11x7SF (11x7SF.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 -1.8854 0.0000 0.0000 0.2500 0.0000 0.1008 0.0000 0.0504 0.0000 0.0400 0.0000 0.0000 0.0916 0.4776 -1.2313 0.0092 -0.4166 0.2512 0.0030 0.0967 0.9143 0.0462 0.0881 0.0420 0.0098 -0.0621 0.1832 0.4654 -0.6022 0.0712 -0.7922 0.2629 0.0114 0.0927 3.5379 0.0431 0.0875 0.0476 0.0280 -0.0596 0.2748 0.4641 0.0018 0.2282 -1.0217 0.2829 0.0243 0.0889 7.5300 0.0412 0.0868 0.0553 0.0505 -0.0556 0.3664 0.4744 0.5809 0.5039 -0.9806 0.3094 0.0410 0.0852 12.3465 0.0404 0.0828 0.0643 0.0764 -0.0498 0.4580 0.4964 1.1350 0.8980 -0.6308 0.3406 0.0606 0.0817 17.3308 0.0405 0.0764 0.0768 0.1040 -0.0423 0.5496 0.5289 1.6640 1.3893 -0.0038 0.3745 0.0822 0.0783 21.9159 0.0414 0.0686 0.0933 0.1324 -0.0330 0.6412 0.5695 2.1681 1.9420 0.8148 0.4094 0.1051 0.0751 25.7350 0.0428 0.0603 0.1130 0.1604 -0.0220 0.7328 0.6153 2.6472 2.5126 1.7055 0.4433 0.1285 0.0721 28.6213 0.0444 0.0527 0.1344 0.1868 -0.0091 0.8244 0.6635 3.1012 3.0562 2.5221 0.4745 0.1513 0.0692 30.5412 0.0459 0.0475 0.1563 0.2094 0.0048 0.9160 0.7109 3.5303 3.5298 3.1100 0.5011 0.1730 0.0665 31.5212 0.0473 0.0468 0.1776 0.2238 0.0175 1.0104 0.7576 3.9463 3.9463 3.5471 0.5244 0.1934 0.0639 31.8653 0.0484 0.0500 0.1981 0.2304 0.0280 1.1530 0.8244 4.5244 4.5244 4.1739 0.5572 0.2205 0.0602 31.9855 0.0496 0.0537 0.2256 0.2382 0.0432 1.2985 0.8880 5.0515 5.0515 4.7642 0.5878 0.2440 0.0569 31.7649 0.0505 0.0563 0.2493 0.2437 0.0575 1.4439 0.9469 5.5156 5.5156 5.2943 0.6156 0.2633 0.0539 31.2983 0.0510 0.0578 0.2691 0.2470 0.0705 1.5893 1.0012 5.9167 5.9167 5.7564 0.6405 0.2788 0.0514 30.6467 0.0514 0.0583 0.2850 0.2483 0.0822 1.7347 1.0507 6.2547 6.2547 6.1475 0.6626 0.2906 0.0492 29.8489 0.0517 0.0579 0.2973 0.2478 0.0926 1.8802 1.0953 6.5297 6.5297 6.4644 0.6818 0.2989 0.0475 28.9309 0.0520 0.0571 0.3062 0.2458 0.1017 2.0256 1.1350 6.7416 6.7416 6.7097 0.6982 0.3038 0.0461 27.9104 0.0524 0.0559 0.3118 0.2424 0.1097 2.1710 1.1698 6.8906 6.8906 6.8856 0.7117 0.3057 0.0452 26.8002 0.0529 0.0546 0.3144 0.2380 0.1165 2.3164 1.1994 6.9765 6.9765 6.9920 0.7224 0.3045 0.0446 25.6099 0.0536 0.0534 0.3142 0.2329 0.1224 2.4619 1.2240 7.0000 7.0000 7.0262 0.7302 0.3006 0.0445 24.3484 0.0545 0.0525 0.3114 0.2273 0.1273 2.6073 1.2433 7.0000 7.0000 7.0332 0.7352 0.2943 0.0445 23.1367 0.0553 0.0519 0.3061 0.2215 0.1304 2.7527 1.2573 7.0000 7.0000 7.0377 0.7374 0.2857 0.0445 22.0341 0.0560 0.0515 0.2987 0.2156 0.1310 2.8982 1.2660 7.0000 7.0000 7.0398 0.7366 0.2752 0.0445 21.0273 0.0563 0.0512 0.2893 0.2095 0.1294 3.0436 1.2693 7.0000 7.0000 7.0396 0.7331 0.2630 0.0445 20.1048 0.0565 0.0511 0.2780 0.2029 0.1257 3.1890 1.2671 7.0000 7.0000 7.0384 0.7267 0.2493 0.0445 19.2569 0.0564 0.0508 0.2652 0.1960 0.1203 3.3344 1.2593 7.0000 7.0000 7.0375 0.7174 0.2343 0.0445 18.4752 0.0560 0.0501 0.2510 0.1886 0.1133 3.4799 1.2459 7.0000 7.0000 7.0371 0.7053 0.2182 0.0445 17.7525 0.0554 0.0491 0.2356 0.1809 0.1052 3.6253 1.2268 7.0000 7.0000 7.0372 0.6904 0.2012 0.0445 17.0826 0.0546 0.0476 0.2192 0.1727 0.0960 3.7707 1.2019 7.0000 7.0000 7.0378 0.6726 0.1836 0.0445 16.4601 0.0535 0.0457 0.2020 0.1641 0.0859 3.9162 1.1711 7.0000 7.0000 7.0391 0.6519 0.1655 0.0445 15.8802 0.0521 0.0434 0.1843 0.1552 0.0752 4.0616 1.1344 7.0000 7.0000 7.0412 0.6284 0.1471 0.0445 15.3389 0.0505 0.0408 0.1662 0.1459 0.0641 4.2070 1.0918 7.0000 7.0000 7.0442 0.6021 0.1288 0.0445 14.8324 0.0486 0.0379 0.1479 0.1362 0.0527 4.3524 1.0430 7.0000 7.0000 7.0486 0.5729 0.1107 0.0445 14.3576 0.0464 0.0347 0.1296 0.1263 0.0414 4.4979 0.9882 7.0000 7.0000 7.0545 0.5408 0.0930 0.0445 13.9117 0.0440 0.0312 0.1116 0.1160 0.0303 4.6433 0.9271 7.0000 7.0000 7.0617 0.5059 0.0759 0.0445 13.4922 0.0413 0.0276 0.0940 0.1054 0.0197 4.7887 0.8597 7.0000 7.0000 7.0717 0.4682 0.0598 0.0445 13.0968 0.0383 0.0239 0.0771 0.0946 0.0097 4.9341 0.7860 7.0000 7.0000 7.0858 0.4276 0.0447 0.0445 12.7235 0.0350 0.0202 0.0610 0.0836 0.0006 5.0796 0.7059 7.0000 7.0000 7.1042 0.3841 0.0309 0.0445 12.3706 0.0314 0.0164 0.0460 0.0725 -0.0074 5.2189 0.6176 7.0000 7.0000 7.1302 0.3346 0.0180 0.0445 12.0502 0.0275 0.0128 0.0316 0.0588 -0.0146 5.2528 0.5885 7.0000 7.0000 7.1375 0.3156 0.0137 0.0445 11.9747 0.0262 0.0117 0.0267 0.0519 -0.0172 5.2806 0.5612 7.0000 7.0000 7.1441 0.2967 0.0096 0.0445 11.9135 0.0250 0.0106 0.0221 0.0446 -0.0198 5.3083 0.5301 7.0000 7.0000 7.1515 0.2743 0.0048 0.0445 11.8529 0.0236 0.0095 0.0167 0.0355 -0.0228 5.3361 0.4945 7.0000 7.0000 7.1610 0.2476 -0.0007 0.0445 11.7929 0.0220 0.0083 0.0104 0.0240 -0.0264 5.3639 0.4530 7.0000 7.0000 7.1867 0.2152 -0.0073 0.0445 11.7336 0.0202 0.0070 0.0030 0.0093 -0.0308 5.3917 0.4031 7.0000 7.0000 7.2251 0.1747 -0.0153 0.0445 11.6748 0.0179 0.0056 -0.0062 -0.0099 -0.0365 5.4194 0.3387 7.0000 7.0000 7.2912 0.1203 -0.0262 0.0445 11.6166 0.0151 0.0040 -0.0184 -0.0366 -0.0442 5.4472 0.2400 7.0000 7.0000 7.4643 0.0322 -0.0437 0.0445 11.5589 0.0107 0.0021 -0.0382 -0.0816 -0.0570 5.4750 0.1252 7.0000 7.0000 8.0123 -0.0714 -0.0641 0.0445 11.5018 0.0056 0.0006 -0.0612 -0.1346 -0.0719 5.5000 0.0219 7.0000 7.0035 7.0035 -0.1647 -0.0823 0.0445 11.4566 0.0010 0.0000 -0.0823 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) = 0.032273 TOTAL WEIGHT (Kg) = 0.014636 TOTAL VOLUME (IN**3) = 0.525770 TOTAL PROJECTED AREA (IN**2) = 9.6518 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000580 MOMENT OF INERTIA (Kg-M**2) = 0.000066 STATIC MOMENT, ONE SIDE (IN-LB) = 0.035535 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) = 4518.59 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.