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Airfoil database list (P).

P-51D ROOT (BL17.5) AIRFOIL to PW98-mod

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(p51droot-il) P-51D ROOT (BL17.5) AIRFOIL

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P-51D ROOT (BL17.5) AIRFOILP-51D root (BL17.5) airfoil
Max thickness 16.5% at 38.9% chord
Max camber 1.3% at 68.3% chord
Source UIUC Airfoil Coordinates Database

(p51dtip-il) P-51D TIP (BL215) AIRFOIL

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P-51D TIP (BL215) AIRFOILP-51D tip (BL215) airfoil
Max thickness 11.4% at 46.3% chord
Max camber 1.3% at 46.3% chord
Source UIUC Airfoil Coordinates Database

(p51hroot-il) NACA 66

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NACA 66NACA 66
Max thickness 15.5% at 45% chord
Max camber 1.3% at 47.5% chord
Source UIUC Airfoil Coordinates Database

(p51htip-il) NACA 66

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NACA 66NACA 66
Max thickness 12% at 45% chord
Max camber 1.3% at 47.5% chord
Source UIUC Airfoil Coordinates Database

(pfcm-il) PROPFAN CRUISE MISSILE WING AIRFOIL

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PROPFAN CRUISE MISSILE WING AIRFOILPropfan Cruise Missile wing airfoil
Max thickness 8.2% at 40% chord
Max camber 1.3% at 50% chord
Source UIUC Airfoil Coordinates Database

(pmc19sm-il) PMC19 Smoothed

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PMC19 SmoothedPMC19
Max thickness 9.2% at 34.2% chord
Max camber 2.1% at 17.5% chord
Source UIUC Airfoil Coordinates Database

(prandtl-d-root-ns) Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag

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Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower DragNASA Preliminary Research Aerodynamic Design To Lower Drag (PRANDTL-D) glider root airfoil
Max thickness 12% at 30.9% chord
Max camber 3.5% at 37.1% chord
Source NASA

(prandtl-d-tip-ns) Prandtl-D tip - NASA Preliminary Research Aerodynamic Design To Lower Drag

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Prandtl-D tip - NASA Preliminary Research Aerodynamic Design To Lower DragNASA Preliminary Research Aerodynamic Design To Lower Drag (PRANDTL-D) glider tip airfoil
Max thickness 9.6% at 26.8% chord
Max camber 0% at 0% chord
Source NASA

(psu-90-125wl-il) PSU-90-125WL

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PSU-90-125WLPSU-90-125WL sailplane winglet airfoil
Max thickness 12.5% at 35.1% chord
Max camber 2% at 54.4% chord
Source UIUC Airfoil Coordinates Database

(psu94097-il) PSU 94-097 (AIAA 2001-2478)

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PSU 94-097 (AIAA 2001-2478)Maughmer PSU 94-097 winglet airfoil
Max thickness 9.7% at 32.3% chord
Max camber 4% at 46.3% chord
Source UIUC Airfoil Coordinates Database

(pt40-il) PT40

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PT40Great Plane PT-40 trainer airfoil
Max thickness 11.6% at 27.1% chord
Max camber 2.9% at 41.6% chord
Source UIUC Airfoil Coordinates Database

(pw106-pw) PW106

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PW106Peter Wick. Modified PW51 with higher camber and therefore a higher clmax
Max thickness 8.9% at 27.5% chord
Max camber 2.1% at 27.5% chord
Source RC Groups

(pw1211-pw) PW1211

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PW1211Peter Wick. Airfoil for plank model gliders
Max thickness 7% at 24% chord
Max camber 1.7% at 28.2% chord
Source RC Groups

(pw51-pw) PW51

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PW51Peter Wick. Airfoil for plank model gliders
Max thickness 8.9% at 27.5% chord
Max camber 1.4% at 27.5% chord
Source RC Groups

(pw75-pw) PW75

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PW75Peter Wick. Modified PW51 with some more reflex
Max thickness 8.9% at 27.5% chord
Max camber 1.5% at 23.4% chord
Source RC Groups

(pw98mod-pw) PW98-mod

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PW98-modPeter Wick. Modified PW51 with higher camber and therefore a higher clmax
Max thickness 8.4% at 27.5% chord
Max camber 1.8% at 27.5% chord
Source RC Groups
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