12x9W (12x9W.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 0.5625 0.0000 0.0000 0.5000 0.0000 0.4600 0.0000 0.4600 0.0000 0.0700 0.0000 0.0000 0.1500 0.9541 1.5446 0.0176 -0.7415 0.4928 0.0062 0.4579 1.0710 0.4369 0.3709 0.0775 0.0101 -0.1413 0.3000 0.9095 2.4660 0.1374 -1.4342 0.4863 0.0229 0.4517 4.1680 0.4108 0.3672 0.0977 0.0274 -0.1338 0.4500 0.8721 3.3266 0.4495 -1.8926 0.4809 0.0476 0.4414 9.0334 0.3849 0.3579 0.1275 0.0450 -0.1194 0.6000 0.8480 4.1265 1.0253 -1.9344 0.4767 0.0776 0.4269 15.2146 0.3620 0.3423 0.1634 0.0624 -0.0994 0.7500 0.8413 4.8656 1.9047 -1.4347 0.4741 0.1105 0.4083 22.0077 0.3435 0.3231 0.2022 0.0791 -0.0760 0.9000 0.8520 5.5440 3.0787 -0.3508 0.4733 0.1437 0.3857 28.5651 0.3286 0.3022 0.2406 0.0945 -0.0512 1.0500 0.8757 6.1616 4.4702 1.2388 0.4746 0.1748 0.3624 34.1208 0.3173 0.2814 0.2754 0.1080 -0.0271 1.2000 0.9051 6.7185 5.9214 3.1043 0.4782 0.2014 0.3403 38.1443 0.3080 0.2620 0.3033 0.1194 -0.0056 1.3500 0.9322 7.2146 7.1981 4.8606 0.4843 0.2209 0.3195 40.3181 0.2979 0.2449 0.3213 0.1281 0.0114 1.5000 0.9503 7.6500 8.0219 6.0131 0.4933 0.2308 0.3000 40.4029 0.2851 0.2302 0.3264 0.1342 0.0217 1.6495 0.9622 8.0234 8.4282 6.5593 0.5046 0.2332 0.2818 39.1189 0.2711 0.2179 0.3224 0.1389 0.0266 1.7897 0.9759 8.3188 8.7473 7.0225 0.5165 0.2339 0.2659 37.8794 0.2594 0.2080 0.3177 0.1432 0.0297 1.9293 0.9915 8.5603 9.0087 7.4355 0.5293 0.2333 0.2511 36.6181 0.2489 0.1994 0.3124 0.1473 0.0316 2.0690 1.0086 8.7492 9.2139 7.7950 0.5426 0.2313 0.2374 35.3283 0.2394 0.1919 0.3065 0.1511 0.0324 2.2086 1.0268 8.8854 9.3634 8.0964 0.5563 0.2281 0.2248 34.0090 0.2308 0.1859 0.2999 0.1535 0.0322 2.3483 1.0457 8.9689 9.4577 8.3355 0.5701 0.2238 0.2133 32.6597 0.2230 0.1812 0.2926 0.1547 0.0312 2.4879 1.0647 8.9998 9.4973 8.5091 0.5835 0.2182 0.2028 31.2806 0.2160 0.1774 0.2848 0.1549 0.0298 2.6276 1.0834 9.0000 9.5050 8.6355 0.5964 0.2117 0.1935 29.9302 0.2097 0.1742 0.2764 0.1547 0.0277 2.7672 1.1013 9.0000 9.5119 8.7429 0.6084 0.2043 0.1853 28.6815 0.2041 0.1711 0.2675 0.1546 0.0249 2.9069 1.1179 9.0000 9.5189 8.8316 0.6193 0.1962 0.1782 27.5270 0.1992 0.1681 0.2579 0.1547 0.0214 3.0466 1.1329 9.0000 9.5276 8.9017 0.6287 0.1869 0.1721 26.4610 0.1950 0.1654 0.2477 0.1551 0.0170 3.1862 1.1457 9.0000 9.5381 8.9530 0.6364 0.1766 0.1672 25.4751 0.1915 0.1631 0.2369 0.1551 0.0117 3.3259 1.1559 9.0000 9.5508 8.9856 0.6421 0.1652 0.1633 24.5623 0.1887 0.1614 0.2255 0.1544 0.0055 3.4655 1.1630 9.0000 9.5660 8.9996 0.6454 0.1528 0.1605 23.7170 0.1867 0.1603 0.2134 0.1529 -0.0015 3.6052 1.1666 9.0000 9.5832 9.0001 0.6461 0.1394 0.1585 22.9314 0.1849 0.1591 0.2006 0.1504 -0.0093 3.7448 1.1660 9.0000 9.5995 9.0002 0.6439 0.1255 0.1566 22.1943 0.1826 0.1569 0.1869 0.1469 -0.0174 3.8845 1.1610 9.0000 9.6146 9.0003 0.6385 0.1111 0.1546 21.5010 0.1795 0.1536 0.1725 0.1423 -0.0259 4.0241 1.1511 9.0000 9.6285 9.0003 0.6295 0.0962 0.1527 20.8473 0.1757 0.1490 0.1573 0.1363 -0.0347 4.1638 1.1356 9.0000 9.6411 9.0003 0.6168 0.0808 0.1507 20.2297 0.1711 0.1432 0.1411 0.1291 -0.0439 4.3034 1.1142 9.0000 9.6521 9.0003 0.6000 0.0647 0.1488 19.6447 0.1657 0.1360 0.1239 0.1203 -0.0534 4.4431 1.0864 9.0000 9.6613 9.0003 0.5787 0.0480 0.1468 19.0894 0.1595 0.1277 0.1057 0.1100 -0.0634 4.5828 1.0517 9.0000 9.6685 9.0002 0.5528 0.0306 0.1448 18.5609 0.1523 0.1181 0.0863 0.0981 -0.0739 4.7224 1.0097 9.0000 9.6732 9.0002 0.5220 0.0123 0.1429 18.0563 0.1443 0.1075 0.0656 0.0844 -0.0850 4.8621 0.9598 9.0000 9.6749 9.0002 0.4858 -0.0069 0.1409 17.5729 0.1353 0.0959 0.0436 0.0688 -0.0967 5.0017 0.9016 9.0000 9.6727 9.0001 0.4441 -0.0270 0.1390 17.1077 0.1253 0.0836 0.0202 0.0514 -0.1090 5.1414 0.8346 8.9730 9.6385 8.9731 0.3965 -0.0483 0.1370 16.6133 0.1144 0.0708 -0.0048 0.0318 -0.1219 5.2810 0.7584 8.8934 9.5460 8.8919 0.3428 -0.0709 0.1351 16.0500 0.1024 0.0578 -0.0315 0.0101 -0.1355 5.4207 0.6727 8.7611 9.4524 8.7194 0.2826 -0.0938 0.1331 15.5109 0.0895 0.0449 -0.0596 -0.0139 -0.1500 5.5603 0.5772 8.5761 9.4072 8.4725 0.2157 -0.1166 0.1312 15.0702 0.0757 0.0327 -0.0889 -0.0402 -0.1654 5.6943 0.4756 8.3492 9.4246 8.2044 0.1449 -0.1392 0.1293 14.7574 0.0615 0.0220 -0.1183 -0.0675 -0.1812 5.7303 0.4466 8.2800 9.4383 8.1318 0.1247 -0.1456 0.1288 14.6891 0.0575 0.0194 -0.1266 -0.0752 -0.1856 5.7606 0.4215 8.2190 9.4515 8.0715 0.1073 -0.1511 0.1284 14.6347 0.0541 0.0172 -0.1336 -0.0818 -0.1895 5.7909 0.3959 8.1555 9.4650 8.0123 0.0896 -0.1567 0.1279 14.5813 0.0506 0.0152 -0.1408 -0.0886 -0.1934 5.8212 0.3695 8.0896 9.4773 7.9544 0.0714 -0.1626 0.1275 14.5267 0.0471 0.0132 -0.1482 -0.0955 -0.1974 5.8515 0.3412 8.0211 9.4864 7.8985 0.0515 -0.1690 0.1271 14.4678 0.0434 0.0113 -0.1561 -0.1032 -0.2017 5.8818 0.3100 7.9502 9.4886 7.8445 0.0290 -0.1762 0.1267 14.3997 0.0393 0.0093 -0.1649 -0.1122 -0.2065 5.9121 0.2745 7.8768 9.4898 7.8291 0.0024 -0.1846 0.1262 14.3306 0.0346 0.0073 -0.1749 -0.1234 -0.2119 5.9424 0.2317 7.8010 9.4614 7.8923 -0.0309 -0.1949 0.1258 14.2196 0.0291 0.0053 -0.1870 -0.1381 -0.2184 5.9727 0.1729 7.7226 9.4013 8.2238 -0.0784 -0.2089 0.1254 14.0640 0.0217 0.0030 -0.2032 -0.1597 -0.2269 6.0000 0.0329 7.6500 7.6500 7.6500 -0.1787 -0.2382 0.1250 11.4709 0.0041 0.0000 -0.2382 0.0000 0.0000 RADIUS: 6.00 PROPELLER RADIUS (IN) HUBRAD: 0.50 HUB RADIUS (IN) HUBTRA: 1.50 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.132014 TOTAL WEIGHT (Kg) = 0.059870 TOTAL VOLUME (IN**3) = 2.150675 TOTAL PROJECTED AREA (IN**2) = 10.2525 MOMENT OF INERTIA (SNAIL-IN**2) = 0.002307 MOMENT OF INERTIA (Kg-M**2) = 0.000261 STATIC MOMENT, ONE SIDE (IN-LB) = 0.138815 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 = 105.804 INNER LIMIT (NORMALIZED BY RADIUS) = 0.083 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 14322.52 BASED ON MODULUS (MILLION) = 1.60 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.