8x7 (8x7.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 0.8000 1.0480 0.0000 0.0000 0.4000 0.0000 0.4688 0.0000 0.3750 0.0000 0.0750 0.0000 0.0000 0.1160 0.7631 1.7184 0.0124 -0.5502 0.3948 0.0033 0.4658 0.9741 0.3555 0.2407 0.0781 0.0093 -0.1009 0.2320 0.7245 2.3488 0.0970 -1.0715 0.3906 0.0122 0.4570 3.8067 0.3311 0.2345 0.0864 0.0254 -0.0999 0.3480 0.6892 2.9391 0.3205 -1.4388 0.3875 0.0253 0.4423 8.3398 0.3048 0.2240 0.0984 0.0430 -0.0967 0.4640 0.6622 3.4894 0.7398 -1.5151 0.3855 0.0412 0.4217 14.2394 0.2792 0.2090 0.1129 0.0612 -0.0915 0.5800 0.6476 3.9996 1.3924 -1.1953 0.3845 0.0586 0.3952 20.9110 0.2559 0.1915 0.1284 0.0789 -0.0848 0.6960 0.6464 4.4698 2.2811 -0.4241 0.3844 0.0762 0.3629 27.5473 0.2346 0.1733 0.1435 0.0951 -0.0772 0.8120 0.6565 4.8999 3.3542 0.7676 0.3854 0.0926 0.3298 33.3221 0.2165 0.1556 0.1568 0.1087 -0.0694 0.9280 0.6728 5.2900 4.4881 2.2266 0.3873 0.1066 0.2999 37.5861 0.2018 0.1395 0.1669 0.1190 -0.0618 1.0440 0.6897 5.6401 5.4864 3.6609 0.3901 0.1167 0.2734 39.9087 0.1885 0.1255 0.1726 0.1249 -0.0550 1.1600 0.7023 5.9501 6.1097 4.6742 0.3937 0.1218 0.2500 39.9722 0.1756 0.1136 0.1723 0.1259 -0.0493 1.2745 0.7101 6.2168 6.3871 5.2255 0.3979 0.1225 0.2302 38.5762 0.1635 0.1033 0.1679 0.1238 -0.0450 1.3630 0.7147 6.3963 6.5706 5.6100 0.4012 0.1221 0.2171 37.4962 0.1551 0.0960 0.1641 0.1226 -0.0423 1.4501 0.7179 6.5500 6.7273 5.9497 0.4045 0.1207 0.2060 36.4408 0.1479 0.0896 0.1601 0.1217 -0.0400 1.5371 0.7199 6.6812 6.8611 6.2473 0.4076 0.1185 0.1968 35.3905 0.1416 0.0839 0.1557 0.1210 -0.0382 1.6241 0.7206 6.7898 6.9729 6.4991 0.4106 0.1154 0.1894 34.3448 0.1365 0.0791 0.1511 0.1207 -0.0368 1.7112 0.7200 6.8759 7.0634 6.7021 0.4132 0.1115 0.1838 33.3034 0.1323 0.0751 0.1462 0.1206 -0.0358 1.7982 0.7181 6.9394 7.1332 6.8538 0.4155 0.1067 0.1801 32.2661 0.1293 0.0721 0.1411 0.1208 -0.0352 1.8852 0.7149 6.9804 7.1813 6.9526 0.4173 0.1013 0.1773 31.2267 0.1268 0.0696 0.1356 0.1213 -0.0349 1.9723 0.7105 6.9989 7.2060 6.9973 0.4187 0.0958 0.1745 30.1779 0.1240 0.0674 0.1300 0.1221 -0.0348 2.0593 0.7047 7.0000 7.2125 7.0000 0.4194 0.0900 0.1718 29.1363 0.1211 0.0652 0.1240 0.1230 -0.0349 2.1463 0.6976 7.0000 7.2169 7.0002 0.4194 0.0842 0.1690 28.1532 0.1179 0.0629 0.1179 0.1241 -0.0352 2.2334 0.6891 7.0000 7.2203 7.0003 0.4186 0.0782 0.1662 27.2273 0.1146 0.0603 0.1115 0.1252 -0.0357 2.3204 0.6793 7.0000 7.2227 7.0004 0.4170 0.0722 0.1635 26.3537 0.1110 0.0577 0.1049 0.1261 -0.0365 2.4074 0.6680 7.0000 7.2240 7.0004 0.4144 0.0661 0.1607 25.5278 0.1073 0.0549 0.0981 0.1269 -0.0374 2.4945 0.6553 7.0000 7.2241 7.0004 0.4108 0.0598 0.1579 24.7457 0.1035 0.0519 0.0911 0.1273 -0.0386 2.5815 0.6412 7.0000 7.2231 7.0004 0.4060 0.0536 0.1552 24.0041 0.0995 0.0489 0.0840 0.1275 -0.0399 2.6686 0.6256 7.0000 7.2211 7.0004 0.4001 0.0472 0.1524 23.3003 0.0953 0.0458 0.0767 0.1271 -0.0413 2.7556 0.6085 7.0000 7.2181 7.0003 0.3929 0.0408 0.1496 22.6312 0.0910 0.0426 0.0692 0.1263 -0.0429 2.8426 0.5898 7.0000 7.2140 7.0003 0.3843 0.0343 0.1468 21.9941 0.0866 0.0393 0.0616 0.1248 -0.0447 2.9297 0.5697 7.0000 7.2087 7.0003 0.3743 0.0277 0.1441 21.3861 0.0821 0.0361 0.0538 0.1227 -0.0466 3.0167 0.5480 7.0000 7.2020 7.0003 0.3627 0.0211 0.1413 20.8050 0.0774 0.0328 0.0459 0.1198 -0.0486 3.1037 0.5247 7.0000 7.1937 7.0003 0.3496 0.0145 0.1385 20.2481 0.0727 0.0295 0.0378 0.1161 -0.0507 3.1908 0.4998 7.0000 7.1836 7.0002 0.3347 0.0077 0.1358 19.7134 0.0679 0.0263 0.0297 0.1114 -0.0529 3.2778 0.4732 7.0000 7.1718 6.9991 0.3180 0.0010 0.1330 19.1996 0.0629 0.0232 0.0214 0.1058 -0.0551 3.3648 0.4451 7.0000 7.1666 6.9825 0.2995 -0.0056 0.1302 18.7254 0.0580 0.0201 0.0131 0.0991 -0.0576 3.4519 0.4154 7.0000 7.1766 6.9534 0.2791 -0.0120 0.1275 18.3089 0.0529 0.0172 0.0047 0.0912 -0.0602 3.5389 0.3841 6.9936 7.2020 6.9144 0.2565 -0.0181 0.1247 17.9469 0.0479 0.0145 -0.0034 0.0821 -0.0627 3.6259 0.3511 6.9334 7.2003 6.8266 0.2319 -0.0240 0.1219 17.5389 0.0428 0.0119 -0.0115 0.0717 -0.0649 3.7130 0.3165 6.8095 7.1643 6.6883 0.2051 -0.0298 0.1192 17.0714 0.0377 0.0094 -0.0193 0.0598 -0.0669 3.7965 0.2815 6.6307 7.0965 6.5147 0.1772 -0.0355 0.1165 16.5675 0.0328 0.0073 -0.0269 0.0471 -0.0685 3.8202 0.2713 6.5694 7.0707 6.4589 0.1689 -0.0371 0.1157 16.4137 0.0314 0.0068 -0.0290 0.0432 -0.0690 3.8404 0.2624 6.5133 7.0461 6.4092 0.1617 -0.0385 0.1151 16.2782 0.0302 0.0063 -0.0309 0.0398 -0.0694 3.8606 0.2533 6.4538 7.0189 6.3576 0.1542 -0.0400 0.1145 16.1382 0.0290 0.0059 -0.0327 0.0363 -0.0698 3.8808 0.2421 6.3909 6.9888 6.3040 0.1446 -0.0420 0.1138 15.9933 0.0275 0.0053 -0.0353 0.0316 -0.0706 3.9010 0.2275 6.3246 6.9556 6.2666 0.1317 -0.0450 0.1132 15.8426 0.0257 0.0047 -0.0388 0.0252 -0.0718 3.9212 0.2087 6.2548 6.9185 6.2707 0.1148 -0.0491 0.1125 15.6853 0.0235 0.0040 -0.0435 0.0166 -0.0737 3.9414 0.1838 6.1816 6.8775 6.3348 0.0919 -0.0547 0.1119 15.5207 0.0206 0.0031 -0.0499 0.0049 -0.0765 3.9616 0.1478 6.1050 6.8316 6.5669 0.0583 -0.0632 0.1112 15.3472 0.0164 0.0020 -0.0594 -0.0125 -0.0809 3.9818 0.0806 6.0250 6.7796 7.5867 -0.0055 -0.0797 0.1106 15.1621 0.0089 0.0006 -0.0777 -0.0458 -0.0898 4.0000 0.0094 5.9500 5.9500 5.9500 -0.0733 -0.0974 0.1100 13.3192 0.0010 0.0000 -0.0974 0.0000 0.0000 RADIUS: 4.00 PROPELLER RADIUS (IN) HUBRAD: 0.40 HUB RADIUS (IN) HUBTRA: 1.16 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.043538 TOTAL WEIGHT (Kg) = 0.019745 TOTAL VOLUME (IN**3) = 0.709288 TOTAL PROJECTED AREA (IN**2) = 4.3241 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000237 MOMENT OF INERTIA (Kg-M**2) = 0.000027 STATIC MOMENT, ONE SIDE (IN-LB) = 0.024482 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 = 88.487 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 28119.90 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.