GIII BL75 AIRFOIL (giiic-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL75 AIRFOIL (giiic-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.17 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiic-il-1000000.txt Download as CSV file: xf-giiic-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL75 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.8899 0.04920 0.04729 -0.0250 1.0000 0.0062
-11.000 -0.9108 0.04458 0.04246 -0.0245 1.0000 0.0062
-10.750 -0.9328 0.04031 0.03792 -0.0216 1.0000 0.0062
-10.500 -0.9525 0.03495 0.03213 -0.0184 1.0000 0.0062
-10.250 -0.9612 0.03025 0.02697 -0.0154 1.0000 0.0063
-10.000 -0.9568 0.02705 0.02344 -0.0132 1.0000 0.0065
-9.750 -0.9434 0.02510 0.02128 -0.0117 1.0000 0.0066
-9.500 -0.9262 0.02370 0.01970 -0.0106 1.0000 0.0068
-9.250 -0.9073 0.02252 0.01838 -0.0096 1.0000 0.0070
-9.000 -0.8876 0.02135 0.01707 -0.0086 1.0000 0.0072
-8.750 -0.8675 0.02017 0.01574 -0.0077 1.0000 0.0074
-8.500 -0.8468 0.01907 0.01450 -0.0067 1.0000 0.0077
-8.250 -0.8252 0.01812 0.01342 -0.0059 1.0000 0.0081
-8.000 -0.8026 0.01739 0.01259 -0.0051 1.0000 0.0085
-7.750 -0.7789 0.01694 0.01207 -0.0045 1.0000 0.0089
-7.500 -0.7565 0.01630 0.01131 -0.0036 1.0000 0.0091
-7.250 -0.7290 0.01405 0.00884 -0.0043 0.9870 0.0100
-7.000 -0.6944 0.01339 0.00812 -0.0062 0.9695 0.0106
-6.750 -0.6645 0.01287 0.00752 -0.0068 0.9458 0.0112
-6.500 -0.6403 0.01242 0.00695 -0.0060 0.9251 0.0119
-6.250 -0.6161 0.01204 0.00646 -0.0053 0.9103 0.0125
-6.000 -0.5907 0.01180 0.00614 -0.0048 0.8990 0.0130
-5.750 -0.5686 0.01089 0.00510 -0.0038 0.8893 0.0146
-5.500 -0.5433 0.01056 0.00472 -0.0033 0.8816 0.0158
-5.250 -0.5174 0.01026 0.00436 -0.0030 0.8743 0.0170
-5.000 -0.4913 0.01001 0.00404 -0.0026 0.8678 0.0181
-4.750 -0.4659 0.00958 0.00353 -0.0022 0.8613 0.0205
-4.500 -0.4398 0.00932 0.00325 -0.0018 0.8556 0.0241
-4.250 -0.4134 0.00902 0.00293 -0.0015 0.8498 0.0296
-4.000 -0.3874 0.00874 0.00267 -0.0012 0.8440 0.0405
-3.750 -0.3613 0.00846 0.00244 -0.0009 0.8387 0.0588
-3.500 -0.3353 0.00814 0.00225 -0.0007 0.8330 0.0896
-3.250 -0.3092 0.00790 0.00209 -0.0004 0.8276 0.1187
-3.000 -0.2827 0.00766 0.00194 -0.0003 0.8220 0.1475
-2.750 -0.2564 0.00741 0.00180 -0.0001 0.8162 0.1847
-2.500 -0.2312 0.00705 0.00166 0.0003 0.8107 0.2487
-2.250 -0.2073 0.00650 0.00149 0.0008 0.8045 0.3550
-2.000 -0.1884 0.00556 0.00125 0.0022 0.7986 0.5601
-1.750 -0.1649 0.00516 0.00117 0.0031 0.7924 0.6555
-1.500 -0.1410 0.00490 0.00113 0.0040 0.7860 0.7240
-1.250 -0.1155 0.00476 0.00110 0.0046 0.7784 0.7665
-1.000 -0.0894 0.00469 0.00107 0.0051 0.7687 0.7949
-0.750 -0.0628 0.00464 0.00104 0.0055 0.7569 0.8156
-0.500 -0.0356 0.00461 0.00101 0.0057 0.7460 0.8303
-0.250 -0.0084 0.00460 0.00100 0.0060 0.7355 0.8442
0.000 0.0188 0.00460 0.00098 0.0062 0.7238 0.8567
0.250 0.0460 0.00462 0.00097 0.0064 0.7115 0.8680
0.500 0.0728 0.00464 0.00098 0.0068 0.6980 0.8807
0.750 0.0993 0.00467 0.00101 0.0072 0.6840 0.8949
1.000 0.1250 0.00472 0.00105 0.0079 0.6692 0.9113
1.250 0.1514 0.00478 0.00111 0.0084 0.6551 0.9225
1.500 0.1788 0.00484 0.00113 0.0085 0.6399 0.9286
1.750 0.2064 0.00491 0.00117 0.0086 0.6228 0.9342
2.000 0.2330 0.00499 0.00120 0.0089 0.6066 0.9408
2.250 0.2613 0.00508 0.00126 0.0088 0.5886 0.9454
2.500 0.2884 0.00520 0.00133 0.0090 0.5695 0.9511
2.750 0.3158 0.00531 0.00139 0.0091 0.5511 0.9565
3.000 0.3450 0.00545 0.00148 0.0088 0.5290 0.9605
3.250 0.3731 0.00560 0.00157 0.0087 0.5037 0.9655
3.500 0.4011 0.00578 0.00167 0.0085 0.4736 0.9702
3.750 0.4319 0.00609 0.00180 0.0077 0.4227 0.9729
4.000 0.4611 0.00665 0.00202 0.0069 0.3346 0.9762
4.250 0.4896 0.00716 0.00225 0.0063 0.2737 0.9801
4.500 0.5195 0.00749 0.00245 0.0056 0.2360 0.9832
4.750 0.5537 0.00778 0.00263 0.0039 0.2081 0.9843
5.000 0.5876 0.00806 0.00282 0.0022 0.1845 0.9857
5.250 0.6208 0.00836 0.00303 0.0007 0.1601 0.9874
5.500 0.6532 0.00869 0.00325 -0.0006 0.1333 0.9894
5.750 0.6836 0.00922 0.00357 -0.0017 0.0887 0.9919
6.000 0.7122 0.01000 0.00407 -0.0026 0.0391 0.9944
6.250 0.7448 0.01054 0.00454 -0.0040 0.0226 0.9957
6.500 0.7771 0.01109 0.00510 -0.0053 0.0168 0.9972
6.750 0.8100 0.01142 0.00545 -0.0068 0.0150 0.9987
7.000 0.8417 0.01188 0.00592 -0.0080 0.0130 1.0000
7.250 0.8581 0.01255 0.00669 -0.0060 0.0117 1.0000
7.500 0.8773 0.01289 0.00708 -0.0045 0.0112 1.0000
7.750 0.8957 0.01331 0.00755 -0.0029 0.0105 1.0000
8.000 0.9140 0.01377 0.00805 -0.0013 0.0099 1.0000
8.250 0.9322 0.01426 0.00858 0.0003 0.0094 1.0000
8.500 0.9497 0.01487 0.00923 0.0020 0.0089 1.0000
8.750 0.9597 0.01625 0.01075 0.0048 0.0081 1.0000
9.000 0.9777 0.01690 0.01146 0.0064 0.0078 1.0000
9.250 0.9978 0.01735 0.01199 0.0075 0.0075 1.0000
9.500 1.0162 0.01806 0.01277 0.0088 0.0072 1.0000
9.750 1.0340 0.01889 0.01368 0.0101 0.0069 1.0000
10.000 1.0517 0.01976 0.01463 0.0114 0.0066 1.0000
10.250 1.0692 0.02065 0.01561 0.0126 0.0064 1.0000
10.500 1.0861 0.02159 0.01663 0.0137 0.0062 1.0000
10.750 1.1023 0.02257 0.01770 0.0150 0.0060 1.0000
11.000 1.1167 0.02368 0.01891 0.0163 0.0058 1.0000
11.250 1.1277 0.02513 0.02047 0.0179 0.0057 1.0000
11.500 1.1312 0.02713 0.02264 0.0204 0.0055 1.0000
11.750 1.1231 0.03027 0.02605 0.0237 0.0054 1.0000
12.000 1.1130 0.03361 0.02967 0.0263 0.0053 1.0000
12.250 1.1185 0.03510 0.03129 0.0272 0.0052 1.0000
12.500 1.1199 0.03719 0.03353 0.0280 0.0052 1.0000
12.750 1.1191 0.03967 0.03616 0.0284 0.0051 1.0000
13.000 1.1139 0.04282 0.03949 0.0284 0.0050 1.0000
13.250 1.1069 0.04644 0.04327 0.0278 0.0050 1.0000
13.500 1.0957 0.05091 0.04793 0.0264 0.0050 1.0000
13.750 1.0819 0.05617 0.05336 0.0240 0.0049 1.0000
14.000 1.0656 0.06229 0.05966 0.0207 0.0049 1.0000
14.250 1.0467 0.06944 0.06697 0.0165 0.0049 1.0000
14.500 1.0240 0.07787 0.07558 0.0112 0.0050 1.0000
14.750 1.0006 0.08732 0.08518 0.0053 0.0050 1.0000
15.000 0.9714 0.09845 0.09645 -0.0013 0.0051 1.0000
15.250 0.9292 0.11278 0.11092 -0.0091 0.0052 1.0000
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