8x6SF (8x6SF.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 2.0490 0.0000 0.0000 0.2500 0.0000 0.1008 0.0000 0.0504 0.0000 0.0300 0.0000 0.0000 0.0750 0.4758 2.3749 0.0096 -0.3018 0.2492 0.0055 0.0962 1.1620 0.0458 0.0771 0.0346 0.0085 -0.0563 0.1500 0.4506 2.6868 0.0756 -0.5910 0.2536 0.0204 0.0917 4.5869 0.0413 0.0771 0.0474 0.0263 -0.0503 0.2250 0.4290 2.9847 0.2521 -0.8202 0.2625 0.0426 0.0875 10.1128 0.0375 0.0778 0.0660 0.0488 -0.0414 0.3000 0.4161 3.2686 0.5873 -0.8399 0.2752 0.0700 0.0834 17.3054 0.0347 0.0731 0.0859 0.0747 -0.0299 0.3750 0.4158 3.5384 1.1129 -0.5206 0.2908 0.1003 0.0796 25.2824 0.0331 0.0643 0.1094 0.1020 -0.0163 0.4500 0.4292 3.7942 1.8271 0.1964 0.3085 0.1315 0.0760 32.8701 0.0326 0.0541 0.1366 0.1290 -0.0015 0.5250 0.4541 4.0359 2.6745 1.2673 0.3276 0.1616 0.0725 39.0341 0.0329 0.0442 0.1647 0.1541 0.0141 0.6000 0.4867 4.2637 3.5376 2.5134 0.3473 0.1885 0.0693 43.1789 0.0337 0.0358 0.1907 0.1759 0.0299 0.6750 0.5225 4.4774 4.2558 3.6119 0.3668 0.2102 0.0662 45.0991 0.0346 0.0301 0.2120 0.1925 0.0446 0.7500 0.5587 4.6771 4.6751 4.2313 0.3854 0.2246 0.0634 44.7725 0.0354 0.0283 0.2264 0.2008 0.0554 0.8264 0.5945 4.8661 4.8661 4.4862 0.4030 0.2335 0.0607 43.1407 0.0361 0.0296 0.2356 0.2018 0.0615 0.9276 0.6392 5.0939 5.0939 4.7961 0.4246 0.2432 0.0574 41.1539 0.0367 0.0309 0.2456 0.2021 0.0688 1.0302 0.6815 5.2989 5.2989 5.0776 0.4446 0.2509 0.0545 39.3052 0.0371 0.0316 0.2537 0.2014 0.0753 1.1328 0.7205 5.4776 5.4776 5.3218 0.4626 0.2564 0.0519 37.5824 0.0374 0.0318 0.2596 0.1998 0.0809 1.2353 0.7563 5.6301 5.6301 5.5275 0.4787 0.2600 0.0498 35.9552 0.0376 0.0315 0.2636 0.1973 0.0857 1.3379 0.7887 5.7563 5.7563 5.6954 0.4928 0.2617 0.0480 34.4013 0.0378 0.0310 0.2657 0.1940 0.0897 1.4405 0.8179 5.8563 5.8563 5.8256 0.5050 0.2615 0.0465 32.9040 0.0381 0.0303 0.2660 0.1901 0.0929 1.5431 0.8436 5.9300 5.9300 5.9230 0.5153 0.2597 0.0455 31.4508 0.0384 0.0295 0.2646 0.1858 0.0954 1.6457 0.8660 5.9775 5.9775 5.9888 0.5236 0.2563 0.0448 30.0316 0.0388 0.0287 0.2616 0.1811 0.0973 1.7483 0.8848 5.9987 5.9987 6.0211 0.5300 0.2513 0.0445 28.6389 0.0394 0.0281 0.2571 0.1763 0.0986 1.8509 0.9001 6.0000 6.0000 6.0283 0.5344 0.2448 0.0445 27.2909 0.0401 0.0277 0.2513 0.1715 0.0990 1.9534 0.9118 6.0000 6.0000 6.0321 0.5369 0.2370 0.0445 26.0514 0.0406 0.0274 0.2441 0.1667 0.0982 2.0560 0.9199 6.0000 6.0000 6.0338 0.5374 0.2281 0.0445 24.9126 0.0409 0.0272 0.2358 0.1619 0.0961 2.1586 0.9243 6.0000 6.0000 6.0336 0.5360 0.2180 0.0445 23.8636 0.0411 0.0271 0.2264 0.1570 0.0929 2.2612 0.9250 6.0000 6.0000 6.0318 0.5326 0.2070 0.0445 22.8948 0.0412 0.0271 0.2160 0.1519 0.0885 2.3638 0.9219 6.0000 6.0000 6.0302 0.5273 0.1952 0.0445 21.9978 0.0410 0.0269 0.2047 0.1465 0.0832 2.4664 0.9150 6.0000 6.0000 6.0289 0.5201 0.1826 0.0445 21.1653 0.0407 0.0264 0.1927 0.1409 0.0771 2.5690 0.9042 6.0000 6.0000 6.0279 0.5109 0.1695 0.0445 20.3910 0.0402 0.0258 0.1799 0.1351 0.0703 2.6716 0.8895 6.0000 6.0000 6.0272 0.4997 0.1558 0.0445 19.6691 0.0396 0.0249 0.1666 0.1290 0.0629 2.7741 0.8709 6.0000 6.0000 6.0269 0.4866 0.1417 0.0445 18.9948 0.0388 0.0239 0.1528 0.1227 0.0551 2.8767 0.8482 6.0000 6.0000 6.0271 0.4716 0.1273 0.0445 18.3636 0.0377 0.0227 0.1386 0.1162 0.0468 2.9793 0.8215 6.0000 6.0000 6.0276 0.4546 0.1127 0.0445 17.7717 0.0366 0.0213 0.1242 0.1094 0.0382 3.0819 0.7907 6.0000 6.0000 6.0285 0.4357 0.0980 0.0445 17.2157 0.0352 0.0197 0.1095 0.1024 0.0295 3.1845 0.7557 6.0000 6.0000 6.0301 0.4149 0.0834 0.0445 16.6924 0.0336 0.0181 0.0948 0.0952 0.0206 3.2871 0.7165 6.0000 6.0000 6.0326 0.3921 0.0688 0.0445 16.1992 0.0319 0.0163 0.0801 0.0879 0.0117 3.3897 0.6731 6.0000 6.0000 6.0364 0.3673 0.0545 0.0445 15.7335 0.0300 0.0144 0.0655 0.0804 0.0030 3.4922 0.6254 6.0000 6.0000 6.0414 0.3406 0.0406 0.0445 15.2933 0.0278 0.0125 0.0511 0.0727 -0.0055 3.5948 0.5734 6.0000 6.0000 6.0482 0.3120 0.0271 0.0445 14.8765 0.0255 0.0106 0.0371 0.0648 -0.0138 3.6974 0.5169 6.0000 6.0000 6.0581 0.2814 0.0142 0.0445 14.4813 0.0230 0.0087 0.0234 0.0569 -0.0215 3.7957 0.4542 6.0000 6.0000 6.0711 0.2459 0.0013 0.0445 14.1215 0.0202 0.0068 0.0097 0.0469 -0.0292 3.8202 0.4329 6.0000 6.0000 6.0755 0.2319 -0.0030 0.0445 14.0345 0.0193 0.0062 0.0051 0.0417 -0.0319 3.8404 0.4128 6.0000 6.0000 6.0791 0.2180 -0.0071 0.0445 13.9636 0.0184 0.0056 0.0006 0.0362 -0.0346 3.8606 0.3899 6.0000 6.0000 6.0829 0.2015 -0.0117 0.0445 13.8934 0.0174 0.0050 -0.0044 0.0293 -0.0376 3.8808 0.3637 6.0000 6.0000 6.0870 0.1818 -0.0171 0.0445 13.8238 0.0162 0.0044 -0.0102 0.0208 -0.0411 3.9010 0.3332 6.0000 6.0000 6.1003 0.1580 -0.0233 0.0445 13.7550 0.0148 0.0037 -0.0170 0.0099 -0.0453 3.9212 0.2963 6.0000 6.0000 6.1239 0.1283 -0.0310 0.0445 13.6868 0.0132 0.0030 -0.0253 -0.0044 -0.0506 3.9414 0.2488 6.0000 6.0000 6.1655 0.0881 -0.0410 0.0445 13.6192 0.0111 0.0021 -0.0362 -0.0244 -0.0577 3.9616 0.1758 6.0000 6.0000 6.2740 0.0233 -0.0569 0.0445 13.5524 0.0078 0.0011 -0.0535 -0.0579 -0.0690 3.9818 0.0918 6.0000 6.0000 6.6158 -0.0521 -0.0750 0.0445 13.4861 0.0041 0.0003 -0.0733 -0.0970 -0.0821 4.0000 0.0162 6.0000 6.0030 6.0030 -0.1199 -0.0912 0.0445 13.4336 0.0007 0.0000 -0.0913 0.0000 0.0000 RADIUS: 4.00 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.75 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.014543 TOTAL WEIGHT (Kg) = 0.006595 TOTAL VOLUME (IN**3) = 0.236920 TOTAL PROJECTED AREA (IN**2) = 5.0120 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000119 MOMENT OF INERTIA (Kg-M**2) = 0.000013 STATIC MOMENT, ONE SIDE (IN-LB) = 0.010306 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 = 130.259 INNER LIMIT (NORMALIZED BY RADIUS) = 0.062 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 7101.88 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.