11x3.8SF (11x38SF.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 0.5000 3.8000 0.0000 0.0000 0.2500 0.0000 0.1008 0.0000 0.0504 0.0000 0.0400 0.0000 0.0000 0.0916 0.4756 3.8000 0.0133 -0.4186 0.2512 0.0063 0.0967 1.3201 0.0460 0.0889 0.0452 0.0109 -0.0605 0.1832 0.4589 3.8000 0.1024 -0.8053 0.2629 0.0232 0.0927 5.0845 0.0425 0.0903 0.0592 0.0317 -0.0539 0.2748 0.4533 3.8000 0.3274 -1.0453 0.2829 0.0479 0.0889 10.7358 0.0403 0.0912 0.0778 0.0579 -0.0441 0.3664 0.4617 3.8000 0.7187 -0.9757 0.3094 0.0774 0.0852 17.3377 0.0393 0.0873 0.0982 0.0877 -0.0319 0.4580 0.4849 3.8000 1.2674 -0.5365 0.3406 0.1091 0.0817 23.7698 0.0396 0.0806 0.1222 0.1189 -0.0181 0.5496 0.5208 3.8000 1.9225 0.2348 0.3745 0.1402 0.0783 29.1063 0.0408 0.0723 0.1486 0.1497 -0.0035 0.6412 0.5654 3.8000 2.5999 1.2098 0.4094 0.1681 0.0751 32.8351 0.0425 0.0634 0.1738 0.1782 0.0111 0.7328 0.6142 3.8000 3.1991 2.1981 0.4433 0.1902 0.0721 34.7919 0.0443 0.0552 0.1945 0.2030 0.0248 0.8244 0.6635 3.8000 3.6241 2.9793 0.4745 0.2038 0.0692 34.9788 0.0459 0.0491 0.2076 0.2215 0.0361 0.9160 0.7109 3.8000 3.7985 3.3416 0.5011 0.2062 0.0665 33.4242 0.0473 0.0475 0.2104 0.2293 0.0411 1.0104 0.7576 3.8000 3.8000 3.4181 0.5244 0.2007 0.0639 30.9030 0.0484 0.0496 0.2058 0.2276 0.0406 1.1530 0.8244 3.8000 3.8000 3.5173 0.5572 0.1927 0.0602 27.6780 0.0496 0.0519 0.1993 0.2250 0.0408 1.2985 0.8880 3.8000 3.8000 3.6012 0.5878 0.1850 0.0569 24.9750 0.0505 0.0533 0.1934 0.2224 0.0419 1.4439 0.9469 3.8000 3.8000 3.6661 0.6156 0.1780 0.0539 22.7270 0.0510 0.0539 0.1882 0.2200 0.0437 1.5893 1.0012 3.8000 3.8000 3.7142 0.6405 0.1715 0.0514 20.8336 0.0514 0.0539 0.1835 0.2175 0.0460 1.7347 1.0507 3.8000 3.8000 3.7482 0.6626 0.1655 0.0492 19.2203 0.0517 0.0535 0.1793 0.2150 0.0485 1.8802 1.0953 3.8000 3.8000 3.7728 0.6818 0.1599 0.0475 17.8313 0.0520 0.0529 0.1756 0.2125 0.0513 2.0256 1.1350 3.8000 3.8000 3.7916 0.6982 0.1547 0.0461 16.6242 0.0524 0.0523 0.1722 0.2100 0.0541 2.1710 1.1698 3.8000 3.8000 3.8055 0.7117 0.1496 0.0452 15.5664 0.0529 0.0517 0.1690 0.2075 0.0569 2.3164 1.1994 3.8000 3.8000 3.8132 0.7224 0.1448 0.0446 14.6324 0.0536 0.0513 0.1661 0.2051 0.0594 2.4619 1.2240 3.8000 3.8000 3.8186 0.7302 0.1400 0.0445 13.8021 0.0545 0.0511 0.1633 0.2027 0.0618 2.6073 1.2433 3.8000 3.8000 3.8223 0.7352 0.1353 0.0445 13.0593 0.0553 0.0511 0.1605 0.2000 0.0638 2.7527 1.2573 3.8000 3.8000 3.8245 0.7374 0.1307 0.0445 12.3913 0.0560 0.0511 0.1577 0.1967 0.0654 2.8982 1.2660 3.8000 3.8000 3.8255 0.7366 0.1261 0.0445 11.7873 0.0563 0.0511 0.1548 0.1928 0.0666 3.0436 1.2693 3.8000 3.8000 3.8252 0.7331 0.1215 0.0445 11.2388 0.0565 0.0511 0.1517 0.1881 0.0674 3.1890 1.2671 3.8000 3.8000 3.8245 0.7267 0.1169 0.0445 10.7385 0.0564 0.0508 0.1483 0.1827 0.0676 3.3344 1.2593 3.8000 3.8000 3.8240 0.7174 0.1120 0.0445 10.2803 0.0560 0.0501 0.1447 0.1768 0.0675 3.4799 1.2459 3.8000 3.8000 3.8239 0.7053 0.1070 0.0445 9.8593 0.0554 0.0491 0.1406 0.1703 0.0669 3.6253 1.2268 3.8000 3.8000 3.8241 0.6904 0.1018 0.0445 9.4711 0.0546 0.0476 0.1360 0.1633 0.0658 3.7707 1.2019 3.8000 3.8000 3.8248 0.6726 0.0962 0.0445 9.1121 0.0535 0.0457 0.1309 0.1558 0.0642 3.9162 1.1711 3.8000 3.8000 3.8260 0.6519 0.0902 0.0445 8.7791 0.0521 0.0434 0.1251 0.1478 0.0619 4.0616 1.1344 3.8000 3.8000 3.8279 0.6284 0.0838 0.0445 8.4694 0.0505 0.0408 0.1186 0.1394 0.0589 4.2070 1.0918 3.8000 3.8000 3.8307 0.6021 0.0769 0.0445 8.1807 0.0486 0.0379 0.1113 0.1306 0.0552 4.3524 1.0430 3.8000 3.8000 3.8346 0.5729 0.0695 0.0445 7.9108 0.0464 0.0347 0.1032 0.1213 0.0507 4.4979 0.9882 3.8000 3.8000 3.8400 0.5408 0.0614 0.0445 7.6581 0.0440 0.0312 0.0941 0.1117 0.0453 4.6433 0.9271 3.8000 3.8000 3.8476 0.5059 0.0527 0.0445 7.4210 0.0413 0.0276 0.0840 0.1017 0.0390 4.7887 0.8597 3.8000 3.8000 3.8568 0.4682 0.0431 0.0445 7.1980 0.0383 0.0239 0.0729 0.0915 0.0317 4.9341 0.7860 3.8000 3.8000 3.8695 0.4276 0.0328 0.0445 6.9880 0.0350 0.0202 0.0605 0.0809 0.0233 5.0796 0.7059 3.8000 3.8000 3.8877 0.3841 0.0216 0.0445 6.7898 0.0314 0.0164 0.0470 0.0702 0.0138 5.2189 0.6169 3.8000 3.8000 3.9110 0.3338 0.0092 0.0445 6.6102 0.0275 0.0127 0.0318 0.0565 0.0029 5.2528 0.5875 3.8000 3.8000 3.9185 0.3143 0.0053 0.0445 6.5679 0.0261 0.0116 0.0269 0.0494 -0.0006 5.2806 0.5599 3.8000 3.8000 3.9252 0.2951 0.0017 0.0445 6.5337 0.0249 0.0106 0.0223 0.0419 -0.0039 5.3083 0.5286 3.8000 3.8000 3.9362 0.2723 -0.0023 0.0445 6.4998 0.0235 0.0095 0.0172 0.0325 -0.0076 5.3361 0.4929 3.8000 3.8000 3.9542 0.2452 -0.0068 0.0445 6.4662 0.0219 0.0083 0.0114 0.0205 -0.0118 5.3639 0.4512 3.8000 3.8000 3.9793 0.2123 -0.0120 0.0445 6.4330 0.0201 0.0070 0.0048 0.0055 -0.0166 5.3917 0.4011 3.8000 3.8000 4.0169 0.1712 -0.0181 0.0445 6.4002 0.0178 0.0056 -0.0032 -0.0141 -0.0223 5.4194 0.3365 3.8000 3.8000 4.0830 0.1159 -0.0258 0.0445 6.3676 0.0150 0.0040 -0.0132 -0.0414 -0.0295 5.4472 0.2375 3.8000 3.8000 4.2549 0.0265 -0.0373 0.0445 6.3354 0.0106 0.0020 -0.0284 -0.0873 -0.0402 5.4750 0.1241 3.8000 3.8000 4.7908 -0.0772 -0.0503 0.0445 6.3035 0.0055 0.0006 -0.0456 -0.1404 -0.0524 5.5000 0.0219 3.8000 3.8019 3.8019 -0.1705 -0.0617 0.0445 6.2783 0.0010 0.0000 -0.0617 0.0000 0.0000 RADIUS: 5.50 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.92 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.031996 TOTAL WEIGHT (Kg) = 0.014511 TOTAL VOLUME (IN**3) = 0.521254 TOTAL PROJECTED AREA (IN**2) = 10.0046 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000575 MOMENT OF INERTIA (Kg-M**2) = 0.000065 STATIC MOMENT, ONE SIDE (IN-LB) = 0.035070 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 = 129.434 INNER LIMIT (NORMALIZED BY RADIUS) = 0.045 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 4417.05 BASED ON MODULUS (MILLION) = 1.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.00, E63 (Transition Start, Airfoil 1) AIRFOIL2: 3.00, E63 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.