GIII BL207 AIRFOIL (giiih-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL207 AIRFOIL (giiih-il) Reynolds number: 1,000,000 Max Cl/Cd: 74.6 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiih-il-1000000-n5.txt Download as CSV file: xf-giiih-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL207 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6454 0.16578 0.16409 0.0311 1.0000 0.0033
-13.500 -0.6409 0.16175 0.16006 0.0295 1.0000 0.0033
-10.000 -0.9215 0.02438 0.02097 -0.0242 1.0000 0.0037
-9.750 -0.9050 0.02213 0.01843 -0.0232 1.0000 0.0038
-9.500 -0.8890 0.01978 0.01575 -0.0220 1.0000 0.0040
-9.250 -0.8687 0.01845 0.01424 -0.0211 1.0000 0.0042
-9.000 -0.8464 0.01764 0.01333 -0.0205 1.0000 0.0044
-8.750 -0.8237 0.01697 0.01256 -0.0199 1.0000 0.0047
-8.500 -0.8010 0.01634 0.01184 -0.0192 1.0000 0.0049
-8.250 -0.7787 0.01570 0.01111 -0.0184 1.0000 0.0052
-8.000 -0.7508 0.01509 0.01040 -0.0188 0.9972 0.0056
-7.750 -0.7206 0.01452 0.00974 -0.0197 0.9929 0.0059
-7.500 -0.6903 0.01400 0.00912 -0.0206 0.9875 0.0062
-7.250 -0.6612 0.01307 0.00806 -0.0213 0.9805 0.0067
-7.000 -0.6307 0.01257 0.00750 -0.0222 0.9728 0.0071
-6.750 -0.6005 0.01219 0.00706 -0.0229 0.9639 0.0076
-6.500 -0.5722 0.01180 0.00660 -0.0232 0.9522 0.0081
-6.250 -0.5455 0.01140 0.00612 -0.0231 0.9389 0.0086
-6.000 -0.5197 0.01107 0.00571 -0.0227 0.9249 0.0091
-5.750 -0.4939 0.01085 0.00540 -0.0224 0.9112 0.0094
-5.500 -0.4684 0.01050 0.00495 -0.0219 0.8985 0.0098
-5.250 -0.4438 0.00990 0.00422 -0.0214 0.8869 0.0107
-5.000 -0.4181 0.00958 0.00383 -0.0210 0.8763 0.0114
-4.750 -0.3919 0.00935 0.00355 -0.0207 0.8660 0.0122
-4.500 -0.3655 0.00914 0.00328 -0.0205 0.8561 0.0130
-4.250 -0.3390 0.00890 0.00297 -0.0203 0.8474 0.0137
-3.750 -0.2856 0.00849 0.00243 -0.0199 0.8309 0.0148
-3.500 -0.2590 0.00826 0.00217 -0.0196 0.8233 0.0174
-3.250 -0.2319 0.00810 0.00200 -0.0195 0.8158 0.0203
-3.000 -0.2048 0.00796 0.00182 -0.0194 0.8089 0.0237
-2.750 -0.1776 0.00782 0.00169 -0.0194 0.8016 0.0287
-2.500 -0.1502 0.00773 0.00157 -0.0193 0.7949 0.0316
-2.250 -0.1228 0.00761 0.00144 -0.0193 0.7878 0.0354
-2.000 -0.0955 0.00751 0.00132 -0.0192 0.7796 0.0406
-1.750 -0.0683 0.00745 0.00122 -0.0191 0.7684 0.0442
-1.500 -0.0411 0.00736 0.00112 -0.0190 0.7550 0.0526
-1.250 -0.0140 0.00726 0.00103 -0.0189 0.7420 0.0656
-1.000 0.0129 0.00711 0.00095 -0.0188 0.7305 0.0970
-0.750 0.0394 0.00687 0.00087 -0.0187 0.7203 0.1629
-0.500 0.0645 0.00641 0.00078 -0.0184 0.7093 0.3013
-0.250 0.0837 0.00520 0.00063 -0.0173 0.6983 0.6418
0.000 0.1088 0.00498 0.00064 -0.0168 0.6870 0.7213
0.250 0.1349 0.00490 0.00066 -0.0163 0.6757 0.7670
0.500 0.1609 0.00483 0.00069 -0.0159 0.6639 0.8012
0.750 0.1880 0.00484 0.00070 -0.0157 0.6516 0.8155
1.000 0.2148 0.00485 0.00072 -0.0155 0.6387 0.8342
1.250 0.2419 0.00488 0.00075 -0.0153 0.6251 0.8467
1.500 0.2693 0.00493 0.00079 -0.0152 0.6110 0.8549
1.750 0.2964 0.00499 0.00083 -0.0151 0.5930 0.8642
2.000 0.3218 0.00523 0.00088 -0.0147 0.5313 0.8740
2.250 0.3453 0.00573 0.00101 -0.0140 0.4292 0.8851
2.500 0.3702 0.00609 0.00116 -0.0136 0.3641 0.8969
3.000 0.4213 0.00662 0.00143 -0.0130 0.2753 0.9225
3.250 0.4467 0.00695 0.00160 -0.0126 0.2239 0.9359
3.500 0.4725 0.00736 0.00181 -0.0125 0.1672 0.9487
3.750 0.4996 0.00784 0.00206 -0.0127 0.1069 0.9603
4.000 0.5290 0.00820 0.00228 -0.0133 0.0732 0.9695
4.250 0.5592 0.00849 0.00249 -0.0141 0.0541 0.9773
4.500 0.5902 0.00875 0.00271 -0.0150 0.0423 0.9836
4.750 0.6215 0.00899 0.00292 -0.0160 0.0349 0.9886
5.000 0.6526 0.00923 0.00315 -0.0170 0.0292 0.9934
5.250 0.6840 0.00951 0.00340 -0.0181 0.0244 0.9969
5.500 0.7150 0.00979 0.00370 -0.0190 0.0206 1.0000
5.750 0.7389 0.01002 0.00395 -0.0184 0.0190 1.0000
6.000 0.7627 0.01029 0.00422 -0.0177 0.0170 1.0000
6.250 0.7863 0.01063 0.00456 -0.0171 0.0145 1.0000
6.500 0.8103 0.01097 0.00494 -0.0165 0.0135 1.0000
6.750 0.8349 0.01124 0.00525 -0.0160 0.0129 1.0000
7.000 0.8595 0.01153 0.00556 -0.0156 0.0119 1.0000
7.250 0.8840 0.01185 0.00589 -0.0152 0.0108 1.0000
7.500 0.9081 0.01224 0.00630 -0.0148 0.0097 1.0000
7.750 0.9317 0.01272 0.00683 -0.0142 0.0088 1.0000
8.000 0.9561 0.01307 0.00722 -0.0138 0.0083 1.0000
8.250 0.9804 0.01344 0.00766 -0.0134 0.0076 1.0000
8.500 1.0045 0.01383 0.00806 -0.0131 0.0068 1.0000
8.750 1.0279 0.01432 0.00857 -0.0126 0.0059 1.0000
9.000 1.0511 0.01485 0.00915 -0.0121 0.0055 1.0000
9.250 1.0743 0.01536 0.00973 -0.0116 0.0051 1.0000
9.500 1.0971 0.01590 0.01034 -0.0111 0.0048 1.0000
9.750 1.1197 0.01646 0.01096 -0.0106 0.0044 1.0000
10.000 1.1419 0.01707 0.01165 -0.0100 0.0041 1.0000
10.250 1.1632 0.01779 0.01243 -0.0093 0.0038 1.0000
10.500 1.1824 0.01877 0.01354 -0.0084 0.0035 1.0000
10.750 1.2019 0.01967 0.01456 -0.0075 0.0033 1.0000
11.000 1.2217 0.02048 0.01548 -0.0067 0.0032 1.0000
11.250 1.2407 0.02136 0.01647 -0.0059 0.0031 1.0000
11.500 1.2587 0.02231 0.01755 -0.0049 0.0030 1.0000
11.750 1.2759 0.02330 0.01866 -0.0039 0.0029 1.0000
12.000 1.2923 0.02431 0.01980 -0.0028 0.0028 1.0000
12.250 1.3075 0.02537 0.02100 -0.0016 0.0026 1.0000
12.500 1.3217 0.02646 0.02220 -0.0004 0.0025 1.0000
12.750 1.3331 0.02760 0.02346 0.0012 0.0024 1.0000
13.000 1.3417 0.02883 0.02481 0.0030 0.0023 1.0000
13.250 1.3479 0.03022 0.02632 0.0049 0.0023 1.0000
13.500 1.3515 0.03187 0.02811 0.0067 0.0022 1.0000
13.750 1.3526 0.03383 0.03021 0.0083 0.0021 1.0000
14.000 1.3506 0.03621 0.03276 0.0095 0.0021 1.0000
14.250 1.3455 0.03909 0.03581 0.0103 0.0020 1.0000
14.500 1.3379 0.04249 0.03938 0.0104 0.0020 1.0000
14.750 1.3257 0.04677 0.04384 0.0098 0.0020 1.0000
15.000 1.3107 0.05183 0.04910 0.0081 0.0019 1.0000
15.250 1.2925 0.05796 0.05541 0.0052 0.0019 1.0000
15.500 1.2723 0.06516 0.06278 0.0011 0.0020 1.0000
15.750 1.2451 0.07471 0.07252 -0.0050 0.0020 1.0000
16.000 1.2103 0.08698 0.08497 -0.0126 0.0020 1.0000
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