at 37.7% chord
Max camber 1.2% at 17.2% chord
Source UIUC Airfoil Coordinates Database

(stcyr171-il) St. CYR 171 (Royer)

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
St. CYR 171 (Royer)St. CYR 171 (Royer) airfoil
Max thickness 11.1% at 30% chord
Max camber 1.5% at 50% chord
Source UIUC Airfoil Coordinates Database

(stcyr172-il) St. CYR 172 (Royer)

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
St. CYR 172 (Royer)St. CYR 172 (Royer) airfoil
Max thickness 13.6% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(stcyr234-il) St. CYR 234 (Bartel 17-IC)

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
St. CYR 234 (Bartel 17-IC)St. CYR 234 (Bartel 17-IC) airfoil
Max thickness 16% at 20% chord
Max camber 5.1% at 50% chord
Source UIUC Airfoil Coordinates Database

(stcyr24-il) St. CYR 24 (Bartel 35-IIIC)

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
St. CYR 24 (Bartel 35-IIIC)St. CYR 24 (Bartel 35-IIIC) airfoil
Max thickness 12.4% at 30% chord
Max camber 5.9% at 40% chord
Source UIUC Airfoil Coordinates Database

(ste87151-il) EPPLER STE 871-514 AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
EPPLER STE 871-514 AIRFOILEppler STE 871-514 airfoil
Max thickness 13.9% at 47.3% chord
Max camber 2.5% at 79% chord
Source UIUC Airfoil Coordinates Database

(ste87391-il) EPPLER STE 87(-3)-914 AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
EPPLER STE 87(-3)-914 AIRFOILEppler STE 87(-3)-914 airfoil
Max thickness 14.6% at 34.1% chord
Max camber 4.2% at 58.3% chord
Source UIUC Airfoil Coordinates Database

(stf86361-il) EPPLER STF 863-615 AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
EPPLER STF 863-615 AIRFOILEppler STF 863-615 airfoil
Max thickness 14.7% at 44.7% chord
Max camber 4.2% at 72.3% chord
Source UIUC Airfoil Coordinates Database

(strand-il) STRAND AIRFOIL

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
STRAND AIRFOILStrand high lift airfoil
Max thickness 15.4% at 26.1% chord
Max camber 4.1% at 32.1% chord
Source UIUC Airfoil Coordinates Database

(supermarine371i-il) Supermarine 371-I (root)

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
Supermarine 371-I (root)Supermarine 371-I root airfoil
Max thickness 13% at 40% chord
Max camber 0.9% at 50% chord
Source UIUC Airfoil Coordinates Database

(supermarine371ii-il) Supermarine 371-II (tip)

Airfoil details
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file
Source dat file
Supermarine 371-II (tip)Supermarine 371-II tip airfoil
Max thickness 8.4% at 50% chord
Max camber 0.9% at 45% chord
Source UIUC Airfoil Coordinates Database
Page 9 of 9     1 2 3 4 5 6 7 8 9     Next

Please see the source web site or designer for any license conditions.