17x10 (17x10.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 1.2500 -1.5659 0.0000 0.0000 0.6250 0.0000 0.4220 0.0000 0.5275 0.0000 0.1600 0.0000 0.0000 0.2040 1.1936 -0.1330 0.0233 -0.9918 0.6191 0.0090 0.3962 1.0430 0.4729 0.6415 0.1675 0.0172 -0.1405 0.4080 1.1487 1.2051 0.1800 -1.8886 0.6210 0.0329 0.3717 4.0167 0.4270 0.6249 0.1870 0.0436 -0.1315 0.6120 1.1196 2.4485 0.5784 -2.4590 0.6293 0.0676 0.3485 8.5546 0.3901 0.6009 0.2143 0.0736 -0.1179 0.8160 1.1104 3.5972 1.2879 -2.5274 0.6428 0.1088 0.3264 14.1008 0.3624 0.5718 0.2466 0.1055 -0.1011 1.0200 1.1225 4.6511 2.3263 -2.0022 0.6602 0.1527 0.3056 19.9502 0.3430 0.5397 0.2808 0.1381 -0.0823 1.2240 1.1530 5.6104 3.6517 -0.8929 0.6804 0.1952 0.2860 25.3997 0.3298 0.5062 0.3135 0.1699 -0.0629 1.4280 1.1951 6.4749 5.1600 0.6805 0.7021 0.2324 0.2677 29.9029 0.3199 0.4724 0.3413 0.1997 -0.0447 1.6320 1.2397 7.2447 6.6890 2.4906 0.7241 0.2601 0.2505 33.1174 0.3106 0.4392 0.3603 0.2261 -0.0298 1.8360 1.2771 7.9198 8.0301 4.2180 0.7451 0.2745 0.2346 34.8416 0.2997 0.4074 0.3666 0.2475 -0.0209 2.0400 1.2992 8.5002 8.9427 5.4745 0.7639 0.2715 0.2200 34.9030 0.2858 0.3778 0.3563 0.2619 -0.0210 2.2438 1.3097 8.9855 9.4498 6.2481 0.7810 0.2560 0.2066 33.8334 0.2705 0.3507 0.3344 0.2708 -0.0280 2.4442 1.3204 9.3705 9.8493 6.9485 0.7981 0.2398 0.1946 32.6733 0.2569 0.3261 0.3129 0.2789 -0.0350 2.6445 1.3313 9.6638 10.1539 7.5754 0.8152 0.2227 0.1838 31.4288 0.2447 0.3035 0.2915 0.2863 -0.0419 2.8447 1.3421 9.8659 10.3648 8.1147 0.8320 0.2048 0.1741 30.1085 0.2337 0.2831 0.2702 0.2931 -0.0487 3.0450 1.3525 9.9767 10.4831 8.5533 0.8485 0.1861 0.1657 28.7195 0.2241 0.2648 0.2490 0.2992 -0.0554 3.2452 1.3622 10.0000 10.5137 8.8838 0.8642 0.1667 0.1585 27.2764 0.2159 0.2487 0.2279 0.3047 -0.0620 3.4455 1.3708 10.0000 10.5223 9.1562 0.8790 0.1468 0.1524 25.9219 0.2089 0.2349 0.2069 0.3103 -0.0695 3.6458 1.3780 10.0000 10.5333 9.3906 0.8926 0.1265 0.1475 24.6944 0.2033 0.2236 0.1860 0.3159 -0.0783 3.8460 1.3835 10.0000 10.5476 9.5869 0.9047 0.1058 0.1438 23.5802 0.1990 0.2145 0.1652 0.3214 -0.0882 4.0462 1.3871 10.0000 10.5659 9.7452 0.9153 0.0845 0.1413 22.5678 0.1960 0.2077 0.1445 0.3267 -0.0991 4.2465 1.3883 10.0000 10.5892 9.8654 0.9239 0.0626 0.1400 21.6468 0.1944 0.2030 0.1238 0.3317 -0.1111 4.4468 1.3869 10.0000 10.6152 9.9475 0.9304 0.0406 0.1393 20.8034 0.1932 0.1994 0.1033 0.3362 -0.1237 4.6470 1.3826 10.0000 10.6411 9.9917 0.9345 0.0190 0.1386 20.0240 0.1916 0.1961 0.0829 0.3401 -0.1367 4.8472 1.3750 10.0000 10.6666 10.0000 0.9359 -0.0024 0.1379 19.3017 0.1896 0.1926 0.0625 0.3432 -0.1499 5.0475 1.3638 10.0000 10.6917 10.0001 0.9345 -0.0233 0.1372 18.6302 0.1871 0.1884 0.0422 0.3452 -0.1630 5.2477 1.3487 10.0000 10.7161 10.0002 0.9300 -0.0439 0.1365 18.0042 0.1841 0.1833 0.0221 0.3460 -0.1760 5.4480 1.3294 10.0000 10.7398 10.0002 0.9222 -0.0641 0.1358 17.4191 0.1805 0.1771 0.0020 0.3453 -0.1887 5.6483 1.3055 10.0000 10.7625 10.0002 0.9107 -0.0839 0.1351 16.8707 0.1763 0.1699 -0.0180 0.3432 -0.2011 5.8485 1.2767 10.0000 10.7842 10.0002 0.8955 -0.1032 0.1344 16.3554 0.1715 0.1616 -0.0379 0.3395 -0.2132 6.0487 1.2427 10.0000 10.8045 10.0002 0.8761 -0.1221 0.1337 15.8699 0.1661 0.1523 -0.0577 0.3341 -0.2249 6.2490 1.2031 10.0000 10.8233 10.0002 0.8525 -0.1405 0.1329 15.4113 0.1600 0.1421 -0.0774 0.3268 -0.2362 6.4493 1.1577 10.0000 10.8402 10.0001 0.8242 -0.1584 0.1322 14.9768 0.1531 0.1309 -0.0971 0.3176 -0.2470 6.6495 1.1061 10.0000 10.8547 10.0001 0.7912 -0.1757 0.1315 14.5638 0.1455 0.1190 -0.1166 0.3064 -0.2573 6.8498 1.0481 10.0000 10.8663 10.0001 0.7532 -0.1926 0.1308 14.1699 0.1371 0.1063 -0.1360 0.2930 -0.2671 7.0500 0.9831 10.0000 10.8739 10.0001 0.7099 -0.2089 0.1301 13.7923 0.1279 0.0932 -0.1554 0.2773 -0.2764 7.2503 0.9110 10.0000 10.8764 10.0001 0.6611 -0.2246 0.1294 13.4283 0.1179 0.0797 -0.1747 0.2592 -0.2851 7.4505 0.8315 9.9931 10.8647 9.9932 0.6065 -0.2397 0.1287 13.0664 0.1070 0.0662 -0.1939 0.2387 -0.2931 7.6508 0.7441 9.9094 10.7657 9.9095 0.5459 -0.2544 0.1280 12.6233 0.0952 0.0529 -0.2130 0.2156 -0.3003 7.8510 0.6487 9.7308 10.6099 9.7081 0.4790 -0.2680 0.1273 12.1384 0.0826 0.0401 -0.2318 0.1897 -0.3065 8.0430 0.5499 9.4705 10.6313 9.3695 0.4089 -0.2776 0.1266 11.8801 0.0696 0.0288 -0.2487 0.1623 -0.3117 8.0941 0.5224 9.3866 10.6772 9.2669 0.3892 -0.2797 0.1264 11.8569 0.0660 0.0260 -0.2529 0.1546 -0.3129 8.1369 0.4988 9.3115 10.7299 9.1794 0.3724 -0.2813 0.1263 11.8529 0.0630 0.0237 -0.2565 0.1480 -0.3138 8.1797 0.4749 9.2321 10.7959 9.0918 0.3552 -0.2829 0.1261 11.8631 0.0599 0.0215 -0.2599 0.1412 -0.3147 8.2225 0.4505 9.1484 10.8749 9.0053 0.3377 -0.2844 0.1260 11.8870 0.0568 0.0193 -0.2634 0.1344 -0.3156 8.2653 0.4247 9.0603 10.9665 8.9209 0.3189 -0.2862 0.1258 11.9240 0.0534 0.0172 -0.2671 0.1268 -0.3166 8.3081 0.3912 8.9678 11.0705 8.8461 0.2927 -0.2894 0.1257 11.9736 0.0492 0.0146 -0.2726 0.1153 -0.3185 8.3509 0.3465 8.8711 11.1847 8.8566 0.2557 -0.2950 0.1255 12.0333 0.0435 0.0115 -0.2807 0.0979 -0.3218 8.3937 0.2836 8.7700 11.3221 9.0275 0.2009 -0.3044 0.1254 12.1164 0.0356 0.0077 -0.2933 0.0709 -0.3273 8.4365 0.1685 8.6646 11.4487 10.1493 0.0953 -0.3250 0.1252 12.1875 0.0211 0.0028 -0.3187 0.0163 -0.3395 8.4750 0.0147 8.5660 8.5661 8.5659 -0.0485 -0.3553 0.1251 9.1387 0.0018 0.0000 -0.3553 0.0000 0.0000 RADIUS: 8.48 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 2.04 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.269070 TOTAL WEIGHT (Kg) = 0.122027 TOTAL VOLUME (IN**3) = 4.383497 TOTAL PROJECTED AREA (IN**2) = 18.2900 MOMENT OF INERTIA (SNAIL-IN**2) = 0.007856 MOMENT OF INERTIA (Kg-M**2) = 0.000887 STATIC MOMENT, ONE SIDE (IN-LB) = 0.355364 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 = 85.485 INNER LIMIT (NORMALIZED BY RADIUS) = 0.074 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 11531.23 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.05, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 3.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.