12x8SF (12x8SF.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 0.0985 0.0000 0.0000 0.2500 0.0000 0.1008 0.0000 0.0504 0.0000 0.0400 0.0000 0.0000 0.1000 0.4746 0.7324 0.0153 -0.4591 0.2520 0.0076 0.0963 1.3918 0.0457 0.0890 0.0466 0.0121 -0.0595 0.2000 0.4595 1.3398 0.1186 -0.8812 0.2664 0.0285 0.0920 5.3893 0.0423 0.0914 0.0646 0.0350 -0.0499 0.3000 0.4579 1.9207 0.3806 -1.1199 0.2908 0.0595 0.0878 11.4145 0.0402 0.0931 0.0890 0.0641 -0.0355 0.4000 0.4724 2.4751 0.8390 -0.9943 0.3228 0.0978 0.0839 18.4610 0.0396 0.0903 0.1179 0.0975 -0.0172 0.5000 0.5035 3.0029 1.4889 -0.4426 0.3601 0.1404 0.0801 25.3583 0.0403 0.0846 0.1529 0.1331 0.0039 0.6000 0.5487 3.5043 2.2841 0.4925 0.4005 0.1845 0.0765 31.2111 0.0420 0.0772 0.1923 0.1688 0.0266 0.7000 0.6035 3.9792 3.1480 1.6798 0.4416 0.2272 0.0732 35.5933 0.0442 0.0692 0.2324 0.2030 0.0500 0.8000 0.6628 4.4276 3.9890 2.9312 0.4812 0.2658 0.0700 38.4350 0.0464 0.0616 0.2698 0.2335 0.0729 0.9000 0.7216 4.8495 4.7149 4.0066 0.5170 0.2974 0.0670 39.8207 0.0483 0.0563 0.3008 0.2577 0.0930 1.0000 0.7759 5.2448 5.2436 4.7086 0.5467 0.3192 0.0641 39.8467 0.0498 0.0556 0.3225 0.2708 0.1062 1.1031 0.8268 5.6246 5.6246 5.1518 0.5721 0.3337 0.0614 39.0609 0.0508 0.0586 0.3373 0.2752 0.1137 1.2586 0.8997 6.1445 6.1445 5.7717 0.6079 0.3528 0.0577 37.8466 0.0519 0.0620 0.3568 0.2799 0.1245 1.4172 0.9690 6.6086 6.6086 6.3358 0.6413 0.3688 0.0544 36.5805 0.0527 0.0640 0.3734 0.2825 0.1347 1.5759 1.0333 7.0060 7.0060 6.8212 0.6716 0.3815 0.0516 35.2822 0.0533 0.0648 0.3867 0.2829 0.1441 1.7345 1.0925 7.3367 7.3367 7.2244 0.6987 0.3912 0.0492 33.9490 0.0538 0.0646 0.3969 0.2813 0.1528 1.8931 1.1464 7.6008 7.6008 7.5438 0.7228 0.3978 0.0473 32.5788 0.0543 0.0638 0.4042 0.2780 0.1608 2.0517 1.1951 7.7982 7.7982 7.7823 0.7438 0.4016 0.0459 31.1704 0.0549 0.0626 0.4086 0.2733 0.1683 2.2103 1.2384 7.9289 7.9289 7.9449 0.7616 0.4026 0.0450 29.7228 0.0557 0.0613 0.4103 0.2675 0.1752 2.3690 1.2763 7.9929 7.9929 8.0312 0.7764 0.4009 0.0446 28.2354 0.0569 0.0603 0.4096 0.2611 0.1817 2.5276 1.3086 8.0000 8.0000 8.0486 0.7880 0.3966 0.0445 26.7361 0.0582 0.0598 0.4064 0.2545 0.1874 2.6862 1.3354 8.0000 8.0000 8.0552 0.7966 0.3900 0.0445 25.3606 0.0594 0.0597 0.4009 0.2479 0.1910 2.8448 1.3564 8.0000 8.0000 8.0588 0.8020 0.3812 0.0445 24.1115 0.0604 0.0598 0.3933 0.2413 0.1924 3.0034 1.3717 8.0000 8.0000 8.0592 0.8043 0.3705 0.0445 22.9733 0.0610 0.0604 0.3837 0.2346 0.1915 3.1621 1.3812 8.0000 8.0000 8.0574 0.8036 0.3580 0.0445 21.9327 0.0615 0.0611 0.3723 0.2275 0.1885 3.3207 1.3848 8.0000 8.0000 8.0560 0.7997 0.3438 0.0445 20.9781 0.0616 0.0613 0.3592 0.2201 0.1838 3.4793 1.3823 8.0000 8.0000 8.0551 0.7927 0.3281 0.0445 20.0999 0.0615 0.0610 0.3445 0.2122 0.1775 3.6379 1.3738 8.0000 8.0000 8.0547 0.7826 0.3112 0.0445 19.2895 0.0611 0.0602 0.3283 0.2039 0.1697 3.7966 1.3592 8.0000 8.0000 8.0549 0.7694 0.2930 0.0445 18.5398 0.0605 0.0589 0.3109 0.1952 0.1605 3.9552 1.3383 8.0000 8.0000 8.0556 0.7531 0.2738 0.0445 17.8443 0.0596 0.0571 0.2923 0.1860 0.1501 4.1138 1.3112 8.0000 8.0000 8.0571 0.7337 0.2537 0.0445 17.1976 0.0583 0.0549 0.2727 0.1764 0.1387 4.2724 1.2776 8.0000 8.0000 8.0594 0.7112 0.2328 0.0445 16.5948 0.0569 0.0522 0.2522 0.1665 0.1263 4.4310 1.2376 8.0000 8.0000 8.0626 0.6855 0.2114 0.0445 16.0318 0.0551 0.0491 0.2310 0.1561 0.1132 4.5897 1.1911 8.0000 8.0000 8.0672 0.6568 0.1895 0.0445 15.5048 0.0530 0.0456 0.2092 0.1454 0.0993 4.7483 1.1379 8.0000 8.0000 8.0733 0.6250 0.1673 0.0445 15.0106 0.0506 0.0417 0.1869 0.1344 0.0850 4.9069 1.0781 8.0000 8.0000 8.0815 0.5900 0.1450 0.0445 14.5463 0.0480 0.0376 0.1643 0.1231 0.0704 5.0655 1.0115 8.0000 8.0000 8.0925 0.5520 0.1227 0.0445 14.1093 0.0450 0.0333 0.1415 0.1114 0.0555 5.2241 0.9380 8.0000 8.0000 8.1059 0.5108 0.1006 0.0445 13.6972 0.0417 0.0289 0.1186 0.0996 0.0407 5.3828 0.8576 8.0000 8.0000 8.1242 0.4665 0.0789 0.0445 13.3082 0.0382 0.0244 0.0959 0.0875 0.0260 5.5414 0.7702 8.0000 8.0000 8.1499 0.4192 0.0576 0.0445 12.9402 0.0343 0.0199 0.0733 0.0753 0.0115 5.6933 0.6741 8.0000 8.0000 8.1831 0.3652 0.0366 0.0445 12.6061 0.0300 0.0155 0.0507 0.0605 -0.0029 5.7303 0.6424 8.0000 8.0000 8.1934 0.3445 0.0300 0.0445 12.5273 0.0286 0.0142 0.0436 0.0531 -0.0074 5.7606 0.6126 8.0000 8.0000 8.2028 0.3239 0.0239 0.0445 12.4634 0.0273 0.0129 0.0369 0.0452 -0.0117 5.7909 0.5787 8.0000 8.0000 8.2124 0.2995 0.0170 0.0445 12.4002 0.0258 0.0116 0.0293 0.0354 -0.0165 5.8212 0.5398 8.0000 8.0000 8.2227 0.2704 0.0092 0.0445 12.3377 0.0240 0.0101 0.0207 0.0231 -0.0220 5.8515 0.4946 8.0000 8.0000 8.2550 0.2352 0.0001 0.0445 12.2757 0.0220 0.0086 0.0108 0.0072 -0.0286 5.8818 0.4401 8.0000 8.0000 8.3033 0.1911 -0.0108 0.0445 12.2144 0.0196 0.0069 -0.0012 -0.0134 -0.0365 5.9121 0.3699 8.0000 8.0000 8.3802 0.1318 -0.0249 0.0445 12.1536 0.0165 0.0050 -0.0167 -0.0430 -0.0471 5.9424 0.2622 8.0000 8.0000 8.5315 0.0359 -0.0474 0.0445 12.0935 0.0117 0.0029 -0.0412 -0.0951 -0.0656 5.9727 0.1368 8.0000 8.0000 9.1424 -0.0772 -0.0731 0.0445 12.0339 0.0061 0.0008 -0.0697 -0.1521 -0.0849 6.0000 0.0239 8.0000 8.0040 8.0040 -0.1790 -0.0957 0.0445 11.9867 0.0011 0.0000 -0.0957 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) = 0.040346 TOTAL WEIGHT (Kg) = 0.018297 TOTAL VOLUME (IN**3) = 0.657285 TOTAL PROJECTED AREA (IN**2) = 11.2286 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000894 MOMENT OF INERTIA (Kg-M**2) = 0.000101 STATIC MOMENT, ONE SIDE (IN-LB) = 0.049677 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) = 3926.81 BASED ON MODULUS (MILLION) = 1.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 5.90, E63 (Transition Start, Airfoil 1) AIRFOIL2: 6.00, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412