8.625x3.75 (8625x375.dat) v2025-1001 Simulation Date: 02/24/2026 ----- AIRFOIL SUMMARY DATA ----- DEFINITIONS: THE QUOTED PITCH REFLECTS, IN GENERAL, ANGULAR MEASURE AS DEFINED WITH A FLAT BOTTOM SURFACE. THIS WILL AGREE WITH A PRATHER GAGE MEASUREMENT OVER MOST OF THE EFFECTIVE PORTION OF THE BLADE. (NOTE: QUOTED=INPUT) THE LE-TE MEASURE IS DEFINED IN TERMS OF LEADING EDGE AND TRAILING EDGE (MOLD) PARTING LINE DATUMS. THE PRATHER MEASURE REFLECTS THE MOST LIKELY PITCH INTERPRETATION FROM A PITCH MEASUREMENT DEVICE THAT RESTS AGAINST THE LOWER SURFACE. SWEEP & RAKE ARE DEFINED WITH (MOLD) LE PARTING LINE. ZHIGH IS HIGHEST ELEVATION ON TOP SURFACE. TWIST IS DEFINED WITH (MOLD) LE AND TE PARTING LINE DATUMS. CHORD IS THE LENGTH BETWEEN (MOLD) LE AND TE PARTING LINES. CGY IS MASS OFFSET, FORE-AFT. CGZ IS MASS OFFSET, ELEVATION. STATION CHORD PITCH PITCH PITCH SWEEP(Y) RAKE(Z) THICKNESS TWIST MAX-THICK CROSS-SECTION ZHIGH CGY CGZ (IN) (IN) (QUOTED) (LE-TE) (PRATHER) (IN) (IN) RATIO (DEG) (IN) (IN**2) (IN) (IN) (IN) 0.0000 0.9000 2.1306 -0.5000 -0.5000 0.4500 0.0000 0.2212 0.0000 0.1990 0.0000 0.1500 0.0000 0.0000 0.1200 0.8610 2.2734 -0.4914 -0.9675 0.4450 0.0032 0.2237 -33.0949 0.1926 0.3082 0.1503 0.0122 -0.0580 0.2400 0.8180 2.4095 -0.4334 -1.4065 0.4418 0.0115 0.2258 -16.0359 0.1847 0.2895 0.1509 0.0311 -0.0568 0.3600 0.7742 2.5391 -0.2825 -1.7167 0.4400 0.0234 0.2276 -7.1179 0.1762 0.2617 0.1509 0.0533 -0.0541 0.4800 0.7333 2.6621 -0.0026 -1.7997 0.4394 0.0372 0.2290 -0.0486 0.1679 0.2278 0.1503 0.0777 -0.0500 0.6000 0.6980 2.7785 0.4300 -1.5832 0.4397 0.0514 0.2300 6.5067 0.1606 0.1922 0.1491 0.1028 -0.0451 0.7200 0.6700 2.8884 1.0175 -1.0351 0.4406 0.0644 0.2307 12.6761 0.1546 0.1582 0.1475 0.1274 -0.0398 0.8400 0.6492 2.9916 1.7281 -0.1902 0.4418 0.0748 0.2311 18.1294 0.1500 0.1285 0.1451 0.1500 -0.0343 0.9600 0.6341 3.0883 2.4804 0.8179 0.4430 0.0810 0.2310 22.3536 0.1465 0.1047 0.1413 0.1694 -0.0295 1.0800 0.6220 3.1784 3.1350 1.7324 0.4439 0.0814 0.2306 24.7967 0.1435 0.0881 0.1355 0.1839 -0.0263 1.2000 0.6109 3.2618 3.5018 2.1800 0.4443 0.0746 0.2299 24.9121 0.1404 0.0797 0.1267 0.1911 -0.0267 1.3187 0.6005 3.3380 3.6028 2.2155 0.4442 0.0632 0.2288 23.5003 0.1374 0.0751 0.1148 0.1930 -0.0301 1.4158 0.5925 3.3954 3.6782 2.3255 0.4439 0.0543 0.2276 22.4650 0.1349 0.0693 0.1035 0.1946 -0.0333 1.5115 0.5848 3.4478 3.7481 2.4795 0.4434 0.0458 0.2262 21.5369 0.1323 0.0632 0.0921 0.1962 -0.0364 1.6073 0.5775 3.4961 3.8132 2.6513 0.4428 0.0376 0.2246 20.6864 0.1297 0.0579 0.0816 0.1974 -0.0394 1.7030 0.5703 3.5401 3.8737 2.8181 0.4420 0.0298 0.2228 19.9009 0.1271 0.0539 0.0729 0.1983 -0.0419 1.7988 0.5632 3.5800 3.9293 2.9652 0.4410 0.0223 0.2207 19.1706 0.1243 0.0514 0.0662 0.1989 -0.0438 1.8945 0.5561 3.6156 3.9799 3.1020 0.4397 0.0151 0.2184 18.4872 0.1215 0.0497 0.0607 0.1993 -0.0453 1.9903 0.5490 3.6471 4.0256 3.2461 0.4382 0.0081 0.2159 17.8438 0.1185 0.0480 0.0554 0.1996 -0.0468 2.0860 0.5418 3.6744 4.0660 3.3908 0.4364 0.0015 0.2132 17.2350 0.1155 0.0462 0.0501 0.1998 -0.0486 2.1818 0.5344 3.6975 4.1013 3.5236 0.4343 -0.0048 0.2102 16.6558 0.1123 0.0444 0.0447 0.1999 -0.0505 2.2775 0.5267 3.7164 4.1311 3.6339 0.4319 -0.0109 0.2069 16.1024 0.1090 0.0426 0.0390 0.2001 -0.0528 2.3733 0.5187 3.7311 4.1554 3.7103 0.4291 -0.0166 0.2035 15.5713 0.1056 0.0407 0.0330 0.2002 -0.0554 2.4691 0.5102 3.7416 4.1741 3.7419 0.4260 -0.0221 0.1998 15.0596 0.1020 0.0387 0.0265 0.2004 -0.0584 2.5648 0.5013 3.7479 4.1875 3.7482 0.4225 -0.0273 0.1960 14.5659 0.0983 0.0366 0.0199 0.2006 -0.0616 2.6606 0.4918 3.7500 4.1957 3.7503 0.4185 -0.0324 0.1923 14.0893 0.0946 0.0346 0.0134 0.2006 -0.0646 2.7563 0.4817 3.7500 4.2008 3.7502 0.4142 -0.0372 0.1885 13.6344 0.0908 0.0325 0.0070 0.2005 -0.0675 2.8521 0.4708 3.7500 4.2049 3.7502 0.4094 -0.0419 0.1847 13.2053 0.0870 0.0305 0.0008 0.2002 -0.0704 2.9478 0.4592 3.7500 4.2078 3.7502 0.4041 -0.0463 0.1809 12.7994 0.0831 0.0284 -0.0053 0.1999 -0.0731 3.0436 0.4467 3.7500 4.2096 3.7502 0.3984 -0.0505 0.1771 12.4144 0.0791 0.0264 -0.0113 0.1995 -0.0757 3.1393 0.4332 3.7500 4.2101 3.7502 0.3921 -0.0545 0.1734 12.0484 0.0751 0.0243 -0.0172 0.1990 -0.0782 3.2351 0.4188 3.7500 4.2092 3.7502 0.3853 -0.0583 0.1696 11.6993 0.0710 0.0222 -0.0229 0.1985 -0.0805 3.3308 0.4032 3.7500 4.2068 3.7502 0.3780 -0.0619 0.1658 11.3655 0.0669 0.0202 -0.0285 0.1978 -0.0826 3.4266 0.3865 3.7500 4.2026 3.7502 0.3701 -0.0653 0.1620 11.0451 0.0626 0.0181 -0.0339 0.1972 -0.0847 3.5223 0.3685 3.7500 4.1965 3.7502 0.3615 -0.0685 0.1582 10.7367 0.0583 0.0161 -0.0393 0.1964 -0.0865 3.6181 0.3492 3.7500 4.1881 3.7501 0.3524 -0.0716 0.1545 10.4384 0.0539 0.0142 -0.0445 0.1957 -0.0882 3.7139 0.3285 3.7500 4.1770 3.7501 0.3426 -0.0744 0.1507 10.1487 0.0495 0.0123 -0.0496 0.1949 -0.0897 3.8096 0.3064 3.7500 4.1627 3.7501 0.3322 -0.0771 0.1469 9.8654 0.0450 0.0104 -0.0545 0.1941 -0.0911 3.9054 0.2827 3.7500 4.1443 3.7501 0.3211 -0.0796 0.1431 9.5863 0.0405 0.0087 -0.0593 0.1934 -0.0923 4.0011 0.2574 3.7500 4.1204 3.7501 0.3093 -0.0820 0.1393 9.3080 0.0359 0.0070 -0.0640 0.1926 -0.0934 4.0930 0.2315 3.7500 4.0905 3.7501 0.2973 -0.0841 0.1357 9.0377 0.0314 0.0056 -0.0684 0.1919 -0.0942 4.1187 0.2240 3.7500 4.0806 3.7501 0.2939 -0.0847 0.1347 8.9609 0.0302 0.0052 -0.0696 0.1917 -0.0944 4.1404 0.2175 3.7500 4.0715 3.7500 0.2909 -0.0851 0.1338 8.8950 0.0291 0.0049 -0.0706 0.1916 -0.0946 4.1622 0.2110 3.7500 4.0618 3.7500 0.2878 -0.0856 0.1330 8.8283 0.0281 0.0045 -0.0716 0.1914 -0.0947 4.1840 0.2043 3.7500 4.0512 3.7500 0.2848 -0.0861 0.1321 8.7606 0.0270 0.0042 -0.0726 0.1913 -0.0949 4.2058 0.1956 3.7500 4.0402 3.7503 0.2797 -0.0869 0.1313 8.6925 0.0257 0.0039 -0.0741 0.1901 -0.0953 4.2276 0.1825 3.7500 4.0286 3.7601 0.2704 -0.0883 0.1304 8.6240 0.0238 0.0034 -0.0765 0.1866 -0.0962 4.2493 0.1639 3.7500 4.0161 3.7954 0.2558 -0.0907 0.1295 8.5543 0.0212 0.0027 -0.0802 0.1802 -0.0978 4.2711 0.1367 3.7500 4.0025 3.8763 0.2326 -0.0945 0.1287 8.4829 0.0176 0.0019 -0.0857 0.1693 -0.1004 4.2929 0.0858 3.7500 3.9879 4.2039 0.1862 -0.1020 0.1278 8.4102 0.0110 0.0007 -0.0966 0.1457 -0.1059 4.3125 0.0081 3.7500 3.7500 3.7500 0.1131 -0.1139 0.1270 7.8794 0.0010 0.0000 -0.1139 0.0000 0.0000 RADIUS: 4.31 PROPELLER RADIUS (IN) HUBRAD: 0.45 HUB RADIUS (IN) HUBTRA: 1.20 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.041486 TOTAL WEIGHT (Kg) = 0.018814 TOTAL VOLUME (IN**3) = 0.675860 TOTAL PROJECTED AREA (IN**2) = 4.3025 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000204 MOMENT OF INERTIA (Kg-M**2) = 0.000023 STATIC MOMENT, ONE SIDE (IN-LB) = 0.020798 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.700 DENSITY (INPUT FILE, LB/IN**3) = 0.6138E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.6138E-01 ACTIVITY FACTOR = 64.007 INNER LIMIT (NORMALIZED BY RADIUS) = 0.104 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 28439.66 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.00, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 3.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.