GIII BL145 AIRFOIL (giiif-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL145 AIRFOIL (giiif-il) Reynolds number: 200,000 Max Cl/Cd: 61.65 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiif-il-200000.txt Download as CSV file: xf-giiif-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL145 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5696 0.08859 0.08525 -0.0104 1.0000 0.0385
-8.250 -0.5738 0.08336 0.08005 -0.0167 1.0000 0.0391
-8.000 -0.5761 0.07853 0.07512 -0.0227 1.0000 0.0402
-7.750 -0.5738 0.07461 0.07101 -0.0263 1.0000 0.0408
-7.500 -0.5115 0.05733 0.05414 -0.0286 1.0000 0.0440
-7.250 -0.5086 0.05367 0.05045 -0.0284 1.0000 0.0462
-7.000 -0.5074 0.04936 0.04605 -0.0289 1.0000 0.0480
-6.750 -0.5046 0.04500 0.04153 -0.0291 1.0000 0.0507
-6.500 -0.5002 0.04292 0.03888 -0.0279 1.0000 0.0535
-6.000 -0.5203 0.04560 0.04110 -0.0255 1.0000 0.0556
-5.750 -0.5081 0.04281 0.03825 -0.0242 1.0000 0.0573
-5.500 -0.4958 0.04030 0.03561 -0.0225 1.0000 0.0600
-5.250 -0.4861 0.03903 0.03362 -0.0189 1.0000 0.0674
-5.000 -0.4744 0.03050 0.02453 -0.0151 1.0000 0.0424
-4.750 -0.4609 0.02701 0.02088 -0.0127 1.0000 0.0363
-4.500 -0.4455 0.02373 0.01712 -0.0101 1.0000 0.0347
-4.250 -0.4281 0.02228 0.01538 -0.0083 1.0000 0.0375
-4.000 -0.4073 0.02008 0.01280 -0.0067 1.0000 0.0376
-3.750 -0.3788 0.01821 0.01059 -0.0065 0.9988 0.0389
-3.500 -0.3417 0.01642 0.00856 -0.0082 0.9957 0.0425
-3.250 -0.3045 0.01544 0.00755 -0.0103 0.9915 0.0507
-3.000 -0.2685 0.01424 0.00635 -0.0121 0.9870 0.0616
-2.750 -0.2302 0.01342 0.00558 -0.0147 0.9830 0.0865
-2.500 -0.1955 0.01276 0.00502 -0.0165 0.9766 0.1174
-2.250 -0.1583 0.01200 0.00446 -0.0190 0.9716 0.1670
-2.000 -0.1403 0.00945 0.00437 -0.0175 0.9665 0.7644
-1.750 -0.1139 0.00946 0.00458 -0.0158 0.9599 0.8604
-1.500 -0.0799 0.00963 0.00472 -0.0158 0.9559 0.9040
-1.250 -0.0454 0.00982 0.00482 -0.0162 0.9502 0.9324
-1.000 -0.0010 0.01000 0.00491 -0.0189 0.9471 0.9534
-0.750 0.0557 0.01013 0.00494 -0.0244 0.9467 0.9685
-0.500 0.1305 0.01013 0.00485 -0.0338 0.9509 0.9846
-0.250 0.1787 0.00999 0.00466 -0.0383 0.9451 0.9908
0.000 0.2172 0.00985 0.00449 -0.0408 0.9346 0.9948
0.250 0.2545 0.00967 0.00428 -0.0428 0.9219 0.9990
0.500 0.2785 0.00957 0.00415 -0.0422 0.9069 1.0000
0.750 0.2990 0.00950 0.00405 -0.0408 0.8923 1.0000
1.000 0.3202 0.00946 0.00399 -0.0396 0.8793 1.0000
1.250 0.3424 0.00944 0.00398 -0.0386 0.8676 1.0000
1.500 0.3648 0.00943 0.00395 -0.0376 0.8564 1.0000
1.750 0.3872 0.00943 0.00396 -0.0366 0.8448 1.0000
2.000 0.4097 0.00945 0.00400 -0.0356 0.8328 1.0000
2.250 0.4323 0.00948 0.00406 -0.0346 0.8208 1.0000
2.500 0.4549 0.00952 0.00416 -0.0336 0.8086 1.0000
2.750 0.4775 0.00955 0.00422 -0.0324 0.7951 1.0000
3.000 0.4979 0.00946 0.00409 -0.0303 0.7719 1.0000
3.250 0.5179 0.00935 0.00394 -0.0281 0.7399 1.0000
3.500 0.5396 0.00932 0.00393 -0.0264 0.7095 1.0000
3.750 0.5617 0.00934 0.00393 -0.0250 0.6763 1.0000
4.000 0.5826 0.00945 0.00392 -0.0232 0.6232 1.0000
4.250 0.6009 0.00983 0.00396 -0.0210 0.5190 1.0000
4.500 0.6104 0.01127 0.00435 -0.0179 0.3180 1.0000
4.750 0.6167 0.01375 0.00547 -0.0151 0.0867 1.0000
5.000 0.6347 0.01492 0.00656 -0.0135 0.0606 1.0000
5.250 0.6522 0.01622 0.00783 -0.0118 0.0501 1.0000
5.500 0.6735 0.01715 0.00885 -0.0105 0.0454 1.0000
5.750 0.6943 0.01826 0.00994 -0.0093 0.0402 1.0000
6.000 0.7152 0.02010 0.01182 -0.0081 0.0368 1.0000
6.250 0.7393 0.02161 0.01349 -0.0071 0.0349 1.0000
6.500 0.7637 0.02357 0.01570 -0.0061 0.0336 1.0000
6.750 0.7868 0.02507 0.01737 -0.0053 0.0308 1.0000
7.000 0.8084 0.02703 0.01949 -0.0045 0.0287 1.0000
7.250 0.8297 0.02995 0.02279 -0.0031 0.0288 1.0000
7.500 0.8451 0.03564 0.02937 0.0000 0.0336 1.0000
11.250 0.7555 0.11996 0.11651 -0.0199 0.0462 1.0000
11.500 0.7530 0.12525 0.12178 -0.0227 0.0442 1.0000
11.750 0.7543 0.12937 0.12588 -0.0243 0.0418 1.0000
12.000 0.7614 0.13182 0.12835 -0.0234 0.0398 1.0000
12.250 0.7648 0.13561 0.13216 -0.0202 0.0381 1.0000
12.500 0.6029 0.13213 0.12880 -0.0100 0.0490 1.0000
12.750 0.5923 0.13635 0.13300 -0.0132 0.0474 1.0000
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Polar data table (+)
Polar graphs
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