22x10 (22x10.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 1.9000 3.0486 0.0000 0.0000 0.9500 0.0000 0.3053 0.0000 0.5800 0.0000 0.2700 0.0000 0.0000 0.3126 1.8184 4.0101 0.0312 -0.6385 0.9380 0.0195 0.3029 0.9108 0.5509 0.9077 0.2868 0.0281 -0.0098 0.6253 1.7612 4.8804 0.2360 -1.1257 0.9324 0.0713 0.2960 3.4376 0.5213 0.8948 0.3304 0.0552 0.0147 0.9379 1.7299 5.6641 0.7435 -1.2350 0.9319 0.1462 0.2862 7.1906 0.4951 0.8776 0.3932 0.0804 0.0522 1.2505 1.7250 6.3657 1.6205 -0.8259 0.9355 0.2352 0.2767 11.6536 0.4773 0.8566 0.4679 0.1036 0.0989 1.5632 1.7440 6.9895 2.8633 0.1396 0.9418 0.3294 0.2676 16.2533 0.4666 0.8318 0.5471 0.1250 0.1505 1.8758 1.7797 7.5400 4.3987 1.5954 0.9496 0.4200 0.2588 20.4664 0.4606 0.8027 0.6232 0.1446 0.2026 2.1884 1.8215 8.0218 6.0910 3.3799 0.9578 0.4979 0.2504 23.8921 0.4562 0.7685 0.6879 0.1625 0.2502 2.5010 1.8567 8.4391 7.7505 5.2477 0.9652 0.5542 0.2424 26.2527 0.4501 0.7289 0.7327 0.1787 0.2879 2.8137 1.8722 8.7966 9.1371 6.8774 0.9706 0.5800 0.2348 27.3318 0.4396 0.6834 0.7493 0.1928 0.3096 3.1263 1.8568 9.0987 9.9572 7.8689 0.9727 0.5663 0.2275 26.8807 0.4225 0.6321 0.7290 0.2043 0.3088 3.4352 1.8189 9.3470 10.2657 8.2600 0.9721 0.5263 0.2207 25.4364 0.4015 0.5792 0.6842 0.2140 0.2918 3.6807 1.7874 9.5117 10.4723 8.5451 0.9713 0.4952 0.2156 24.3622 0.3853 0.5394 0.6491 0.2226 0.2777 3.9225 1.7552 9.6479 10.6478 8.8060 0.9701 0.4652 0.2107 23.3662 0.3698 0.5023 0.6152 0.2316 0.2635 4.1642 1.7219 9.7604 10.7979 9.0456 0.9685 0.4359 0.2061 22.4256 0.3548 0.4673 0.5819 0.2412 0.2491 4.4060 1.6875 9.8513 10.9249 9.2624 0.9664 0.4073 0.2017 21.5359 0.3403 0.4344 0.5493 0.2511 0.2343 4.6477 1.6521 9.9226 11.0310 9.4551 0.9637 0.3792 0.1975 20.6935 0.3263 0.4035 0.5173 0.2613 0.2193 4.8895 1.6156 9.9763 11.1184 9.6225 0.9605 0.3518 0.1935 19.8956 0.3127 0.3746 0.4859 0.2717 0.2040 5.1313 1.5782 10.0146 11.1894 9.7634 0.9567 0.3250 0.1898 19.1398 0.2995 0.3477 0.4551 0.2822 0.1885 5.3730 1.5397 10.0395 11.2463 9.8769 0.9522 0.2988 0.1863 18.4243 0.2868 0.3225 0.4250 0.2927 0.1728 5.6148 1.5003 10.0530 11.2912 9.9624 0.9469 0.2732 0.1830 17.7477 0.2745 0.2992 0.3956 0.3032 0.1569 5.8565 1.4599 10.0573 11.3265 10.0193 0.9409 0.2481 0.1799 17.1086 0.2627 0.2775 0.3667 0.3135 0.1408 6.0983 1.4186 10.0543 11.3544 10.0472 0.9341 0.2237 0.1771 16.5062 0.2512 0.2573 0.3385 0.3236 0.1246 6.3401 1.3764 10.0461 11.3771 10.0462 0.9264 0.1998 0.1744 15.9394 0.2401 0.2384 0.3110 0.3333 0.1084 6.5818 1.3332 10.0349 11.3958 10.0349 0.9178 0.1767 0.1719 15.4061 0.2291 0.2204 0.2840 0.3427 0.0923 6.8236 1.2892 10.0226 11.4120 10.0225 0.9082 0.1544 0.1693 14.9051 0.2183 0.2031 0.2578 0.3516 0.0766 7.0653 1.2443 10.0113 11.4277 10.0111 0.8976 0.1329 0.1667 14.4357 0.2075 0.1863 0.2321 0.3600 0.0611 7.3071 1.1985 10.0031 11.4450 10.0028 0.8859 0.1122 0.1642 13.9975 0.1968 0.1702 0.2071 0.3677 0.0459 7.5489 1.1518 10.0000 11.4659 9.9997 0.8731 0.0922 0.1616 13.5899 0.1861 0.1548 0.1827 0.3748 0.0310 7.7906 1.1043 10.0000 11.4883 9.9997 0.8592 0.0729 0.1590 13.2080 0.1756 0.1400 0.1589 0.3811 0.0165 8.0324 1.0560 10.0000 11.5092 9.9996 0.8440 0.0544 0.1565 12.8463 0.1652 0.1260 0.1357 0.3866 0.0024 8.2742 1.0069 10.0000 11.5284 9.9996 0.8276 0.0365 0.1539 12.5031 0.1550 0.1127 0.1132 0.3913 -0.0113 8.5159 0.9569 10.0000 11.5460 9.9996 0.8099 0.0192 0.1513 12.1769 0.1448 0.1001 0.0914 0.3950 -0.0246 8.7577 0.9062 10.0000 11.5619 9.9997 0.7908 0.0027 0.1488 11.8662 0.1348 0.0883 0.0701 0.3978 -0.0375 8.9994 0.8547 10.0000 11.5760 9.9997 0.7703 -0.0133 0.1462 11.5698 0.1250 0.0772 0.0495 0.3995 -0.0500 9.2412 0.8025 10.0000 11.5883 9.9997 0.7483 -0.0286 0.1437 11.2866 0.1153 0.0668 0.0295 0.4001 -0.0620 9.4830 0.7495 10.0000 11.5986 9.9997 0.7249 -0.0433 0.1411 11.0156 0.1057 0.0573 0.0102 0.3995 -0.0736 9.7247 0.6957 10.0000 11.6069 9.9998 0.6999 -0.0574 0.1385 10.7557 0.0964 0.0485 -0.0085 0.3977 -0.0848 9.9665 0.6412 10.0000 11.6130 9.9998 0.6733 -0.0709 0.1360 10.5061 0.0872 0.0404 -0.0266 0.3946 -0.0955 10.2082 0.5861 10.0000 11.6167 9.9999 0.6450 -0.0839 0.1334 10.2658 0.0782 0.0331 -0.0441 0.3902 -0.1058 10.4403 0.5327 10.0000 11.7853 9.9566 0.6163 -0.0944 0.1309 10.1850 0.0697 0.0269 -0.0598 0.3847 -0.1151 10.5056 0.5177 10.0000 11.9293 9.9308 0.6079 -0.0966 0.1302 10.2441 0.0674 0.0252 -0.0639 0.3829 -0.1176 10.5611 0.5049 10.0000 12.0909 9.9090 0.6007 -0.0982 0.1296 10.3265 0.0655 0.0239 -0.0673 0.3813 -0.1197 10.6167 0.4921 10.0000 12.2908 9.8896 0.5934 -0.0996 0.1291 10.4398 0.0635 0.0226 -0.0705 0.3796 -0.1217 10.6722 0.4794 10.0000 12.5310 9.8749 0.5860 -0.1007 0.1285 10.5850 0.0616 0.0213 -0.0735 0.3778 -0.1236 10.7278 0.4634 10.0000 12.8148 9.8681 0.5753 -0.1022 0.1279 10.7645 0.0593 0.0198 -0.0771 0.3743 -0.1259 10.7833 0.4367 10.0000 13.1457 9.8762 0.5540 -0.1056 0.1273 10.9802 0.0556 0.0174 -0.0832 0.3647 -0.1296 10.8389 0.3960 10.0000 13.5252 9.9067 0.5190 -0.1117 0.1267 11.2328 0.0502 0.0143 -0.0925 0.3474 -0.1351 10.8944 0.3341 10.0000 13.9543 9.9693 0.4630 -0.1221 0.1261 11.5222 0.0421 0.0101 -0.1070 0.3183 -0.1434 10.9500 0.2155 10.0000 14.4373 10.1403 0.3516 -0.1445 0.1255 11.8511 0.0270 0.0042 -0.1355 0.2582 -0.1594 11.0000 0.0200 10.0000 10.0000 10.0000 0.1650 -0.1857 0.1250 8.2328 0.0025 0.0000 -0.1857 0.0000 0.0000 RADIUS: 11.00 PROPELLER RADIUS (IN) HUBRAD: 0.95 HUB RADIUS (IN) HUBTRA: 3.13 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.530283 TOTAL WEIGHT (Kg) = 0.240491 TOTAL VOLUME (IN**3) = 8.638986 TOTAL PROJECTED AREA (IN**2) = 28.6380 MOMENT OF INERTIA (SNAIL-IN**2) = 0.020650 MOMENT OF INERTIA (Kg-M**2) = 0.002332 STATIC MOMENT, ONE SIDE (IN-LB) = 0.821270 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 = 62.127 INNER LIMIT (NORMALIZED BY RADIUS) = 0.086 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 11627.90 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 4.00, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 6.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.