22x8 (22x8.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 8.0000 0.0000 0.0000 0.9500 0.0000 0.2947 0.0000 0.5600 0.0000 0.2700 0.0000 0.0000 0.3126 1.8192 8.0000 0.0302 -0.5965 0.9380 0.0192 0.2936 0.8806 0.5341 0.8777 0.2867 0.0282 -0.0008 0.6253 1.7639 8.0000 0.2271 -1.0477 0.9324 0.0700 0.2902 3.3091 0.5119 0.8671 0.3298 0.0545 0.0234 0.9379 1.7349 8.0000 0.7121 -1.1403 0.9319 0.1430 0.2846 6.8904 0.4937 0.8531 0.3915 0.0785 0.0603 1.2505 1.7321 8.0000 1.5434 -0.7463 0.9355 0.2292 0.2767 11.1128 0.4792 0.8358 0.4645 0.1002 0.1058 1.5632 1.7521 8.0000 2.7089 0.1613 0.9418 0.3196 0.2676 15.4195 0.4688 0.8148 0.5412 0.1200 0.1559 1.8758 1.7877 8.0000 4.1293 1.5091 0.9496 0.4051 0.2588 19.3086 0.4627 0.7893 0.6137 0.1379 0.2058 2.1884 1.8281 8.0000 5.6662 3.1341 0.9578 0.4766 0.2504 22.3955 0.4578 0.7584 0.6737 0.1542 0.2506 2.5010 1.8611 8.0000 7.1303 4.7964 0.9652 0.5251 0.2424 24.4057 0.4512 0.7212 0.7125 0.1690 0.2846 2.8137 1.8744 8.0000 8.2862 6.1864 0.9706 0.5415 0.2348 25.1128 0.4401 0.6773 0.7217 0.1820 0.3018 3.1263 1.8577 8.0000 8.8472 6.9228 0.9727 0.5169 0.2275 24.2467 0.4227 0.6264 0.6926 0.1925 0.2954 3.4352 1.8199 8.0000 8.9067 7.0751 0.9721 0.4657 0.2207 22.4234 0.4017 0.5735 0.6386 0.2020 0.2717 3.6807 1.7882 8.0000 8.9482 7.1926 0.9713 0.4268 0.2156 21.1527 0.3855 0.5340 0.5967 0.2108 0.2520 3.9225 1.7560 8.0000 8.9876 7.3073 0.9701 0.3901 0.2107 20.0356 0.3700 0.4975 0.5567 0.2205 0.2320 4.1642 1.7226 8.0000 9.0255 7.4192 0.9685 0.3550 0.2061 19.0319 0.3550 0.4632 0.5178 0.2308 0.2116 4.4060 1.6881 8.0000 9.0621 7.5263 0.9664 0.3212 0.2017 18.1256 0.3405 0.4311 0.4800 0.2415 0.1910 4.6477 1.6526 8.0000 9.0975 7.6269 0.9637 0.2887 0.1975 17.3034 0.3264 0.4010 0.4433 0.2526 0.1704 4.8895 1.6161 8.0000 9.1319 7.7193 0.9605 0.2576 0.1935 16.5544 0.3128 0.3728 0.4078 0.2639 0.1498 5.1313 1.5786 8.0000 9.1654 7.8016 0.9567 0.2276 0.1898 15.8694 0.2996 0.3464 0.3734 0.2752 0.1294 5.3730 1.5401 8.0000 9.1981 7.8720 0.9522 0.1988 0.1863 15.2408 0.2869 0.3218 0.3402 0.2865 0.1091 5.6148 1.5006 8.0000 9.2304 7.9288 0.9469 0.1712 0.1830 14.6623 0.2746 0.2988 0.3081 0.2977 0.0892 5.8565 1.4602 8.0000 9.2622 7.9702 0.9409 0.1447 0.1799 14.1282 0.2627 0.2773 0.2771 0.3087 0.0696 6.0983 1.4189 8.0000 9.2939 7.9945 0.9341 0.1193 0.1771 13.6340 0.2512 0.2572 0.2472 0.3193 0.0505 6.3401 1.3766 8.0000 9.3254 8.0000 0.9264 0.0951 0.1744 13.1755 0.2401 0.2384 0.2185 0.3296 0.0318 6.5818 1.3334 8.0000 9.3560 7.9999 0.9178 0.0720 0.1719 12.7479 0.2292 0.2204 0.1909 0.3394 0.0139 6.8236 1.2894 8.0000 9.3851 7.9998 0.9082 0.0502 0.1693 12.3473 0.2183 0.2031 0.1644 0.3486 -0.0031 7.0653 1.2444 8.0000 9.4126 7.9997 0.8976 0.0297 0.1667 11.9711 0.2075 0.1863 0.1391 0.3573 -0.0193 7.3071 1.1986 8.0000 9.4386 7.9996 0.8859 0.0105 0.1642 11.6170 0.1968 0.1702 0.1149 0.3654 -0.0346 7.5489 1.1519 8.0000 9.4630 7.9996 0.8731 -0.0076 0.1616 11.2830 0.1862 0.1548 0.0919 0.3727 -0.0489 7.7906 1.1044 8.0000 9.4858 7.9996 0.8592 -0.0245 0.1590 10.9671 0.1756 0.1400 0.0699 0.3792 -0.0624 8.0324 1.0561 8.0000 9.5069 7.9995 0.8440 -0.0402 0.1565 10.6679 0.1653 0.1260 0.0491 0.3850 -0.0749 8.2742 1.0070 8.0000 9.5264 7.9995 0.8276 -0.0547 0.1539 10.3838 0.1550 0.1127 0.0294 0.3898 -0.0865 8.5159 0.9570 8.0000 9.5443 7.9995 0.8099 -0.0681 0.1513 10.1137 0.1448 0.1001 0.0109 0.3937 -0.0971 8.7577 0.9063 8.0000 9.5604 7.9996 0.7908 -0.0803 0.1488 9.8563 0.1348 0.0883 -0.0065 0.3966 -0.1068 8.9994 0.8548 8.0000 9.5747 7.9996 0.7703 -0.0914 0.1462 9.6106 0.1250 0.0772 -0.0228 0.3984 -0.1156 9.2412 0.8025 8.0000 9.5871 7.9997 0.7483 -0.1014 0.1437 9.3757 0.1153 0.0668 -0.0380 0.3991 -0.1233 9.4830 0.7495 8.0000 9.5976 7.9997 0.7249 -0.1104 0.1411 9.1506 0.1057 0.0573 -0.0520 0.3987 -0.1302 9.7247 0.6957 8.0000 9.6060 7.9998 0.6999 -0.1182 0.1385 8.9345 0.0964 0.0485 -0.0649 0.3970 -0.1360 9.9665 0.6413 8.0000 9.6123 7.9998 0.6733 -0.1250 0.1360 8.7267 0.0872 0.0404 -0.0766 0.3940 -0.1409 10.2082 0.5861 8.0000 9.6161 7.9999 0.6450 -0.1307 0.1334 8.5264 0.0782 0.0331 -0.0873 0.3897 -0.1449 10.4403 0.5327 8.0000 9.8156 7.9486 0.6163 -0.1336 0.1309 8.5101 0.0697 0.0269 -0.0960 0.3842 -0.1477 10.5056 0.5177 8.0000 9.9861 7.9181 0.6079 -0.1334 0.1302 8.6028 0.0674 0.0252 -0.0980 0.3824 -0.1482 10.5611 0.5049 8.0000 10.1777 7.8923 0.6007 -0.1329 0.1296 8.7199 0.0655 0.0239 -0.0996 0.3808 -0.1486 10.6167 0.4922 8.0000 10.4146 7.8693 0.5934 -0.1321 0.1291 8.8737 0.0635 0.0226 -0.1009 0.3792 -0.1489 10.6722 0.4794 8.0000 10.6991 7.8518 0.5860 -0.1310 0.1285 9.0655 0.0616 0.0213 -0.1021 0.3774 -0.1490 10.7278 0.4633 8.0000 11.0351 7.8436 0.5752 -0.1302 0.1279 9.2976 0.0592 0.0198 -0.1038 0.3737 -0.1495 10.7833 0.4364 8.0000 11.4270 7.8506 0.5536 -0.1310 0.1273 9.5732 0.0555 0.0174 -0.1076 0.3640 -0.1511 10.8389 0.3956 8.0000 11.8762 7.8876 0.5183 -0.1340 0.1267 9.8922 0.0501 0.0142 -0.1143 0.3466 -0.1543 10.8944 0.3336 8.0000 12.3834 7.9510 0.4621 -0.1410 0.1261 10.2543 0.0421 0.0100 -0.1256 0.3173 -0.1600 10.9500 0.2147 8.0000 12.9552 8.1334 0.3500 -0.1590 0.1255 10.6639 0.0270 0.0041 -0.1499 0.2568 -0.1726 11.0000 0.0200 8.0000 8.0001 8.0000 0.1634 -0.1949 0.1250 6.6026 0.0025 0.0000 -0.1949 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) = 0.522563 TOTAL WEIGHT (Kg) = 0.236990 TOTAL VOLUME (IN**3) = 8.513227 TOTAL PROJECTED AREA (IN**2) = 29.0019 MOMENT OF INERTIA (SNAIL-IN**2) = 0.020574 MOMENT OF INERTIA (Kg-M**2) = 0.002324 STATIC MOMENT, ONE SIDE (IN-LB) = 0.815463 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) = 11412.38 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.