14x12 (14x12.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 -0.6405 0.0000 0.0000 0.5750 0.0000 0.4565 0.0000 0.5250 0.0000 0.1000 0.0000 0.0000 0.1650 1.0969 0.8846 0.0205 -0.7755 0.5686 0.0092 0.4549 1.1325 0.4990 0.4883 0.1099 0.0144 -0.1423 0.3300 1.0410 2.3117 0.1604 -1.5033 0.5658 0.0341 0.4499 4.4241 0.4683 0.4829 0.1366 0.0410 -0.1308 0.4950 0.9904 3.6408 0.5291 -1.9852 0.5660 0.0705 0.4416 9.6551 0.4373 0.4708 0.1757 0.0697 -0.1091 0.6600 0.9541 4.8718 1.2218 -2.0224 0.5688 0.1144 0.4299 16.4172 0.4102 0.4514 0.2227 0.0997 -0.0801 0.8250 0.9383 6.0049 2.3070 -1.4569 0.5738 0.1621 0.4150 23.9920 0.3894 0.4270 0.2731 0.1301 -0.0476 0.9900 0.9441 7.0399 3.8019 -0.2026 0.5808 0.2098 0.3967 31.4334 0.3745 0.3996 0.3225 0.1597 -0.0150 1.1550 0.9661 7.9770 5.6373 1.6987 0.5891 0.2535 0.3751 37.8403 0.3624 0.3714 0.3663 0.1871 0.0147 1.3200 0.9949 8.8160 7.6214 4.0126 0.5985 0.2895 0.3527 42.5807 0.3509 0.3442 0.4003 0.2105 0.0389 1.4850 1.0194 9.5570 9.4236 6.2713 0.6085 0.3140 0.3315 45.2845 0.3379 0.3189 0.4203 0.2287 0.0557 1.6500 1.0303 10.2000 10.6121 7.8106 0.6187 0.3231 0.3115 45.6687 0.3210 0.2956 0.4223 0.2406 0.0633 1.8151 1.0314 10.7453 11.1998 8.5772 0.6293 0.3212 0.2928 44.4811 0.3020 0.2741 0.4121 0.2487 0.0649 1.9817 1.0350 11.1961 11.6834 9.2693 0.6411 0.3186 0.2751 43.1770 0.2847 0.2551 0.4023 0.2564 0.0663 2.1484 1.0408 11.5472 12.0614 9.8752 0.6537 0.3154 0.2587 41.7807 0.2692 0.2385 0.3929 0.2633 0.0677 2.3152 1.0483 11.7982 12.3337 10.3841 0.6668 0.3117 0.2435 40.2936 0.2552 0.2238 0.3839 0.2693 0.0691 2.4819 1.0571 11.9491 12.5005 10.7867 0.6801 0.3073 0.2295 38.7161 0.2426 0.2108 0.3750 0.2745 0.0708 2.6486 1.0668 12.0000 12.5626 11.0752 0.6934 0.3021 0.2168 37.0486 0.2313 0.1993 0.3663 0.2788 0.0726 2.8153 1.0770 12.0000 12.5705 11.2895 0.7063 0.2964 0.2054 35.3986 0.2212 0.1891 0.3575 0.2825 0.0742 2.9821 1.0871 12.0000 12.5767 11.4755 0.7187 0.2901 0.1952 33.8705 0.2122 0.1802 0.3487 0.2860 0.0750 3.1488 1.0968 12.0000 12.5823 11.6333 0.7302 0.2832 0.1862 32.4550 0.2043 0.1726 0.3396 0.2892 0.0748 3.3155 1.1057 12.0000 12.5883 11.7630 0.7406 0.2755 0.1785 31.1437 0.1974 0.1660 0.3302 0.2919 0.0738 3.4822 1.1134 12.0000 12.5959 11.8645 0.7495 0.2670 0.1721 29.9286 0.1916 0.1606 0.3204 0.2941 0.0717 3.6490 1.1194 12.0000 12.6057 11.9378 0.7568 0.2574 0.1669 28.8028 0.1868 0.1562 0.3100 0.2956 0.0687 3.8157 1.1233 12.0000 12.6188 11.9830 0.7621 0.2467 0.1629 27.7595 0.1830 0.1528 0.2989 0.2964 0.0647 3.9824 1.1247 12.0000 12.6358 11.9999 0.7651 0.2347 0.1602 26.7929 0.1802 0.1502 0.2871 0.2963 0.0595 4.1491 1.1232 12.0000 12.6550 12.0001 0.7657 0.2216 0.1583 25.8933 0.1778 0.1479 0.2744 0.2953 0.0534 4.3159 1.1182 12.0000 12.6732 12.0004 0.7636 0.2078 0.1563 25.0489 0.1748 0.1446 0.2607 0.2931 0.0465 4.4826 1.1093 12.0000 12.6902 12.0005 0.7583 0.1931 0.1544 24.2548 0.1713 0.1405 0.2459 0.2898 0.0389 4.6493 1.0962 12.0000 12.7057 12.0005 0.7498 0.1776 0.1524 23.5063 0.1671 0.1355 0.2299 0.2851 0.0305 4.8160 1.0783 12.0000 12.7197 12.0005 0.7377 0.1610 0.1505 22.7993 0.1623 0.1294 0.2127 0.2791 0.0213 4.9828 1.0552 12.0000 12.7320 12.0005 0.7218 0.1433 0.1486 22.1302 0.1568 0.1223 0.1940 0.2715 0.0111 5.1495 1.0265 12.0000 12.7421 12.0004 0.7018 0.1245 0.1466 21.4955 0.1505 0.1143 0.1738 0.2624 0.0000 5.3162 0.9917 12.0000 12.7498 12.0004 0.6774 0.1044 0.1447 20.8918 0.1435 0.1053 0.1520 0.2517 -0.0122 5.4829 0.9504 12.0000 12.7545 12.0003 0.6484 0.0829 0.1427 20.3160 0.1356 0.0955 0.1285 0.2392 -0.0255 5.6497 0.9020 12.0000 12.7556 12.0003 0.6144 0.0600 0.1408 19.7651 0.1270 0.0850 0.1031 0.2249 -0.0399 5.8164 0.8462 12.0000 12.7520 12.0002 0.5753 0.0355 0.1388 19.2358 0.1175 0.0739 0.0758 0.2087 -0.0557 5.9831 0.7826 12.0000 12.7423 12.0002 0.5307 0.0093 0.1369 18.7243 0.1071 0.0624 0.0465 0.1905 -0.0728 6.1498 0.7106 11.9596 12.6833 11.9598 0.4805 -0.0187 0.1349 18.1718 0.0959 0.0509 0.0149 0.1702 -0.0911 6.3166 0.6298 11.8196 12.5116 11.8198 0.4243 -0.0487 0.1330 17.4973 0.0838 0.0396 -0.0188 0.1477 -0.1105 6.4833 0.5398 11.5796 12.2190 11.5797 0.3618 -0.0807 0.1310 16.6971 0.0707 0.0288 -0.0550 0.1229 -0.1314 6.6431 0.4444 11.2554 11.8100 11.2555 0.2959 -0.1134 0.1292 15.7984 0.0574 0.0194 -0.0920 0.0971 -0.1530 6.6854 0.4176 11.1545 11.6775 11.1546 0.2774 -0.1223 0.1287 15.5359 0.0537 0.0172 -0.1021 0.0900 -0.1590 6.7207 0.3948 11.0650 11.5572 11.0651 0.2616 -0.1299 0.1283 15.3064 0.0506 0.0153 -0.1107 0.0839 -0.1642 6.7561 0.3714 10.9711 11.4277 10.9711 0.2455 -0.1376 0.1279 15.0672 0.0475 0.0136 -0.1195 0.0777 -0.1694 6.7914 0.3476 10.8726 11.2877 10.8727 0.2291 -0.1453 0.1274 14.8168 0.0443 0.0119 -0.1284 0.0714 -0.1748 6.8268 0.3233 10.7696 11.1359 10.7697 0.2124 -0.1532 0.1270 14.5536 0.0411 0.0103 -0.1374 0.0651 -0.1802 6.8621 0.2978 10.6621 10.9702 10.6622 0.1946 -0.1613 0.1266 14.2751 0.0377 0.0088 -0.1467 0.0582 -0.1859 6.8975 0.2644 10.5502 10.7881 10.5508 0.1694 -0.1713 0.1262 13.9784 0.0334 0.0070 -0.1583 0.0475 -0.1929 6.9328 0.2176 10.4337 10.5849 10.5417 0.1313 -0.1844 0.1258 13.6579 0.0274 0.0048 -0.1736 0.0299 -0.2020 6.9682 0.1380 10.3127 10.3539 10.9568 0.0613 -0.2047 0.1254 13.3052 0.0173 0.0020 -0.1979 -0.0046 -0.2161 7.0000 0.0099 10.2000 10.2001 10.1999 -0.0568 -0.2348 0.1250 13.0569 0.0012 0.0000 -0.2348 0.0000 0.0000 RADIUS: 7.00 PROPELLER RADIUS (IN) HUBRAD: 0.57 HUB RADIUS (IN) HUBTRA: 1.65 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.173264 TOTAL WEIGHT (Kg) = 0.078578 TOTAL VOLUME (IN**3) = 2.822698 TOTAL PROJECTED AREA (IN**2) = 11.7297 MOMENT OF INERTIA (SNAIL-IN**2) = 0.003462 MOMENT OF INERTIA (Kg-M**2) = 0.000391 STATIC MOMENT, ONE SIDE (IN-LB) = 0.189733 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 = 86.069 INNER LIMIT (NORMALIZED BY RADIUS) = 0.082 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 16449.05 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.