10x7SF (10x7SF.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 -0.9002 0.0000 0.0000 0.2500 0.0000 0.1008 0.0000 0.0504 0.0000 0.0300 0.0000 0.0000 0.0833 0.4773 -0.3185 0.0093 -0.4218 0.2505 0.0031 0.0967 1.0200 0.0461 0.0920 0.0323 0.0088 -0.0757 0.1666 0.4603 0.2410 0.0727 -0.8109 0.2593 0.0116 0.0927 3.9743 0.0427 0.0908 0.0387 0.0267 -0.0732 0.2499 0.4510 0.7783 0.2365 -1.0843 0.2751 0.0247 0.0889 8.5639 0.0401 0.0902 0.0480 0.0492 -0.0694 0.3332 0.4520 1.2933 0.5326 -1.0933 0.2961 0.0415 0.0852 14.2745 0.0385 0.0852 0.0579 0.0749 -0.0640 0.4165 0.4646 1.7861 0.9707 -0.7604 0.3212 0.0609 0.0817 20.3509 0.0379 0.0771 0.0714 0.1024 -0.0570 0.4998 0.4885 2.2566 1.5331 -0.0877 0.3487 0.0822 0.0783 26.0220 0.0383 0.0674 0.0890 0.1302 -0.0484 0.5831 0.5218 2.7049 2.1765 0.8435 0.3773 0.1044 0.0751 30.7130 0.0392 0.0574 0.1091 0.1571 -0.0382 0.6664 0.5613 3.1309 2.8370 1.8845 0.4057 0.1266 0.0721 34.1200 0.0405 0.0486 0.1303 0.1816 -0.0261 0.7497 0.6038 3.5347 3.4409 2.8371 0.4322 0.1478 0.0692 36.1471 0.0418 0.0424 0.1511 0.2020 -0.0128 0.8330 0.6465 3.9162 3.9153 3.4704 0.4557 0.1673 0.0665 36.7991 0.0430 0.0409 0.1705 0.2145 -0.0006 0.9188 0.6889 4.2861 4.2861 3.8757 0.4768 0.1850 0.0639 36.5904 0.0440 0.0435 0.1884 0.2196 0.0095 1.0485 0.7496 4.8000 4.8000 4.4534 0.5066 0.2085 0.0602 36.0775 0.0451 0.0465 0.2122 0.2254 0.0234 1.1807 0.8074 5.2685 5.2685 4.9949 0.5344 0.2283 0.0568 35.3817 0.0459 0.0485 0.2324 0.2292 0.0359 1.3129 0.8611 5.6810 5.6810 5.4793 0.5596 0.2443 0.0539 34.5542 0.0464 0.0497 0.2488 0.2311 0.0468 1.4451 0.9104 6.0374 6.0374 5.9000 0.5823 0.2567 0.0514 33.6212 0.0468 0.0500 0.2616 0.2312 0.0562 1.5773 0.9554 6.3378 6.3378 6.2549 0.6023 0.2655 0.0492 32.5995 0.0470 0.0496 0.2709 0.2296 0.0641 1.7095 0.9960 6.5822 6.5822 6.5419 0.6198 0.2711 0.0475 31.5005 0.0473 0.0488 0.2769 0.2267 0.0707 1.8417 1.0321 6.7706 6.7706 6.7633 0.6347 0.2737 0.0461 30.3320 0.0476 0.0477 0.2800 0.2225 0.0761 1.9739 1.0637 6.9029 6.9029 6.9219 0.6470 0.2733 0.0452 29.0997 0.0481 0.0465 0.2802 0.2174 0.0805 2.1061 1.0906 6.9792 6.9792 7.0183 0.6567 0.2702 0.0446 27.8078 0.0487 0.0454 0.2778 0.2116 0.0839 2.2383 1.1130 7.0000 7.0000 7.0492 0.6638 0.2645 0.0445 26.4616 0.0495 0.0446 0.2729 0.2055 0.0865 2.3705 1.1305 7.0000 7.0000 7.0558 0.6683 0.2565 0.0445 25.1729 0.0503 0.0440 0.2658 0.1994 0.0874 2.5027 1.1433 7.0000 7.0000 7.0600 0.6702 0.2464 0.0445 23.9967 0.0509 0.0436 0.2567 0.1934 0.0861 2.6349 1.1513 7.0000 7.0000 7.0618 0.6696 0.2346 0.0445 22.9199 0.0512 0.0433 0.2458 0.1873 0.0830 2.7671 1.1543 7.0000 7.0000 7.0613 0.6663 0.2212 0.0445 21.9310 0.0514 0.0431 0.2332 0.1810 0.0779 2.8992 1.1523 7.0000 7.0000 7.0598 0.6605 0.2064 0.0445 21.0201 0.0513 0.0429 0.2192 0.1744 0.0714 3.0314 1.1452 7.0000 7.0000 7.0588 0.6520 0.1905 0.0445 20.1789 0.0510 0.0423 0.2039 0.1676 0.0636 3.1636 1.1330 7.0000 7.0000 7.0583 0.6410 0.1736 0.0445 19.3998 0.0504 0.0414 0.1877 0.1604 0.0547 3.2958 1.1157 7.0000 7.0000 7.0584 0.6274 0.1560 0.0445 18.6767 0.0496 0.0401 0.1706 0.1528 0.0449 3.4280 1.0930 7.0000 7.0000 7.0592 0.6112 0.1379 0.0445 18.0038 0.0486 0.0385 0.1528 0.1450 0.0345 3.5602 1.0651 7.0000 7.0000 7.0607 0.5924 0.1194 0.0445 17.3762 0.0474 0.0366 0.1347 0.1368 0.0236 3.6924 1.0318 7.0000 7.0000 7.0628 0.5711 0.1009 0.0445 16.7897 0.0459 0.0344 0.1163 0.1284 0.0124 3.8246 0.9930 7.0000 7.0000 7.0658 0.5471 0.0824 0.0445 16.2404 0.0442 0.0319 0.0979 0.1196 0.0012 3.9568 0.9487 7.0000 7.0000 7.0699 0.5206 0.0643 0.0445 15.7251 0.0422 0.0292 0.0797 0.1106 -0.0099 4.0890 0.8988 7.0000 7.0000 7.0757 0.4914 0.0467 0.0445 15.2407 0.0400 0.0263 0.0619 0.1013 -0.0207 4.2212 0.8433 7.0000 7.0000 7.0836 0.4597 0.0298 0.0445 14.7847 0.0375 0.0233 0.0446 0.0918 -0.0308 4.3534 0.7820 7.0000 7.0000 7.0943 0.4254 0.0139 0.0445 14.3545 0.0348 0.0202 0.0281 0.0822 -0.0402 4.4856 0.7150 7.0000 7.0000 7.1079 0.3885 -0.0008 0.0445 13.9482 0.0318 0.0170 0.0126 0.0723 -0.0486 4.6178 0.6422 7.0000 7.0000 7.1277 0.3490 -0.0142 0.0445 13.5639 0.0286 0.0139 -0.0017 0.0624 -0.0558 4.7444 0.5621 7.0000 7.0000 7.1530 0.3041 -0.0266 0.0445 13.2148 0.0250 0.0108 -0.0154 0.0503 -0.0621 4.7753 0.5357 7.0000 7.0000 7.1602 0.2868 -0.0308 0.0451 13.1324 0.0241 0.0099 -0.0200 0.0445 -0.0645 4.8005 0.5108 7.0000 7.0000 7.1653 0.2697 -0.0350 0.0468 13.0657 0.0239 0.0093 -0.0244 0.0389 -0.0667 4.8258 0.4826 7.0000 7.0000 7.1695 0.2495 -0.0400 0.0496 12.9997 0.0239 0.0087 -0.0295 0.0320 -0.0695 4.8510 0.4503 7.0000 7.0000 7.1728 0.2253 -0.0459 0.0536 12.9343 0.0241 0.0080 -0.0356 0.0233 -0.0729 4.8763 0.4125 7.0000 7.0000 7.1905 0.1959 -0.0530 0.0587 12.8695 0.0242 0.0073 -0.0429 0.0116 -0.0773 4.9015 0.3671 7.0000 7.0000 7.2211 0.1593 -0.0618 0.0649 12.8054 0.0238 0.0062 -0.0521 -0.0043 -0.0831 4.9268 0.3087 7.0000 7.0000 7.2204 0.1099 -0.0739 0.0722 12.7419 0.0223 0.0051 -0.0646 -0.0293 -0.0925 4.9520 0.2189 7.0000 7.0000 7.2515 0.0301 -0.0933 0.0807 12.6791 0.0177 0.0031 -0.0856 -0.0714 -0.1078 4.9773 0.1142 7.0000 7.0000 7.6713 -0.0641 -0.1155 0.0904 12.6168 0.0103 0.0010 -0.1109 -0.1193 -0.1240 5.0000 0.0199 7.0000 7.0035 7.0035 -0.1489 -0.1346 0.1000 12.5674 0.0020 0.0000 -0.1346 0.0000 0.0000 RADIUS: 5.00 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.83 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.026054 TOTAL WEIGHT (Kg) = 0.011816 TOTAL VOLUME (IN**3) = 0.424454 TOTAL PROJECTED AREA (IN**2) = 7.8729 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000370 MOMENT OF INERTIA (Kg-M**2) = 0.000042 STATIC MOMENT, ONE SIDE (IN-LB) = 0.025101 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 = 129.506 INNER LIMIT (NORMALIZED BY RADIUS) = 0.050 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 5305.22 BASED ON MODULUS (MILLION) = 1.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 4.90, E63 (Transition Start, Airfoil 1) AIRFOIL2: 5.00, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412