8.8x9.5 (88x95.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 0.9000 6.4418 -0.5000 -0.5000 0.4500 0.0000 0.2141 0.0000 0.1927 0.0000 0.2100 0.0000 0.0000 0.1200 0.8601 6.2213 -0.4857 -1.0223 0.4452 0.0070 0.2204 -32.7875 0.1896 0.3742 0.2124 0.0137 -0.0444 0.2400 0.8158 6.0662 -0.3883 -1.5158 0.4424 0.0259 0.2262 -14.4382 0.1845 0.3574 0.2185 0.0340 -0.0427 0.3600 0.7735 5.9715 -0.1317 -1.8468 0.4414 0.0530 0.2313 -3.3311 0.1789 0.3305 0.2265 0.0577 -0.0381 0.4800 0.7399 5.9327 0.3509 -1.8740 0.4416 0.0850 0.2358 6.6371 0.1745 0.2958 0.2353 0.0833 -0.0312 0.6000 0.7200 5.9447 1.1088 -1.4862 0.4429 0.1188 0.2397 16.3902 0.1726 0.2582 0.2442 0.1091 -0.0231 0.7200 0.7147 6.0029 2.1563 -0.6219 0.4447 0.1512 0.2430 25.4850 0.1737 0.2215 0.2524 0.1336 -0.0148 0.8400 0.7203 6.1024 3.4449 0.6878 0.4467 0.1790 0.2457 33.1327 0.1770 0.1887 0.2589 0.1552 -0.0073 0.9600 0.7297 6.2385 4.8305 2.2636 0.4487 0.1989 0.2477 38.6888 0.1808 0.1616 0.2621 0.1725 -0.0014 1.0800 0.7346 6.4064 6.0535 3.7359 0.4501 0.2079 0.2492 41.7357 0.1831 0.1417 0.2602 0.1839 0.0021 1.2000 0.7280 6.6012 6.7620 4.5640 0.4507 0.2028 0.2500 41.8869 0.1820 0.1299 0.2511 0.1880 0.0023 1.3188 0.7129 6.8160 7.0083 4.8192 0.4506 0.1883 0.2503 40.2230 0.1784 0.1210 0.2359 0.1881 -0.0001 1.4176 0.7002 7.0079 7.2219 5.1515 0.4503 0.1767 0.2500 39.0348 0.1751 0.1103 0.2218 0.1894 -0.0027 1.5153 0.6876 7.2064 7.4416 5.5472 0.4499 0.1659 0.2493 38.0118 0.1714 0.0991 0.2078 0.1912 -0.0054 1.6129 0.6748 7.4113 7.6672 5.9638 0.4493 0.1555 0.2483 37.1099 0.1675 0.0893 0.1947 0.1931 -0.0080 1.7106 0.6620 7.6199 7.8962 6.3707 0.4485 0.1456 0.2468 36.3042 0.1634 0.0818 0.1834 0.1947 -0.0100 1.8082 0.6492 7.8297 8.1259 6.7593 0.4475 0.1362 0.2449 35.5737 0.1590 0.0768 0.1739 0.1959 -0.0113 1.9058 0.6363 8.0381 8.3538 7.1439 0.4463 0.1272 0.2426 34.9004 0.1544 0.0732 0.1659 0.1968 -0.0122 2.0035 0.6233 8.2426 8.5771 7.5389 0.4448 0.1186 0.2400 34.2690 0.1496 0.0696 0.1582 0.1977 -0.0130 2.1011 0.6103 8.4404 8.7931 7.9323 0.4430 0.1104 0.2369 33.6662 0.1446 0.0660 0.1506 0.1985 -0.0140 2.1987 0.5972 8.6291 8.9993 8.3078 0.4409 0.1026 0.2334 33.0807 0.1394 0.0624 0.1431 0.1995 -0.0152 2.2964 0.5841 8.8061 9.1928 8.6454 0.4385 0.0952 0.2295 32.5023 0.1340 0.0587 0.1355 0.2005 -0.0166 2.3940 0.5708 8.9687 9.3710 8.9225 0.4357 0.0880 0.2252 31.9225 0.1285 0.0551 0.1276 0.2017 -0.0185 2.4917 0.5575 9.1145 9.5312 9.1158 0.4326 0.0812 0.2204 31.3333 0.1229 0.0515 0.1194 0.2030 -0.0207 2.5893 0.5442 9.2407 9.6704 9.2422 0.4290 0.0746 0.2155 30.7276 0.1173 0.0479 0.1111 0.2044 -0.0232 2.6869 0.5307 9.3449 9.7860 9.3463 0.4251 0.0681 0.2106 30.0989 0.1117 0.0445 0.1030 0.2053 -0.0256 2.7846 0.5171 9.4245 9.8752 9.4258 0.4207 0.0619 0.2056 29.4415 0.1063 0.0412 0.0950 0.2059 -0.0277 2.8822 0.5035 9.4768 9.9352 9.4780 0.4159 0.0558 0.2007 28.7500 0.1010 0.0382 0.0873 0.2060 -0.0297 2.9798 0.4897 9.4993 9.9633 9.5004 0.4106 0.0498 0.1957 28.0194 0.0958 0.0352 0.0798 0.2056 -0.0315 3.0775 0.4758 9.5000 9.9673 9.5010 0.4048 0.0440 0.1908 27.2697 0.0908 0.0324 0.0725 0.2049 -0.0331 3.1751 0.4618 9.5000 9.9683 9.5009 0.3984 0.0384 0.1858 26.5499 0.0858 0.0297 0.0655 0.2037 -0.0347 3.2728 0.4476 9.5000 9.9668 9.5008 0.3916 0.0331 0.1809 25.8589 0.0810 0.0272 0.0586 0.2021 -0.0363 3.3704 0.4334 9.5000 9.9625 9.5007 0.3841 0.0279 0.1759 25.1943 0.0762 0.0248 0.0520 0.2000 -0.0378 3.4680 0.4190 9.5000 9.9552 9.5006 0.3761 0.0229 0.1710 24.5538 0.0716 0.0226 0.0455 0.1975 -0.0393 3.5657 0.4044 9.5000 9.9446 9.5005 0.3675 0.0182 0.1660 23.9354 0.0671 0.0205 0.0393 0.1944 -0.0408 3.6633 0.3897 9.5000 9.9303 9.5004 0.3582 0.0136 0.1611 23.3368 0.0628 0.0185 0.0333 0.1908 -0.0422 3.7609 0.3749 9.5000 9.9121 9.5003 0.3483 0.0092 0.1561 22.7559 0.0585 0.0166 0.0275 0.1866 -0.0436 3.8586 0.3599 9.5000 9.8893 9.5002 0.3377 0.0050 0.1512 22.1907 0.0544 0.0149 0.0219 0.1818 -0.0449 3.9562 0.3447 9.5000 9.8614 9.5002 0.3264 0.0010 0.1462 21.6390 0.0504 0.0133 0.0165 0.1764 -0.0461 4.0539 0.3294 9.4706 9.7984 9.4707 0.3144 -0.0029 0.1413 21.0411 0.0465 0.0117 0.0114 0.1702 -0.0472 4.1476 0.3145 9.2794 9.5689 9.2795 0.3022 -0.0066 0.1365 20.1627 0.0429 0.0104 0.0066 0.1635 -0.0476 4.1736 0.3097 9.1948 9.4727 9.1950 0.2981 -0.0079 0.1352 19.8613 0.0419 0.0100 0.0051 0.1611 -0.0477 4.1956 0.3031 9.1123 9.3802 9.1129 0.2922 -0.0098 0.1341 19.5868 0.0406 0.0095 0.0028 0.1579 -0.0484 4.2177 0.2937 9.0199 9.2777 9.0211 0.2836 -0.0127 0.1330 19.2948 0.0391 0.0089 -0.0005 0.1531 -0.0496 4.2398 0.2811 8.9176 9.1651 8.9243 0.2721 -0.0166 0.1319 18.9855 0.0371 0.0081 -0.0050 0.1468 -0.0514 4.2619 0.2647 8.8054 9.0423 8.8414 0.2568 -0.0216 0.1308 18.6586 0.0346 0.0071 -0.0107 0.1384 -0.0540 4.2839 0.2434 8.6834 8.9092 8.7658 0.2368 -0.0282 0.1296 18.3141 0.0316 0.0060 -0.0182 0.1274 -0.0575 4.3060 0.2147 8.5515 8.7658 8.7143 0.2097 -0.0369 0.1285 17.9520 0.0276 0.0047 -0.0281 0.1125 -0.0625 4.3281 0.1714 8.4097 8.6121 8.7511 0.1687 -0.0499 0.1274 17.5725 0.0218 0.0030 -0.0428 0.0902 -0.0702 4.3501 0.0915 8.2581 8.4493 9.3886 0.0925 -0.0737 0.1263 17.1779 0.0115 0.0009 -0.0700 0.0490 -0.0849 4.3700 0.0139 8.1132 8.1132 8.1132 0.0184 -0.0963 0.1253 16.4615 0.0017 0.0000 -0.0963 0.0000 0.0000 RADIUS: 4.37 PROPELLER RADIUS (IN) HUBRAD: 0.45 HUB RADIUS (IN) HUBTRA: 1.20 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.056635 TOTAL WEIGHT (Kg) = 0.025685 TOTAL VOLUME (IN**3) = 0.922649 TOTAL PROJECTED AREA (IN**2) = 4.3234 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000293 MOMENT OF INERTIA (Kg-M**2) = 0.000033 STATIC MOMENT, ONE SIDE (IN-LB) = 0.029710 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 = 73.662 INNER LIMIT (NORMALIZED BY RADIUS) = 0.103 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 35654.72 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.