12x3.8SF (12x38SF.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 0.1000 0.4751 3.8000 0.0150 -0.4573 0.2520 0.0058 0.0963 1.3674 0.0458 0.0890 0.0448 0.0118 -0.0611 0.2000 0.4617 3.8000 0.1150 -0.8734 0.2664 0.0217 0.0920 5.2272 0.0425 0.0913 0.0578 0.0339 -0.0560 0.3000 0.4624 3.8000 0.3625 -1.1045 0.2908 0.0452 0.0878 10.8845 0.0406 0.0931 0.0747 0.0615 -0.0480 0.4000 0.4792 3.8000 0.7811 -0.9866 0.3228 0.0738 0.0839 17.2655 0.0402 0.0905 0.0944 0.0927 -0.0372 0.5000 0.5118 3.8000 1.3491 -0.4813 0.3601 0.1054 0.0801 23.2396 0.0410 0.0851 0.1187 0.1254 -0.0240 0.6000 0.5570 3.8000 2.0049 0.3442 0.4005 0.1376 0.0765 28.0045 0.0426 0.0777 0.1465 0.1577 -0.0087 0.7000 0.6104 3.8000 2.6635 1.3431 0.4416 0.1682 0.0732 31.1982 0.0447 0.0694 0.1745 0.1879 0.0085 0.8000 0.6671 3.8000 3.2341 2.3271 0.4812 0.1949 0.0700 32.7570 0.0467 0.0612 0.1999 0.2141 0.0270 0.9000 0.7232 3.8000 3.6344 3.0768 0.5170 0.2154 0.0670 32.7289 0.0484 0.0549 0.2200 0.2337 0.0454 1.0000 0.7759 3.8000 3.7986 3.4209 0.5467 0.2275 0.0641 31.1555 0.0498 0.0531 0.2325 0.2415 0.0605 1.1031 0.8268 3.8000 3.8000 3.4972 0.5721 0.2332 0.0614 28.7353 0.0508 0.0551 0.2394 0.2396 0.0722 1.2586 0.8997 3.8000 3.8000 3.5926 0.6079 0.2399 0.0577 25.6651 0.0519 0.0572 0.2480 0.2370 0.0882 1.4172 0.9690 3.8000 3.8000 3.6675 0.6413 0.2446 0.0544 23.1097 0.0527 0.0583 0.2547 0.2344 0.1026 1.5759 1.0333 3.8000 3.8000 3.7217 0.6716 0.2472 0.0516 20.9959 0.0533 0.0587 0.2595 0.2320 0.1148 1.7345 1.0925 3.8000 3.8000 3.7591 0.6987 0.2479 0.0492 19.2229 0.0538 0.0586 0.2623 0.2296 0.1249 1.8931 1.1464 3.8000 3.8000 3.7855 0.7228 0.2469 0.0473 17.7171 0.0543 0.0582 0.2634 0.2272 0.1330 2.0517 1.1951 3.8000 3.8000 3.8053 0.7438 0.2441 0.0459 16.4240 0.0549 0.0579 0.2628 0.2250 0.1389 2.2103 1.2384 3.8000 3.8000 3.8189 0.7616 0.2397 0.0450 15.3026 0.0557 0.0577 0.2606 0.2229 0.1429 2.3690 1.2763 3.8000 3.8000 3.8261 0.7764 0.2337 0.0446 14.3215 0.0569 0.0578 0.2570 0.2209 0.1451 2.5276 1.3086 3.8000 3.8000 3.8311 0.7880 0.2264 0.0445 13.4565 0.0582 0.0583 0.2520 0.2191 0.1454 2.6862 1.3354 3.8000 3.8000 3.8344 0.7966 0.2179 0.0445 12.6883 0.0594 0.0589 0.2458 0.2168 0.1440 2.8448 1.3564 3.8000 3.8000 3.8361 0.8020 0.2083 0.0445 12.0020 0.0604 0.0596 0.2384 0.2139 0.1410 3.0034 1.3717 3.8000 3.8000 3.8362 0.8043 0.1978 0.0445 11.3851 0.0610 0.0604 0.2300 0.2102 0.1366 3.1621 1.3812 3.8000 3.8000 3.8353 0.8036 0.1866 0.0445 10.8278 0.0615 0.0611 0.2206 0.2057 0.1310 3.3207 1.3848 3.8000 3.8000 3.8346 0.7997 0.1747 0.0445 10.3220 0.0616 0.0613 0.2104 0.2005 0.1243 3.4793 1.3823 3.8000 3.8000 3.8343 0.7927 0.1623 0.0445 9.8609 0.0615 0.0610 0.1995 0.1946 0.1169 3.6379 1.3738 3.8000 3.8000 3.8344 0.7826 0.1495 0.0445 9.4388 0.0611 0.0602 0.1879 0.1882 0.1088 3.7966 1.3592 3.8000 3.8000 3.8350 0.7694 0.1364 0.0445 9.0511 0.0605 0.0589 0.1758 0.1812 0.1002 3.9552 1.3383 3.8000 3.8000 3.8361 0.7531 0.1232 0.0445 8.6938 0.0596 0.0571 0.1633 0.1736 0.0911 4.1138 1.3112 3.8000 3.8000 3.8378 0.7337 0.1099 0.0445 8.3634 0.0583 0.0549 0.1505 0.1654 0.0817 4.2724 1.2776 3.8000 3.8000 3.8404 0.7112 0.0968 0.0445 8.0571 0.0569 0.0522 0.1375 0.1567 0.0721 4.4310 1.2376 3.8000 3.8000 3.8439 0.6855 0.0838 0.0445 7.7722 0.0551 0.0491 0.1243 0.1475 0.0625 4.5897 1.1911 3.8000 3.8000 3.8482 0.6568 0.0712 0.0445 7.5067 0.0530 0.0456 0.1112 0.1379 0.0529 4.7483 1.1379 3.8000 3.8000 3.8536 0.6250 0.0590 0.0445 7.2587 0.0506 0.0417 0.0982 0.1278 0.0435 4.9069 1.0781 3.8000 3.8000 3.8609 0.5900 0.0474 0.0445 7.0264 0.0480 0.0376 0.0853 0.1173 0.0344 5.0655 1.0115 3.8000 3.8000 3.8708 0.5520 0.0365 0.0445 6.8085 0.0450 0.0333 0.0728 0.1065 0.0257 5.2241 0.9380 3.8000 3.8000 3.8841 0.5108 0.0263 0.0445 6.6036 0.0417 0.0289 0.0607 0.0953 0.0175 5.3828 0.8576 3.8000 3.8000 3.9012 0.4665 0.0171 0.0445 6.4107 0.0382 0.0244 0.0491 0.0839 0.0100 5.5414 0.7702 3.8000 3.8000 3.9244 0.4192 0.0089 0.0445 6.2286 0.0343 0.0199 0.0381 0.0723 0.0032 5.6933 0.6732 3.8000 3.8000 3.9559 0.3642 0.0013 0.0445 6.0637 0.0300 0.0155 0.0273 0.0574 -0.0032 5.7303 0.6410 3.8000 3.8000 3.9652 0.3429 -0.0011 0.0445 6.0248 0.0285 0.0141 0.0237 0.0497 -0.0054 5.7606 0.6109 3.8000 3.8000 3.9735 0.3218 -0.0034 0.0445 5.9934 0.0272 0.0129 0.0203 0.0416 -0.0074 5.7909 0.5768 3.8000 3.8000 3.9894 0.2969 -0.0061 0.0445 5.9622 0.0257 0.0115 0.0164 0.0313 -0.0098 5.8212 0.5377 3.8000 3.8000 4.0128 0.2673 -0.0091 0.0445 5.9314 0.0239 0.0101 0.0119 0.0184 -0.0127 5.8515 0.4922 3.8000 3.8000 4.0451 0.2314 -0.0127 0.0445 5.9009 0.0219 0.0085 0.0066 0.0021 -0.0160 5.8818 0.4375 3.8000 3.8000 4.0922 0.1865 -0.0172 0.0445 5.8707 0.0195 0.0068 0.0000 -0.0190 -0.0203 5.9121 0.3670 3.8000 3.8000 4.1747 0.1260 -0.0232 0.0445 5.8408 0.0163 0.0049 -0.0087 -0.0485 -0.0259 5.9424 0.2590 3.8000 3.8000 4.3899 0.0283 -0.0328 0.0445 5.8113 0.0115 0.0025 -0.0225 -0.0982 -0.0352 5.9727 0.1353 3.8000 3.8000 5.0606 -0.0848 -0.0438 0.0445 5.7820 0.0060 0.0007 -0.0385 -0.1554 -0.0457 6.0000 0.0239 3.8000 3.8019 3.8019 -0.1866 -0.0537 0.0445 5.7588 0.0011 0.0000 -0.0537 0.0000 0.0000 RADIUS: 6.00 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 1.00 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.039432 TOTAL WEIGHT (Kg) = 0.017883 TOTAL VOLUME (IN**3) = 0.642396 TOTAL PROJECTED AREA (IN**2) = 11.9307 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000886 MOMENT OF INERTIA (Kg-M**2) = 0.000100 STATIC MOMENT, ONE SIDE (IN-LB) = 0.048877 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 = 129.456 INNER LIMIT (NORMALIZED BY RADIUS) = 0.042 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 3678.67 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.