GIII BL369 AIRFOIL (giiik-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL369 AIRFOIL (giiik-il) Reynolds number: 100,000 Max Cl/Cd: 42.61 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiik-il-100000-n5.txt Download as CSV file: xf-giiik-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL369 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5678 0.11494 0.10965 -0.0004 1.0000 0.0536
-9.750 -0.5708 0.11078 0.10554 -0.0051 1.0000 0.0539
-9.500 -0.5730 0.10630 0.10109 -0.0098 1.0000 0.0541
-9.250 -0.5769 0.10136 0.09620 -0.0154 1.0000 0.0542
-8.750 -0.5796 0.09176 0.08660 -0.0201 1.0000 0.0546
-8.500 -0.5661 0.08775 0.08267 -0.0175 1.0000 0.0556
-8.250 -0.5612 0.08414 0.07908 -0.0177 1.0000 0.0563
-8.000 -0.5573 0.08032 0.07525 -0.0191 1.0000 0.0571
-7.750 -0.5537 0.07640 0.07130 -0.0208 1.0000 0.0580
-7.500 -0.5494 0.07243 0.06728 -0.0226 1.0000 0.0588
-7.250 -0.5441 0.06847 0.06324 -0.0241 1.0000 0.0597
-7.000 -0.5373 0.06460 0.05926 -0.0252 1.0000 0.0607
-6.500 -0.5196 0.05334 0.04712 -0.0266 1.0000 0.0423
-6.250 -0.5080 0.04988 0.04358 -0.0259 1.0000 0.0413
-6.000 -0.4958 0.04656 0.04010 -0.0251 1.0000 0.0400
-5.750 -0.4828 0.04329 0.03659 -0.0239 1.0000 0.0388
-5.500 -0.4689 0.04012 0.03313 -0.0224 1.0000 0.0377
-5.250 -0.4540 0.03713 0.02981 -0.0207 1.0000 0.0369
-5.000 -0.4379 0.03443 0.02676 -0.0190 1.0000 0.0364
-4.750 -0.4207 0.03207 0.02407 -0.0174 1.0000 0.0363
-4.500 -0.4026 0.03013 0.02184 -0.0158 1.0000 0.0368
-4.250 -0.3838 0.02857 0.02003 -0.0143 1.0000 0.0384
-4.000 -0.3641 0.02702 0.01819 -0.0129 1.0000 0.0399
-3.750 -0.3435 0.02546 0.01634 -0.0114 1.0000 0.0405
-3.500 -0.3221 0.02405 0.01466 -0.0101 1.0000 0.0412
-3.250 -0.3002 0.02289 0.01323 -0.0089 1.0000 0.0422
-3.000 -0.2724 0.02155 0.01179 -0.0092 0.9977 0.0446
-2.750 -0.2329 0.02035 0.01055 -0.0117 0.9906 0.0471
-2.500 -0.1941 0.01928 0.00940 -0.0138 0.9838 0.0492
-2.250 -0.1570 0.01854 0.00858 -0.0157 0.9768 0.0532
-2.000 -0.1226 0.01758 0.00768 -0.0171 0.9694 0.0556
-1.750 -0.0858 0.01680 0.00696 -0.0191 0.9632 0.0588
-1.500 -0.0525 0.01632 0.00647 -0.0202 0.9539 0.0644
-1.250 -0.0185 0.01581 0.00593 -0.0214 0.9451 0.0693
-1.000 0.0159 0.01539 0.00549 -0.0227 0.9361 0.0766
-0.750 0.0475 0.01499 0.00515 -0.0233 0.9251 0.0952
-0.500 0.0634 0.01234 0.00523 -0.0206 0.9164 0.7808
-0.250 0.1116 0.01229 0.00543 -0.0222 0.9106 0.9387
0.000 0.2032 0.01221 0.00522 -0.0345 0.9110 1.0000
0.250 0.2324 0.01215 0.00507 -0.0348 0.8941 1.0000
0.500 0.2595 0.01211 0.00494 -0.0345 0.8762 1.0000
0.750 0.2853 0.01206 0.00482 -0.0338 0.8575 1.0000
1.000 0.3093 0.01205 0.00475 -0.0328 0.8368 1.0000
1.250 0.3331 0.01205 0.00468 -0.0318 0.8158 1.0000
1.500 0.3571 0.01206 0.00461 -0.0306 0.7947 1.0000
1.750 0.3802 0.01209 0.00459 -0.0293 0.7703 1.0000
2.000 0.4034 0.01214 0.00455 -0.0280 0.7449 1.0000
2.250 0.4266 0.01221 0.00453 -0.0267 0.7179 1.0000
2.500 0.4496 0.01232 0.00457 -0.0254 0.6894 1.0000
2.750 0.4727 0.01245 0.00462 -0.0242 0.6589 1.0000
3.000 0.4952 0.01261 0.00465 -0.0228 0.6223 1.0000
3.250 0.5174 0.01283 0.00469 -0.0213 0.5802 1.0000
3.500 0.5396 0.01312 0.00480 -0.0200 0.5376 1.0000
3.750 0.5620 0.01345 0.00496 -0.0188 0.4977 1.0000
4.000 0.5842 0.01382 0.00517 -0.0176 0.4571 1.0000
4.250 0.6062 0.01423 0.00544 -0.0165 0.4094 1.0000
4.500 0.6276 0.01473 0.00571 -0.0153 0.3502 1.0000
4.750 0.6480 0.01541 0.00604 -0.0142 0.2870 1.0000
5.000 0.6684 0.01618 0.00650 -0.0132 0.2287 1.0000
5.250 0.6892 0.01698 0.00706 -0.0122 0.1833 1.0000
5.500 0.7106 0.01774 0.00765 -0.0114 0.1501 1.0000
5.750 0.7320 0.01851 0.00829 -0.0105 0.1272 1.0000
6.000 0.7533 0.01930 0.00897 -0.0097 0.1111 1.0000
6.250 0.7749 0.02005 0.00976 -0.0088 0.0995 1.0000
6.500 0.7962 0.02087 0.01060 -0.0079 0.0911 1.0000
6.750 0.8164 0.02183 0.01148 -0.0069 0.0840 1.0000
7.000 0.8383 0.02262 0.01239 -0.0061 0.0776 1.0000
7.250 0.8591 0.02357 0.01337 -0.0052 0.0730 1.0000
7.500 0.8798 0.02470 0.01453 -0.0042 0.0696 1.0000
7.750 0.9016 0.02571 0.01568 -0.0034 0.0658 1.0000
8.000 0.9227 0.02671 0.01673 -0.0027 0.0622 1.0000
8.250 0.9430 0.02806 0.01805 -0.0019 0.0595 1.0000
8.500 0.9647 0.02937 0.01962 -0.0011 0.0571 1.0000
8.750 0.9854 0.03068 0.02113 -0.0003 0.0543 1.0000
9.000 1.0052 0.03188 0.02243 0.0005 0.0516 1.0000
9.250 1.0244 0.03340 0.02398 0.0011 0.0497 1.0000
9.500 1.0422 0.03526 0.02615 0.0021 0.0477 1.0000
9.750 1.0582 0.03710 0.02834 0.0033 0.0454 1.0000
10.000 1.0729 0.03895 0.03046 0.0044 0.0435 1.0000
10.250 1.0864 0.04091 0.03265 0.0055 0.0422 1.0000
10.500 1.0992 0.04274 0.03460 0.0065 0.0409 1.0000
10.750 1.1084 0.04521 0.03723 0.0076 0.0397 1.0000
11.000 1.1072 0.04830 0.04085 0.0096 0.0386 1.0000
11.250 1.1013 0.05162 0.04459 0.0115 0.0377 1.0000
11.500 1.0891 0.05499 0.04829 0.0135 0.0371 1.0000
11.750 1.0727 0.05889 0.05248 0.0146 0.0367 1.0000
12.000 1.0519 0.06364 0.05751 0.0142 0.0366 1.0000
12.250 1.0264 0.06971 0.06384 0.0116 0.0366 1.0000
12.500 0.9943 0.07802 0.07238 0.0062 0.0369 1.0000
12.750 0.9508 0.09068 0.08525 -0.0033 0.0376 1.0000
13.000 0.8989 0.10853 0.10315 -0.0154 0.0388 1.0000
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Polar data table (+)
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