11x8 (11x8.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 1.0000 1.8019 0.0000 0.0000 0.5000 0.0000 0.3622 0.0000 0.3622 0.0000 0.2250 0.0000 0.0000 0.1400 0.9575 2.4766 0.0169 -0.4408 0.4934 0.0101 0.3474 1.1020 0.3326 0.3856 0.2308 0.0142 -0.0091 0.2800 0.9168 3.1125 0.1307 -0.8425 0.4877 0.0374 0.3331 4.2498 0.3054 0.3782 0.2463 0.0304 -0.0030 0.4200 0.8832 3.7095 0.4229 -1.0782 0.4832 0.0770 0.3194 9.1053 0.2821 0.3631 0.2681 0.0477 0.0077 0.5600 0.8623 4.2676 0.9543 -1.0351 0.4798 0.1248 0.3063 15.1745 0.2641 0.3417 0.2940 0.0655 0.0221 0.7000 0.8569 4.7869 1.7552 -0.6370 0.4779 0.1763 0.2937 21.7553 0.2517 0.3166 0.3218 0.0832 0.0392 0.8400 0.8661 5.2673 2.8124 0.1412 0.4774 0.2273 0.2817 28.0517 0.2440 0.2898 0.3494 0.1001 0.0577 0.9800 0.8848 5.7088 4.0548 1.2533 0.4787 0.2735 0.2703 33.3656 0.2392 0.2631 0.3742 0.1159 0.0766 1.1200 0.9054 6.1114 5.3428 2.5640 0.4817 0.3106 0.2595 37.2068 0.2350 0.2378 0.3937 0.1298 0.0943 1.2600 0.9195 6.4752 6.4678 3.8417 0.4867 0.3344 0.2493 39.2478 0.2292 0.2148 0.4047 0.1414 0.1093 1.4000 0.9199 6.8000 7.1693 4.7724 0.4938 0.3404 0.2396 39.1807 0.2204 0.1946 0.4038 0.1501 0.1199 1.5393 0.9117 7.0848 7.4798 5.3280 0.5025 0.3338 0.2306 37.7168 0.2102 0.1775 0.3945 0.1566 0.1260 1.6671 0.9068 7.3120 7.7256 5.8027 0.5111 0.3271 0.2228 36.4112 0.2020 0.1644 0.3855 0.1625 0.1296 1.7941 0.9041 7.5059 7.9364 6.2384 0.5200 0.3197 0.2155 35.1466 0.1948 0.1532 0.3764 0.1681 0.1317 1.9212 0.9034 7.6678 8.1139 6.6318 0.5290 0.3118 0.2087 33.9074 0.1885 0.1438 0.3671 0.1734 0.1323 2.0483 0.9043 7.7976 8.2581 6.9780 0.5380 0.3034 0.2023 32.6870 0.1830 0.1358 0.3574 0.1782 0.1319 2.1753 0.9063 7.8955 8.3693 7.2727 0.5468 0.2944 0.1965 31.4802 0.1781 0.1290 0.3476 0.1825 0.1304 2.3024 0.9092 7.9613 8.4479 7.5121 0.5552 0.2849 0.1911 30.2833 0.1738 0.1234 0.3374 0.1863 0.1281 2.4295 0.9126 7.9951 8.4939 7.6936 0.5629 0.2749 0.1862 29.0930 0.1699 0.1187 0.3270 0.1894 0.1250 2.5566 0.9161 8.0000 8.5109 7.8179 0.5698 0.2644 0.1818 27.9162 0.1665 0.1148 0.3164 0.1919 0.1214 2.6836 0.9193 8.0000 8.5232 7.9074 0.5758 0.2535 0.1778 26.8155 0.1634 0.1117 0.3055 0.1939 0.1168 2.8107 0.9219 8.0000 8.5360 7.9669 0.5805 0.2423 0.1743 25.7967 0.1607 0.1092 0.2943 0.1953 0.1114 2.9378 0.9235 8.0000 8.5494 7.9965 0.5839 0.2307 0.1713 24.8521 0.1582 0.1072 0.2829 0.1961 0.1052 3.0648 0.9238 8.0000 8.5635 8.0000 0.5857 0.2189 0.1687 23.9746 0.1558 0.1055 0.2712 0.1962 0.0985 3.1919 0.9224 8.0000 8.5771 8.0002 0.5857 0.2069 0.1662 23.1550 0.1533 0.1036 0.2592 0.1954 0.0914 3.3190 0.9189 8.0000 8.5899 8.0003 0.5837 0.1948 0.1636 22.3874 0.1503 0.1012 0.2470 0.1937 0.0842 3.4460 0.9129 8.0000 8.6020 8.0003 0.5796 0.1828 0.1611 21.6670 0.1470 0.0983 0.2345 0.1909 0.0770 3.5731 0.9041 8.0000 8.6132 8.0003 0.5731 0.1706 0.1585 20.9894 0.1433 0.0949 0.2217 0.1872 0.0696 3.7002 0.8922 8.0000 8.6234 8.0002 0.5640 0.1585 0.1560 20.3507 0.1392 0.0909 0.2087 0.1823 0.0623 3.8272 0.8766 8.0000 8.6326 8.0002 0.5522 0.1464 0.1535 19.7473 0.1345 0.0864 0.1954 0.1764 0.0550 3.9543 0.8572 8.0000 8.6406 8.0002 0.5375 0.1342 0.1509 19.1762 0.1294 0.0813 0.1819 0.1692 0.0478 4.0814 0.8334 8.0000 8.6474 8.0002 0.5197 0.1221 0.1484 18.6345 0.1237 0.0755 0.1681 0.1609 0.0407 4.2084 0.8050 8.0000 8.6526 8.0001 0.4985 0.1100 0.1458 18.1193 0.1174 0.0693 0.1540 0.1513 0.0338 4.3355 0.7716 8.0000 8.6562 8.0001 0.4738 0.0979 0.1433 17.6284 0.1106 0.0626 0.1397 0.1403 0.0270 4.4626 0.7328 8.0000 8.6577 8.0001 0.4454 0.0858 0.1407 17.1592 0.1031 0.0555 0.1251 0.1281 0.0204 4.5897 0.6881 8.0000 8.6568 8.0001 0.4131 0.0738 0.1382 16.7093 0.0951 0.0481 0.1102 0.1145 0.0140 4.7167 0.6374 8.0000 8.6527 8.0001 0.3767 0.0618 0.1357 16.2760 0.0865 0.0406 0.0951 0.0995 0.0078 4.8438 0.5802 8.0000 8.6598 7.9858 0.3360 0.0501 0.1331 15.8832 0.0772 0.0331 0.0798 0.0830 0.0018 4.9709 0.5164 8.0000 8.7309 7.9364 0.2908 0.0395 0.1306 15.6179 0.0674 0.0257 0.0646 0.0651 -0.0040 5.0979 0.4455 8.0000 8.8921 7.8810 0.2409 0.0298 0.1280 15.5151 0.0570 0.0188 0.0497 0.0456 -0.0094 5.2198 0.3705 8.0000 9.1473 7.8508 0.1885 0.0208 0.1256 15.5841 0.0465 0.0128 0.0355 0.0255 -0.0140 5.2528 0.3490 8.0000 9.2335 7.8500 0.1735 0.0184 0.1249 15.6299 0.0436 0.0113 0.0317 0.0199 -0.0152 5.2806 0.3304 8.0000 9.3115 7.8525 0.1606 0.0162 0.1244 15.6765 0.0411 0.0101 0.0285 0.0150 -0.0162 5.3083 0.3114 8.0000 9.3937 7.8581 0.1475 0.0140 0.1238 15.7295 0.0386 0.0089 0.0252 0.0100 -0.0172 5.3361 0.2920 8.0000 9.4796 7.8672 0.1341 0.0118 0.1233 15.7877 0.0360 0.0078 0.0219 0.0050 -0.0181 5.3639 0.2721 8.0000 9.5681 7.8800 0.1205 0.0094 0.1227 15.8492 0.0334 0.0068 0.0185 -0.0001 -0.0190 5.3917 0.2502 8.0000 9.6577 7.8968 0.1050 0.0065 0.1222 15.9120 0.0306 0.0057 0.0145 -0.0061 -0.0203 5.4194 0.2212 8.0000 9.7468 7.9338 0.0829 0.0017 0.1216 15.9731 0.0269 0.0045 0.0085 -0.0157 -0.0226 5.4472 0.1810 8.0000 9.8316 8.0622 0.0501 -0.0063 0.1211 16.0271 0.0219 0.0030 -0.0010 -0.0310 -0.0267 5.4750 0.1114 8.0000 9.9072 8.6130 -0.0106 -0.0225 0.1205 16.0663 0.0134 0.0011 -0.0193 -0.0614 -0.0355 5.5000 0.0083 8.0000 8.0000 8.0000 -0.1039 -0.0489 0.1200 13.0343 0.0010 0.0000 -0.0489 0.0000 0.0000 RADIUS: 5.50 PROPELLER RADIUS (IN) HUBRAD: 0.50 HUB RADIUS (IN) HUBTRA: 1.40 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.098198 TOTAL WEIGHT (Kg) = 0.044534 TOTAL VOLUME (IN**3) = 1.599772 TOTAL PROJECTED AREA (IN**2) = 8.1027 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001145 MOMENT OF INERTIA (Kg-M**2) = 0.000129 STATIC MOMENT, ONE SIDE (IN-LB) = 0.081042 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 = 90.324 INNER LIMIT (NORMALIZED BY RADIUS) = 0.091 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 22276.47 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.00, 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.