GIII BL387 AIRFOIL (giiil-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL387 AIRFOIL (giiil-il) Reynolds number: 200,000 Max Cl/Cd: 57.45 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiil-il-200000.txt Download as CSV file: xf-giiil-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL387 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4375 0.08814 0.08465 -0.0093 1.0000 0.0447
-8.750 -0.4388 0.08403 0.08056 -0.0107 1.0000 0.0455
-8.500 -0.4417 0.07973 0.07628 -0.0124 1.0000 0.0463
-8.250 -0.4468 0.07515 0.07173 -0.0149 1.0000 0.0473
-8.000 -0.4556 0.07014 0.06675 -0.0186 1.0000 0.0479
-7.750 -0.4693 0.06496 0.06156 -0.0230 1.0000 0.0482
-7.500 -0.4818 0.05993 0.05640 -0.0267 1.0000 0.0493
-7.250 -0.4914 0.05591 0.05204 -0.0286 1.0000 0.0501
-7.000 -0.4897 0.05231 0.04818 -0.0281 1.0000 0.0503
-6.750 -0.4857 0.04497 0.04101 -0.0282 1.0000 0.0514
-6.500 -0.5159 0.05426 0.04982 -0.0263 1.0000 0.0516
-6.250 -0.5026 0.05133 0.04694 -0.0258 1.0000 0.0527
-6.000 -0.4891 0.04887 0.04445 -0.0251 1.0000 0.0546
-5.750 -0.4752 0.04642 0.04187 -0.0242 1.0000 0.0576
-5.500 -0.4574 0.04798 0.04265 -0.0214 1.0000 0.0621
-5.250 -0.4508 0.04081 0.03565 -0.0211 1.0000 0.0640
-5.000 -0.4372 0.03841 0.03329 -0.0198 1.0000 0.0657
-4.750 -0.4234 0.03651 0.03132 -0.0182 1.0000 0.0684
-4.500 -0.4047 0.03897 0.03312 -0.0147 1.0000 0.0757
-4.250 -0.3963 0.03268 0.02699 -0.0141 1.0000 0.0786
-4.000 -0.3815 0.03091 0.02523 -0.0126 1.0000 0.0819
-3.750 -0.3663 0.02992 0.02386 -0.0106 1.0000 0.0925
-3.500 -0.3500 0.02783 0.02185 -0.0096 1.0000 0.0965
-3.250 -0.3311 0.02649 0.02037 -0.0088 0.9995 0.1104
-3.000 -0.2937 0.02478 0.01861 -0.0117 0.9952 0.1298
-2.750 -0.2579 0.02304 0.01678 -0.0144 0.9901 0.1589
-2.500 -0.2030 0.01925 0.01167 -0.0128 0.9876 0.0600
-2.250 -0.1613 0.01804 0.01028 -0.0152 0.9837 0.0609
-2.000 -0.1235 0.01669 0.00884 -0.0169 0.9775 0.0606
-1.750 -0.0810 0.01588 0.00794 -0.0196 0.9728 0.0619
-1.500 -0.0441 0.01446 0.00663 -0.0214 0.9665 0.0656
-1.250 -0.0037 0.01368 0.00592 -0.0239 0.9606 0.0686
-1.000 0.0358 0.01311 0.00539 -0.0262 0.9537 0.0740
-0.750 0.0719 0.01241 0.00476 -0.0277 0.9449 0.0799
-0.500 0.1055 0.01201 0.00435 -0.0286 0.9344 0.0892
-0.250 0.1381 0.01134 0.00394 -0.0293 0.9243 0.1427
0.000 0.1506 0.00904 0.00435 -0.0236 0.9138 0.9397
0.250 0.2502 0.00899 0.00416 -0.0366 0.9109 0.9975
0.500 0.2773 0.00888 0.00396 -0.0361 0.8881 1.0000
0.750 0.2985 0.00879 0.00378 -0.0343 0.8654 1.0000
1.000 0.3200 0.00875 0.00364 -0.0327 0.8424 1.0000
1.250 0.3420 0.00873 0.00352 -0.0312 0.8189 1.0000
1.500 0.3644 0.00874 0.00343 -0.0298 0.7944 1.0000
1.750 0.3870 0.00877 0.00334 -0.0284 0.7685 1.0000
2.000 0.4098 0.00883 0.00328 -0.0271 0.7388 1.0000
2.250 0.4328 0.00891 0.00324 -0.0259 0.7080 1.0000
2.500 0.4560 0.00903 0.00323 -0.0247 0.6766 1.0000
2.750 0.4793 0.00917 0.00324 -0.0236 0.6443 1.0000
3.000 0.5025 0.00935 0.00327 -0.0225 0.6119 1.0000
3.250 0.5257 0.00957 0.00335 -0.0214 0.5786 1.0000
3.500 0.5489 0.00981 0.00346 -0.0204 0.5452 1.0000
3.750 0.5718 0.01009 0.00360 -0.0193 0.5103 1.0000
4.000 0.5945 0.01040 0.00377 -0.0183 0.4732 1.0000
4.250 0.6170 0.01074 0.00396 -0.0172 0.4290 1.0000
4.500 0.6389 0.01115 0.00415 -0.0161 0.3685 1.0000
4.750 0.6589 0.01183 0.00443 -0.0149 0.2898 1.0000
5.000 0.6788 0.01267 0.00489 -0.0138 0.2233 1.0000
5.250 0.6996 0.01349 0.00542 -0.0128 0.1761 1.0000
5.500 0.7210 0.01426 0.00600 -0.0119 0.1473 1.0000
5.750 0.7432 0.01496 0.00660 -0.0110 0.1283 1.0000
6.000 0.7654 0.01568 0.00726 -0.0102 0.1149 1.0000
6.250 0.7873 0.01651 0.00802 -0.0092 0.1051 1.0000
6.500 0.8098 0.01723 0.00871 -0.0085 0.0968 1.0000
6.750 0.8324 0.01807 0.00957 -0.0077 0.0900 1.0000
7.000 0.8552 0.01885 0.01034 -0.0069 0.0845 1.0000
7.250 0.8775 0.02000 0.01148 -0.0061 0.0799 1.0000
7.500 0.9010 0.02073 0.01230 -0.0055 0.0753 1.0000
7.750 0.9238 0.02169 0.01324 -0.0049 0.0715 1.0000
8.000 0.9464 0.02310 0.01474 -0.0042 0.0681 1.0000
8.250 0.9695 0.02398 0.01577 -0.0035 0.0648 1.0000
8.500 0.9921 0.02496 0.01681 -0.0029 0.0618 1.0000
8.750 1.0136 0.02709 0.01893 -0.0025 0.0587 1.0000
9.000 1.0347 0.02802 0.02015 -0.0015 0.0565 1.0000
9.250 1.0553 0.02946 0.02183 -0.0006 0.0542 1.0000
9.500 1.0754 0.03077 0.02327 0.0002 0.0520 1.0000
9.750 1.0954 0.03224 0.02476 0.0008 0.0499 1.0000
10.000 1.1095 0.03506 0.02789 0.0019 0.0482 1.0000
10.250 1.1220 0.03727 0.03053 0.0035 0.0469 1.0000
10.500 1.1311 0.04006 0.03371 0.0051 0.0457 1.0000
10.750 1.1369 0.04307 0.03709 0.0068 0.0448 1.0000
11.000 1.1414 0.04585 0.04017 0.0084 0.0438 1.0000
11.250 1.1511 0.04770 0.04212 0.0096 0.0427 1.0000
11.500 1.1618 0.04944 0.04388 0.0105 0.0415 1.0000
11.750 1.1584 0.05312 0.04773 0.0119 0.0409 1.0000
12.000 1.1420 0.05725 0.05214 0.0141 0.0407 1.0000
12.250 1.1221 0.06117 0.05630 0.0156 0.0407 1.0000
12.500 1.0999 0.06548 0.06085 0.0155 0.0408 1.0000
12.750 1.0669 0.07159 0.06727 0.0125 0.0412 1.0000
13.000 0.7060 0.11652 0.11286 -0.0065 0.0589 1.0000
13.250 0.6503 0.13708 0.13340 -0.0147 0.0812 1.0000
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Polar data table (+)
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