GIII BL332 AIRFOIL (giiij-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL332 AIRFOIL (giiij-il) Reynolds number: 50,000 Max Cl/Cd: 32.66 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiij-il-50000.txt Download as CSV file: xf-giiij-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL332 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5586 0.11659 0.10949 0.0105 1.0000 0.2250
-9.250 -0.5756 0.11511 0.10812 0.0076 1.0000 0.2347
-9.000 -0.5632 0.11086 0.10388 0.0086 1.0000 0.2490
-8.750 -0.5563 0.10716 0.10022 0.0091 1.0000 0.2636
-8.500 -0.5550 0.10396 0.09707 0.0092 1.0000 0.2791
-8.250 -0.5599 0.10119 0.09439 0.0088 1.0000 0.2950
-8.000 -0.5328 0.09657 0.08973 0.0119 1.0000 0.3191
-7.750 -0.5487 0.09476 0.08805 0.0117 1.0000 0.3401
-7.500 -0.5198 0.09047 0.08371 0.0155 1.0000 0.3749
-7.250 -0.5154 0.08823 0.08153 0.0184 1.0000 0.4139
-7.000 -0.5047 0.08579 0.07912 0.0222 1.0000 0.4597
-6.750 -0.4684 0.08191 0.07519 0.0262 1.0000 0.5164
-6.500 -0.4399 0.07852 0.07177 0.0294 1.0000 0.5743
-6.250 -0.4125 0.07532 0.06855 0.0321 1.0000 0.6361
-6.000 -0.3740 0.07119 0.06438 0.0331 1.0000 0.7037
-5.250 -0.3270 0.04862 0.04260 0.0170 1.0000 0.5846
-4.750 -0.4611 0.04274 0.03433 -0.0193 1.0000 0.2025
-4.500 -0.4356 0.03924 0.03017 -0.0189 1.0000 0.1707
-4.250 -0.4123 0.03651 0.02689 -0.0179 1.0000 0.1560
-4.000 -0.3904 0.03405 0.02404 -0.0167 1.0000 0.1511
-3.750 -0.3661 0.03256 0.02176 -0.0151 1.0000 0.1449
-3.500 -0.3424 0.03020 0.01927 -0.0141 1.0000 0.1425
-3.250 -0.3178 0.02833 0.01717 -0.0131 1.0000 0.1407
-3.000 -0.2932 0.02689 0.01543 -0.0119 1.0000 0.1428
-2.750 -0.2679 0.02542 0.01380 -0.0110 1.0000 0.1468
-2.500 -0.2411 0.02407 0.01243 -0.0101 1.0000 0.1505
-2.250 -0.2141 0.02302 0.01130 -0.0091 1.0000 0.1568
-2.000 -0.1895 0.02201 0.01033 -0.0082 1.0000 0.1691
-1.750 -0.1678 0.02111 0.00944 -0.0069 1.0000 0.1819
-1.500 -0.0486 0.01697 0.00814 -0.0175 1.0000 1.0000
-1.250 -0.0434 0.01695 0.00784 -0.0140 1.0000 1.0000
-1.000 -0.0380 0.01697 0.00762 -0.0107 1.0000 1.0000
-0.750 -0.0311 0.01702 0.00747 -0.0077 1.0000 1.0000
-0.500 -0.0215 0.01713 0.00738 -0.0052 1.0000 1.0000
-0.250 -0.0093 0.01727 0.00736 -0.0032 1.0000 1.0000
0.000 0.0049 0.01747 0.00740 -0.0017 1.0000 1.0000
0.250 0.0206 0.01771 0.00750 -0.0005 1.0000 1.0000
0.500 0.0373 0.01800 0.00767 0.0005 1.0000 1.0000
0.750 0.0547 0.01834 0.00791 0.0013 1.0000 1.0000
1.000 0.0724 0.01874 0.00823 0.0018 1.0000 1.0000
1.250 0.0903 0.01919 0.00863 0.0022 1.0000 1.0000
1.500 0.1083 0.01971 0.00910 0.0025 1.0000 1.0000
1.750 0.1261 0.02030 0.00967 0.0026 1.0000 1.0000
2.000 0.1436 0.02097 0.01034 0.0026 1.0000 1.0000
2.250 0.1608 0.02173 0.01111 0.0025 1.0000 1.0000
2.500 0.2207 0.02300 0.01248 -0.0057 0.9814 1.0000
2.750 0.2897 0.02420 0.01384 -0.0149 0.9564 1.0000
3.000 0.3497 0.02505 0.01488 -0.0219 0.9286 1.0000
3.250 0.4093 0.02564 0.01572 -0.0280 0.8995 1.0000
3.500 0.4749 0.02578 0.01620 -0.0341 0.8683 1.0000
3.750 0.5348 0.02532 0.01607 -0.0374 0.8348 1.0000
4.000 0.5764 0.02460 0.01565 -0.0366 0.7964 1.0000
4.250 0.6130 0.02337 0.01462 -0.0336 0.7541 1.0000
4.500 0.6402 0.02228 0.01364 -0.0291 0.7078 1.0000
4.750 0.6629 0.02141 0.01281 -0.0243 0.6548 1.0000
5.000 0.6805 0.02092 0.01217 -0.0192 0.5829 1.0000
5.250 0.6933 0.02123 0.01187 -0.0139 0.4728 1.0000
5.500 0.7035 0.02289 0.01253 -0.0096 0.3471 1.0000
5.750 0.7214 0.02487 0.01390 -0.0075 0.2743 1.0000
6.000 0.7439 0.02674 0.01548 -0.0062 0.2325 1.0000
6.250 0.7680 0.02863 0.01725 -0.0052 0.2049 1.0000
6.500 0.7932 0.03067 0.01922 -0.0045 0.1857 1.0000
6.750 0.8172 0.03280 0.02139 -0.0037 0.1704 1.0000
7.000 0.8398 0.03523 0.02421 -0.0027 0.1597 1.0000
7.250 0.8615 0.03800 0.02721 -0.0018 0.1518 1.0000
7.500 0.8808 0.04057 0.03011 -0.0007 0.1437 1.0000
7.750 0.9002 0.04405 0.03377 0.0002 0.1398 1.0000
8.000 0.9119 0.04780 0.03819 0.0017 0.1381 1.0000
8.250 0.9189 0.05185 0.04283 0.0031 0.1363 1.0000
8.500 0.9223 0.05622 0.04774 0.0043 0.1350 1.0000
8.750 0.9214 0.06115 0.05309 0.0051 0.1356 1.0000
9.000 0.9196 0.06643 0.05867 0.0055 0.1379 1.0000
9.250 0.9269 0.07176 0.06410 0.0057 0.1401 1.0000
9.500 0.8628 0.08072 0.07351 0.0022 0.1501 1.0000
9.750 0.8022 0.09520 0.08797 -0.0106 0.1736 1.0000
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Polar data table (+)
Polar graphs
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