11x7 (11x7.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 1.5763 0.0000 0.0000 0.5000 0.0000 0.3622 0.0000 0.3622 0.0000 0.2500 0.0000 0.0000 0.1400 0.9587 2.1667 0.0158 -0.3517 0.4934 0.0096 0.3474 1.0261 0.3330 0.3659 0.2548 0.0152 0.0239 0.2800 0.9207 2.7231 0.1213 -0.6685 0.4877 0.0355 0.3331 3.9432 0.3067 0.3603 0.2676 0.0299 0.0280 0.4200 0.8905 3.2456 0.3901 -0.8399 0.4832 0.0733 0.3194 8.4083 0.2844 0.3477 0.2854 0.0452 0.0355 0.5600 0.8722 3.7339 0.8737 -0.7709 0.4798 0.1187 0.3063 13.9445 0.2671 0.3292 0.3064 0.0606 0.0459 0.7000 0.8678 4.1883 1.5933 -0.4023 0.4779 0.1676 0.2937 19.9137 0.2549 0.3071 0.3289 0.0759 0.0586 0.8400 0.8761 4.6087 2.5305 0.2789 0.4774 0.2161 0.2817 25.6157 0.2468 0.2830 0.3511 0.0905 0.0727 0.9800 0.8926 4.9950 3.6178 1.2268 0.4787 0.2600 0.2703 30.4363 0.2413 0.2585 0.3711 0.1044 0.0876 1.1200 0.9103 5.3474 4.7336 2.3269 0.4817 0.2952 0.2595 33.9271 0.2362 0.2348 0.3864 0.1170 0.1021 1.2600 0.9219 5.6657 5.7033 3.3939 0.4867 0.3177 0.2493 35.7690 0.2298 0.2126 0.3946 0.1280 0.1149 1.4000 0.9212 5.9500 6.3106 4.1808 0.4938 0.3234 0.2396 35.6556 0.2207 0.1928 0.3926 0.1371 0.1246 1.5393 0.9128 6.1991 6.5843 4.6661 0.5025 0.3169 0.2306 34.2458 0.2104 0.1758 0.3833 0.1445 0.1306 1.6671 0.9077 6.3979 6.8013 5.0810 0.5111 0.3103 0.2228 32.9964 0.2022 0.1628 0.3744 0.1511 0.1340 1.7941 0.9050 6.5676 6.9876 5.4617 0.5200 0.3031 0.2155 31.7930 0.1950 0.1519 0.3653 0.1574 0.1359 1.9212 0.9041 6.7093 7.1446 5.8055 0.5290 0.2953 0.2087 30.6200 0.1887 0.1426 0.3559 0.1633 0.1364 2.0483 0.9049 6.8229 7.2726 6.1079 0.5380 0.2870 0.2023 29.4707 0.1831 0.1348 0.3463 0.1688 0.1357 2.1753 0.9069 6.9085 7.3718 6.3653 0.5468 0.2781 0.1965 28.3400 0.1782 0.1283 0.3365 0.1738 0.1340 2.3024 0.9097 6.9661 7.4424 6.5744 0.5552 0.2686 0.1911 27.2240 0.1738 0.1228 0.3264 0.1781 0.1314 2.4295 0.9130 6.9957 7.4846 6.7327 0.5629 0.2587 0.1862 26.1195 0.1700 0.1183 0.3160 0.1819 0.1281 2.5566 0.9164 7.0000 7.5015 6.8412 0.5698 0.2482 0.1818 25.0323 0.1666 0.1146 0.3053 0.1850 0.1240 2.6836 0.9196 7.0000 7.5143 6.9193 0.5758 0.2374 0.1778 24.0197 0.1635 0.1115 0.2944 0.1875 0.1191 2.8107 0.9222 7.0000 7.5275 6.9712 0.5805 0.2262 0.1743 23.0859 0.1607 0.1091 0.2833 0.1895 0.1133 2.9378 0.9238 7.0000 7.5414 6.9970 0.5839 0.2147 0.1713 22.2230 0.1582 0.1072 0.2718 0.1907 0.1068 3.0648 0.9240 7.0000 7.5559 7.0000 0.5857 0.2029 0.1687 21.4239 0.1559 0.1055 0.2601 0.1912 0.0996 3.1919 0.9226 7.0000 7.5700 7.0001 0.5857 0.1910 0.1662 20.6792 0.1533 0.1036 0.2482 0.1907 0.0922 3.3190 0.9190 7.0000 7.5832 7.0002 0.5837 0.1790 0.1636 19.9832 0.1504 0.1012 0.2359 0.1893 0.0846 3.4460 0.9131 7.0000 7.5957 7.0002 0.5796 0.1670 0.1611 19.3311 0.1471 0.0983 0.2235 0.1869 0.0769 3.5731 0.9043 7.0000 7.6072 7.0002 0.5731 0.1550 0.1585 18.7186 0.1434 0.0949 0.2107 0.1834 0.0691 3.7002 0.8923 7.0000 7.6178 7.0002 0.5640 0.1430 0.1560 18.1420 0.1392 0.0910 0.1977 0.1789 0.0614 3.8272 0.8767 7.0000 7.6273 7.0001 0.5522 0.1310 0.1535 17.5979 0.1345 0.0864 0.1844 0.1732 0.0536 3.9543 0.8573 7.0000 7.6356 7.0001 0.5375 0.1190 0.1509 17.0834 0.1294 0.0813 0.1709 0.1663 0.0460 4.0814 0.8335 7.0000 7.6427 7.0001 0.5197 0.1071 0.1484 16.5956 0.1237 0.0756 0.1571 0.1582 0.0384 4.2084 0.8051 7.0000 7.6483 7.0001 0.4985 0.0952 0.1458 16.1321 0.1174 0.0693 0.1430 0.1488 0.0309 4.3355 0.7717 7.0000 7.6521 7.0001 0.4738 0.0833 0.1433 15.6904 0.1106 0.0626 0.1287 0.1381 0.0236 4.4626 0.7328 7.0000 7.6540 7.0001 0.4454 0.0715 0.1407 15.2682 0.1031 0.0555 0.1141 0.1261 0.0164 4.5897 0.6882 7.0000 7.6534 7.0000 0.4131 0.0597 0.1382 14.8634 0.0951 0.0481 0.0992 0.1127 0.0095 4.7167 0.6374 7.0000 7.6496 7.0000 0.3767 0.0480 0.1357 14.4732 0.0865 0.0406 0.0841 0.0979 0.0027 4.8438 0.5802 7.0000 7.6568 6.9861 0.3360 0.0366 0.1331 14.1216 0.0772 0.0331 0.0688 0.0817 -0.0040 4.9709 0.5164 7.0000 7.7266 6.9376 0.2908 0.0263 0.1306 13.8953 0.0674 0.0257 0.0535 0.0639 -0.0104 5.0979 0.4455 7.0000 7.8851 6.8831 0.2409 0.0169 0.1280 13.8295 0.0570 0.0188 0.0385 0.0447 -0.0165 5.2198 0.3703 7.0000 8.1360 6.8534 0.1885 0.0083 0.1256 13.9322 0.0465 0.0128 0.0242 0.0248 -0.0219 5.2528 0.3488 7.0000 8.2209 6.8526 0.1735 0.0059 0.1249 13.9870 0.0436 0.0113 0.0204 0.0192 -0.0232 5.2806 0.3302 7.0000 8.2977 6.8550 0.1606 0.0038 0.1244 14.0411 0.0411 0.0101 0.0171 0.0143 -0.0244 5.3083 0.3112 7.0000 8.3787 6.8605 0.1475 0.0017 0.1238 14.1015 0.0385 0.0089 0.0138 0.0094 -0.0255 5.3361 0.2917 7.0000 8.4633 6.8694 0.1341 -0.0004 0.1233 14.1670 0.0360 0.0078 0.0105 0.0044 -0.0266 5.3639 0.2719 7.0000 8.5504 6.8819 0.1205 -0.0027 0.1227 14.2358 0.0334 0.0068 0.0071 -0.0006 -0.0277 5.3917 0.2499 7.0000 8.6389 6.8985 0.1049 -0.0055 0.1222 14.3060 0.0305 0.0057 0.0031 -0.0067 -0.0291 5.4194 0.2208 7.0000 8.7374 6.9381 0.0826 -0.0100 0.1216 14.3913 0.0269 0.0044 -0.0027 -0.0163 -0.0315 5.4472 0.1805 7.0000 8.8219 7.0668 0.0496 -0.0174 0.1211 14.4537 0.0218 0.0030 -0.0117 -0.0317 -0.0355 5.4750 0.1108 7.0000 8.8852 7.6141 -0.0115 -0.0323 0.1205 14.4823 0.0133 0.0011 -0.0289 -0.0624 -0.0439 5.5000 0.0083 7.0000 7.0000 7.0000 -0.1048 -0.0562 0.1200 11.4510 0.0010 0.0000 -0.0562 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) = 0.096297 TOTAL WEIGHT (Kg) = 0.043672 TOTAL VOLUME (IN**3) = 1.568807 TOTAL PROJECTED AREA (IN**2) = 8.2788 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001142 MOMENT OF INERTIA (Kg-M**2) = 0.000129 STATIC MOMENT, ONE SIDE (IN-LB) = 0.080510 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) = 21919.59 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.