17x8N (17x8N.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 8.0000 -0.5000 -0.5000 0.5750 0.0000 0.3572 0.0000 0.4108 0.0000 0.1200 0.0000 0.0000 0.2040 1.0921 8.0000 -0.4741 -1.5499 0.5703 0.0067 0.3447 -20.2982 0.3764 0.5373 0.1259 0.0188 -0.1540 0.4080 1.0434 8.0000 -0.3001 -2.5166 0.5753 0.0246 0.3326 -6.6762 0.3470 0.5241 0.1415 0.0502 -0.1504 0.6120 1.0092 8.0000 0.1424 -3.1591 0.5880 0.0506 0.3208 2.1209 0.3238 0.5046 0.1637 0.0871 -0.1439 0.8160 0.9946 8.0000 0.9316 -3.2810 0.6065 0.0817 0.3095 10.2987 0.3078 0.4804 0.1903 0.1270 -0.1342 1.0200 1.0013 8.0000 2.0863 -2.7671 0.6290 0.1151 0.2986 18.0322 0.2990 0.4534 0.2192 0.1674 -0.1215 1.2240 1.0259 8.0000 3.5498 -1.6115 0.6536 0.1478 0.2880 24.7767 0.2955 0.4250 0.2480 0.2061 -0.1059 1.4280 1.0605 8.0000 5.1806 0.0605 0.6786 0.1769 0.2779 30.0016 0.2947 0.3961 0.2740 0.2408 -0.0879 1.6320 1.0951 8.0000 6.7556 1.9857 0.7019 0.1995 0.2682 33.3775 0.2937 0.3672 0.2943 0.2693 -0.0681 1.8360 1.1201 8.0000 7.9880 3.7802 0.7218 0.2128 0.2589 34.7004 0.2900 0.3386 0.3060 0.2893 -0.0476 2.0400 1.1282 8.0000 8.5588 4.9789 0.7365 0.2138 0.2500 33.7324 0.2820 0.3099 0.3064 0.2984 -0.0279 2.2438 1.1254 8.0000 8.5971 5.5829 0.7475 0.2064 0.2415 31.3744 0.2718 0.2827 0.2987 0.3005 -0.0109 2.4451 1.1244 8.0000 8.6276 6.1080 0.7589 0.1990 0.2335 29.3182 0.2625 0.2600 0.2910 0.3042 0.0023 2.6461 1.1251 8.0000 8.6560 6.5678 0.7707 0.1917 0.2259 27.5027 0.2542 0.2410 0.2832 0.3090 0.0125 2.8472 1.1271 8.0000 8.6826 6.9630 0.7825 0.1843 0.2187 25.8893 0.2465 0.2253 0.2753 0.3146 0.0201 3.0483 1.1301 8.0000 8.7075 7.2942 0.7943 0.1770 0.2119 24.4480 0.2395 0.2123 0.2673 0.3207 0.0255 3.2493 1.1337 8.0000 8.7310 7.5615 0.8058 0.1696 0.2055 23.1540 0.2330 0.2016 0.2591 0.3270 0.0289 3.4504 1.1376 8.0000 8.7534 7.7653 0.8168 0.1621 0.1995 21.9869 0.2269 0.1930 0.2508 0.3335 0.0307 3.6515 1.1415 8.0000 8.7747 7.9058 0.8270 0.1545 0.1938 20.9298 0.2212 0.1862 0.2424 0.3398 0.0310 3.8526 1.1449 8.0000 8.7954 7.9833 0.8363 0.1467 0.1886 19.9687 0.2159 0.1808 0.2339 0.3458 0.0301 4.0536 1.1474 8.0000 8.8155 8.0000 0.8444 0.1389 0.1837 19.0917 0.2108 0.1766 0.2252 0.3515 0.0282 4.2547 1.1489 8.0000 8.8354 8.0001 0.8511 0.1310 0.1793 18.2890 0.2060 0.1727 0.2164 0.3564 0.0256 4.4558 1.1487 8.0000 8.8552 8.0001 0.8562 0.1229 0.1752 17.5521 0.2013 0.1687 0.2074 0.3606 0.0226 4.6568 1.1466 8.0000 8.8752 8.0002 0.8595 0.1147 0.1716 16.8738 0.1967 0.1646 0.1984 0.3639 0.0193 4.8579 1.1423 8.0000 8.8953 8.0002 0.8608 0.1064 0.1682 16.2476 0.1922 0.1602 0.1892 0.3663 0.0158 5.0590 1.1352 8.0000 8.9140 8.0001 0.8598 0.0983 0.1649 15.6653 0.1872 0.1551 0.1799 0.3677 0.0123 5.2600 1.1251 8.0000 8.9310 8.0001 0.8564 0.0904 0.1616 15.1218 0.1819 0.1493 0.1704 0.3680 0.0088 5.4611 1.1116 8.0000 8.9463 8.0001 0.8503 0.0827 0.1584 14.6131 0.1760 0.1428 0.1608 0.3673 0.0053 5.6622 1.0943 8.0000 8.9596 8.0000 0.8413 0.0752 0.1551 14.1355 0.1697 0.1355 0.1511 0.3653 0.0020 5.8632 1.0727 8.0000 8.9710 8.0000 0.8291 0.0680 0.1518 13.6860 0.1628 0.1275 0.1413 0.3620 -0.0011 6.0643 1.0467 8.0000 8.9803 8.0000 0.8137 0.0609 0.1485 13.2617 0.1554 0.1188 0.1313 0.3575 -0.0041 6.2654 1.0157 8.0000 8.9873 8.0000 0.7947 0.0540 0.1452 12.8601 0.1475 0.1095 0.1212 0.3516 -0.0069 6.4664 0.9794 8.0000 8.9918 8.0000 0.7719 0.0474 0.1419 12.4790 0.1390 0.0995 0.1109 0.3442 -0.0095 6.6675 0.9373 8.0000 8.9936 8.0000 0.7451 0.0410 0.1386 12.1163 0.1299 0.0891 0.1006 0.3354 -0.0118 6.8686 0.8893 8.0000 8.9922 8.0000 0.7142 0.0347 0.1353 11.7699 0.1203 0.0784 0.0900 0.3250 -0.0140 7.0697 0.8348 8.0000 8.9871 8.0000 0.6788 0.0286 0.1320 11.4378 0.1102 0.0674 0.0794 0.3131 -0.0158 7.2707 0.7734 8.0000 8.9776 8.0000 0.6389 0.0227 0.1288 11.1180 0.0996 0.0565 0.0686 0.2995 -0.0174 7.4718 0.7049 8.0000 8.9623 8.0000 0.5940 0.0169 0.1255 10.8080 0.0884 0.0458 0.0577 0.2841 -0.0188 7.6729 0.6288 8.0000 8.9393 8.0000 0.5441 0.0112 0.1222 10.5047 0.0768 0.0356 0.0467 0.2670 -0.0200 7.8739 0.5448 7.9672 8.8719 7.9673 0.4890 0.0056 0.1189 10.1666 0.0648 0.0261 0.0355 0.2481 -0.0208 8.0668 0.4564 7.7860 8.6396 7.7860 0.4309 0.0000 0.1157 9.6735 0.0528 0.0179 0.0247 0.2281 -0.0210 8.1179 0.4316 7.7113 8.5469 7.7113 0.4146 -0.0014 0.1149 9.5124 0.0496 0.0159 0.0218 0.2225 -0.0210 8.1609 0.4103 7.6399 8.4585 7.6400 0.4007 -0.0027 0.1142 9.3671 0.0469 0.0143 0.0193 0.2178 -0.0210 8.2038 0.3887 7.5608 8.3600 7.5608 0.3865 -0.0039 0.1135 9.2123 0.0441 0.0128 0.0169 0.2129 -0.0210 8.2467 0.3666 7.4737 8.2511 7.4738 0.3720 -0.0052 0.1128 9.0477 0.0413 0.0114 0.0144 0.2079 -0.0210 8.2896 0.3442 7.3788 8.1311 7.3789 0.3572 -0.0064 0.1121 8.8729 0.0386 0.0100 0.0120 0.2029 -0.0209 8.3326 0.3209 7.2761 7.9994 7.2762 0.3418 -0.0077 0.1114 8.6871 0.0357 0.0086 0.0094 0.1975 -0.0210 8.3755 0.2892 7.1654 7.8560 7.1722 0.3182 -0.0102 0.1107 8.4906 0.0320 0.0070 0.0052 0.1877 -0.0219 8.4184 0.2422 7.0470 7.6994 7.1118 0.2797 -0.0150 0.1100 8.2819 0.0266 0.0049 -0.0020 0.1698 -0.0246 8.4614 0.1607 6.9206 7.5274 7.2441 0.2071 -0.0246 0.1093 8.0588 0.0176 0.0022 -0.0160 0.1333 -0.0309 8.5000 0.0114 6.8002 6.8002 6.8002 0.0667 -0.0441 0.1086 7.2563 0.0012 0.0000 -0.0441 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) = 0.220863 TOTAL WEIGHT (Kg) = 0.100164 TOTAL VOLUME (IN**3) = 3.598136 TOTAL PROJECTED AREA (IN**2) = 15.7471 MOMENT OF INERTIA (SNAIL-IN**2) = 0.006205 MOMENT OF INERTIA (Kg-M**2) = 0.000701 STATIC MOMENT, ONE SIDE (IN-LB) = 0.285703 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) = 11805.02 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.04, 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.