17x10N (17x10N.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 1.1500 10.0000 -0.5000 -0.5000 0.5750 0.0000 0.3572 0.0000 0.4108 0.0000 0.1200 0.0000 0.0000 0.2040 1.0897 10.0000 -0.4715 -1.5765 0.5703 0.0091 0.3461 -20.1969 0.3772 0.5463 0.1281 0.0199 -0.1571 0.4080 1.0350 10.0000 -0.2785 -2.5808 0.5753 0.0337 0.3354 -6.1992 0.3471 0.5331 0.1499 0.0544 -0.1496 0.6120 0.9939 10.0000 0.2205 -3.2633 0.5880 0.0694 0.3249 3.2816 0.3229 0.5138 0.1812 0.0952 -0.1366 0.8160 0.9740 10.0000 1.1294 -3.4031 0.6065 0.1122 0.3148 12.4225 0.3066 0.4897 0.2189 0.1392 -0.1191 1.0200 0.9788 10.0000 2.4919 -2.8471 0.6290 0.1582 0.3049 21.2471 0.2985 0.4628 0.2597 0.1839 -0.0980 1.2240 1.0054 10.0000 4.2625 -1.5501 0.6536 0.2036 0.2954 28.9972 0.2970 0.4348 0.3003 0.2262 -0.0746 1.4280 1.0447 10.0000 6.2808 0.3796 0.6786 0.2443 0.2862 34.9928 0.2990 0.4068 0.3370 0.2636 -0.0500 1.6320 1.0849 10.0000 8.2632 2.6513 0.7019 0.2764 0.2773 38.8630 0.3009 0.3795 0.3661 0.2935 -0.0254 1.8360 1.1144 10.0000 9.8254 4.8007 0.7218 0.2961 0.2687 40.4218 0.2995 0.3529 0.3838 0.3132 -0.0023 2.0400 1.1247 10.0000 10.5447 6.2538 0.7365 0.2993 0.2605 39.4429 0.2930 0.3258 0.3863 0.3203 0.0181 2.2438 1.1225 10.0000 10.5889 7.0020 0.7475 0.2910 0.2525 36.9090 0.2835 0.2990 0.3781 0.3198 0.0346 2.4451 1.1221 10.0000 10.6235 7.6529 0.7589 0.2826 0.2450 34.6641 0.2749 0.2762 0.3697 0.3211 0.0476 2.6461 1.1231 10.0000 10.6556 8.2230 0.7707 0.2740 0.2378 32.6555 0.2671 0.2568 0.3611 0.3237 0.0577 2.8472 1.1255 10.0000 10.6857 8.7132 0.7825 0.2654 0.2309 30.8504 0.2599 0.2405 0.3523 0.3273 0.0651 3.0483 1.1287 10.0000 10.7139 9.1240 0.7943 0.2566 0.2243 29.2221 0.2532 0.2269 0.3433 0.3317 0.0703 3.2493 1.1325 10.0000 10.7406 9.4557 0.8058 0.2477 0.2180 27.7479 0.2469 0.2156 0.3340 0.3366 0.0734 3.4504 1.1366 10.0000 10.7659 9.7086 0.8168 0.2386 0.2120 26.4085 0.2410 0.2065 0.3245 0.3418 0.0748 3.6515 1.1406 10.0000 10.7899 9.8830 0.8270 0.2293 0.2063 25.1873 0.2353 0.1992 0.3147 0.3470 0.0745 3.8526 1.1441 10.0000 10.8130 9.9793 0.8363 0.2199 0.2009 24.0703 0.2299 0.1935 0.3047 0.3522 0.0729 4.0536 1.1468 10.0000 10.8351 10.0000 0.8444 0.2103 0.1958 23.0455 0.2246 0.1890 0.2944 0.3572 0.0701 4.2547 1.1483 10.0000 10.8565 10.0002 0.8511 0.2005 0.1911 22.1025 0.2194 0.1848 0.2838 0.3616 0.0665 4.4558 1.1482 10.0000 10.8774 10.0004 0.8562 0.1906 0.1866 21.2325 0.2143 0.1804 0.2730 0.3653 0.0626 4.6568 1.1462 10.0000 10.8978 10.0005 0.8595 0.1804 0.1824 20.4279 0.2091 0.1756 0.2619 0.3682 0.0582 4.8579 1.1419 10.0000 10.9180 10.0005 0.8608 0.1701 0.1786 19.6819 0.2039 0.1706 0.2506 0.3701 0.0535 5.0590 1.1349 10.0000 10.9381 10.0004 0.8598 0.1597 0.1750 18.9889 0.1987 0.1651 0.2390 0.3712 0.0486 5.2600 1.1248 10.0000 10.9582 10.0004 0.8564 0.1491 0.1718 18.3438 0.1932 0.1592 0.2272 0.3711 0.0434 5.4611 1.1113 10.0000 10.9784 10.0003 0.8503 0.1384 0.1688 17.7420 0.1876 0.1527 0.2151 0.3700 0.0381 5.6622 1.0940 10.0000 10.9974 10.0003 0.8413 0.1277 0.1659 17.1774 0.1815 0.1454 0.2027 0.3677 0.0328 5.8632 1.0726 10.0000 11.0146 10.0003 0.8291 0.1171 0.1630 16.6460 0.1749 0.1373 0.1900 0.3643 0.0275 6.0643 1.0465 10.0000 11.0300 10.0002 0.8137 0.1066 0.1601 16.1446 0.1676 0.1284 0.1771 0.3595 0.0223 6.2654 1.0155 10.0000 11.0435 10.0002 0.7947 0.0962 0.1572 15.6704 0.1597 0.1188 0.1640 0.3534 0.0172 6.4664 0.9792 10.0000 11.0547 10.0001 0.7719 0.0860 0.1543 15.2207 0.1511 0.1084 0.1505 0.3459 0.0123 6.6675 0.9373 10.0000 11.0634 10.0001 0.7451 0.0758 0.1514 14.7933 0.1419 0.0975 0.1368 0.3369 0.0076 6.8686 0.8892 10.0000 11.0693 10.0001 0.7142 0.0658 0.1485 14.3858 0.1321 0.0861 0.1229 0.3264 0.0030 7.0697 0.8347 10.0000 11.0719 10.0001 0.6788 0.0559 0.1456 13.9961 0.1215 0.0745 0.1087 0.3143 -0.0014 7.2707 0.7734 10.0000 11.0704 10.0001 0.6389 0.0460 0.1427 13.6218 0.1104 0.0627 0.0942 0.3006 -0.0056 7.4718 0.7049 10.0000 11.0635 10.0000 0.5940 0.0363 0.1398 13.2604 0.0985 0.0511 0.0794 0.2852 -0.0095 7.6729 0.6288 10.0000 11.0493 10.0000 0.5441 0.0266 0.1369 12.9088 0.0861 0.0399 0.0644 0.2681 -0.0133 7.8739 0.5447 9.9590 10.9833 9.9591 0.4890 0.0169 0.1340 12.5169 0.0730 0.0294 0.0491 0.2491 -0.0167 8.0668 0.4563 9.7324 10.7157 9.7325 0.4309 0.0075 0.1312 11.9376 0.0599 0.0203 0.0342 0.2291 -0.0193 8.1179 0.4315 9.6390 10.6071 9.6390 0.4146 0.0049 0.1305 11.7476 0.0563 0.0181 0.0302 0.2235 -0.0199 8.1609 0.4103 9.5498 10.5034 9.5498 0.4007 0.0028 0.1299 11.5763 0.0533 0.0163 0.0268 0.2187 -0.0204 8.2038 0.3887 9.4508 10.3877 9.4508 0.3865 0.0007 0.1292 11.3939 0.0502 0.0146 0.0235 0.2138 -0.0209 8.2467 0.3666 9.3420 10.2598 9.3420 0.3720 -0.0014 0.1286 11.2000 0.0472 0.0129 0.0201 0.2088 -0.0215 8.2896 0.3442 9.2233 10.1190 9.2234 0.3572 -0.0035 0.1280 10.9943 0.0441 0.0113 0.0167 0.2037 -0.0220 8.3326 0.3209 9.0948 9.9648 9.0949 0.3418 -0.0057 0.1274 10.7763 0.0409 0.0098 0.0132 0.1984 -0.0225 8.3755 0.2894 8.9565 9.7974 8.9585 0.3185 -0.0094 0.1268 10.5463 0.0367 0.0080 0.0077 0.1888 -0.0242 8.4184 0.2426 8.8084 9.6154 8.8696 0.2802 -0.0158 0.1261 10.3030 0.0306 0.0056 -0.0014 0.1710 -0.0279 8.4614 0.1612 8.6504 9.4168 8.9734 0.2081 -0.0282 0.1255 10.0444 0.0202 0.0025 -0.0186 0.1347 -0.0362 8.5000 0.0114 8.4998 8.4998 8.4998 0.0679 -0.0528 0.1250 9.0429 0.0014 0.0000 -0.0528 0.0000 0.0000 RADIUS: 8.50 PROPELLER RADIUS (IN) HUBRAD: 0.57 HUB RADIUS (IN) HUBTRA: 2.04 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.231405 TOTAL WEIGHT (Kg) = 0.104946 TOTAL VOLUME (IN**3) = 3.769886 TOTAL PROJECTED AREA (IN**2) = 15.2792 MOMENT OF INERTIA (SNAIL-IN**2) = 0.006689 MOMENT OF INERTIA (Kg-M**2) = 0.000755 STATIC MOMENT, ONE SIDE (IN-LB) = 0.305030 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 = 71.472 INNER LIMIT (NORMALIZED BY RADIUS) = 0.068 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 12260.24 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.10, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 3.10, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.