GIII BL75 AIRFOIL (giiic-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL75 AIRFOIL (giiic-il) Reynolds number: 500,000 Max Cl/Cd: 60.72 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiic-il-500000-n5.txt Download as CSV file: xf-giiic-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.9271 0.04630 0.04369 -0.0249 1.0000 0.0050
-11.000 -0.9552 0.04086 0.03791 -0.0221 1.0000 0.0050
-10.750 -0.9678 0.03625 0.03289 -0.0194 1.0000 0.0051
-10.500 -0.9690 0.03264 0.02884 -0.0172 1.0000 0.0053
-10.250 -0.9630 0.02974 0.02557 -0.0152 1.0000 0.0054
-10.000 -0.9520 0.02741 0.02291 -0.0136 1.0000 0.0056
-9.750 -0.9373 0.02555 0.02076 -0.0122 1.0000 0.0058
-9.500 -0.9191 0.02421 0.01920 -0.0111 1.0000 0.0060
-9.250 -0.9030 0.02254 0.01733 -0.0099 1.0000 0.0064
-9.000 -0.8816 0.02180 0.01652 -0.0092 1.0000 0.0067
-8.750 -0.8596 0.02111 0.01575 -0.0086 1.0000 0.0070
-8.500 -0.8380 0.02026 0.01477 -0.0078 1.0000 0.0074
-8.250 -0.8167 0.01928 0.01364 -0.0070 1.0000 0.0078
-8.000 -0.7952 0.01833 0.01252 -0.0061 1.0000 0.0083
-7.750 -0.7733 0.01750 0.01155 -0.0052 1.0000 0.0087
-7.500 -0.7461 0.01676 0.01069 -0.0055 0.9901 0.0091
-7.250 -0.7168 0.01555 0.00935 -0.0063 0.9701 0.0099
-7.000 -0.6852 0.01500 0.00875 -0.0075 0.9521 0.0108
-6.750 -0.6559 0.01456 0.00824 -0.0080 0.9345 0.0118
-6.500 -0.6304 0.01409 0.00766 -0.0076 0.9170 0.0127
-6.250 -0.6063 0.01365 0.00707 -0.0069 0.9018 0.0133
-6.000 -0.5830 0.01309 0.00638 -0.0061 0.8892 0.0142
-5.500 -0.5337 0.01226 0.00542 -0.0050 0.8706 0.0174
-5.250 -0.5084 0.01195 0.00502 -0.0045 0.8634 0.0189
-5.000 -0.4825 0.01165 0.00463 -0.0041 0.8565 0.0201
-4.750 -0.4574 0.01125 0.00418 -0.0036 0.8503 0.0235
-4.500 -0.4314 0.01097 0.00388 -0.0033 0.8440 0.0280
-4.250 -0.4055 0.01069 0.00357 -0.0030 0.8380 0.0341
-4.000 -0.3793 0.01044 0.00331 -0.0027 0.8324 0.0424
-3.750 -0.3533 0.01016 0.00305 -0.0024 0.8264 0.0558
-3.500 -0.3274 0.00990 0.00283 -0.0021 0.8210 0.0759
-3.250 -0.3014 0.00961 0.00265 -0.0019 0.8151 0.1038
-3.000 -0.2756 0.00933 0.00247 -0.0016 0.8095 0.1356
-2.750 -0.2496 0.00906 0.00230 -0.0014 0.8037 0.1686
-2.500 -0.2238 0.00878 0.00214 -0.0011 0.7974 0.2090
-2.250 -0.1982 0.00847 0.00199 -0.0008 0.7917 0.2596
-2.000 -0.1748 0.00790 0.00180 -0.0002 0.7849 0.3655
-1.750 -0.1580 0.00685 0.00156 0.0016 0.7786 0.5891
-1.500 -0.1350 0.00649 0.00151 0.0026 0.7714 0.6743
-1.250 -0.1100 0.00633 0.00146 0.0033 0.7647 0.7198
-1.000 -0.0840 0.00621 0.00145 0.0039 0.7571 0.7546
-0.750 -0.0574 0.00616 0.00141 0.0042 0.7494 0.7789
-0.500 -0.0309 0.00612 0.00139 0.0047 0.7382 0.8010
-0.250 -0.0046 0.00610 0.00136 0.0052 0.7225 0.8210
0.000 0.0216 0.00610 0.00135 0.0057 0.7047 0.8411
0.250 0.0474 0.00611 0.00138 0.0064 0.6884 0.8653
0.500 0.0733 0.00616 0.00143 0.0071 0.6726 0.8859
0.750 0.1002 0.00622 0.00143 0.0074 0.6555 0.8962
1.000 0.1276 0.00629 0.00144 0.0076 0.6374 0.9024
1.250 0.1548 0.00636 0.00145 0.0077 0.6189 0.9087
1.500 0.1827 0.00644 0.00148 0.0077 0.6008 0.9143
1.750 0.2098 0.00653 0.00152 0.0079 0.5839 0.9209
2.000 0.2381 0.00665 0.00158 0.0078 0.5649 0.9259
2.250 0.2659 0.00676 0.00164 0.0078 0.5465 0.9319
2.500 0.2938 0.00688 0.00172 0.0078 0.5261 0.9374
2.750 0.3227 0.00704 0.00181 0.0075 0.5016 0.9422
3.000 0.3500 0.00720 0.00190 0.0075 0.4751 0.9482
3.250 0.3789 0.00745 0.00203 0.0071 0.4345 0.9525
3.500 0.4072 0.00780 0.00219 0.0067 0.3804 0.9572
3.750 0.4332 0.00819 0.00237 0.0068 0.3286 0.9632
4.000 0.4639 0.00855 0.00259 0.0059 0.2926 0.9663
4.250 0.4939 0.00885 0.00282 0.0052 0.2653 0.9702
4.500 0.5214 0.00921 0.00304 0.0049 0.2289 0.9752
4.750 0.5532 0.00954 0.00327 0.0037 0.2014 0.9776
5.000 0.5844 0.00989 0.00351 0.0026 0.1726 0.9804
5.250 0.6143 0.01026 0.00377 0.0017 0.1444 0.9840
5.500 0.6455 0.01063 0.00405 0.0006 0.1182 0.9866
5.750 0.6764 0.01117 0.00442 -0.0006 0.0798 0.9891
6.000 0.7058 0.01184 0.00490 -0.0016 0.0447 0.9922
6.250 0.7358 0.01237 0.00537 -0.0026 0.0296 0.9950
6.500 0.7674 0.01280 0.00582 -0.0038 0.0225 0.9972
6.750 0.7982 0.01330 0.00633 -0.0049 0.0176 0.9995
7.000 0.8209 0.01369 0.00676 -0.0042 0.0155 1.0000
7.250 0.8400 0.01413 0.00723 -0.0028 0.0139 1.0000
7.500 0.8576 0.01478 0.00794 -0.0011 0.0121 1.0000
7.750 0.8774 0.01520 0.00844 0.0002 0.0115 1.0000
8.000 0.8970 0.01565 0.00895 0.0015 0.0105 1.0000
8.250 0.9164 0.01614 0.00949 0.0028 0.0096 1.0000
8.500 0.9349 0.01674 0.01013 0.0042 0.0088 1.0000
8.750 0.9506 0.01769 0.01116 0.0059 0.0081 1.0000
9.000 0.9689 0.01840 0.01196 0.0073 0.0078 1.0000
9.250 0.9872 0.01913 0.01279 0.0085 0.0074 1.0000
9.500 1.0051 0.01995 0.01371 0.0098 0.0070 1.0000
9.750 1.0226 0.02080 0.01469 0.0111 0.0066 1.0000
10.000 1.0403 0.02161 0.01559 0.0122 0.0063 1.0000
10.250 1.0582 0.02237 0.01642 0.0132 0.0059 1.0000
10.500 1.0751 0.02321 0.01733 0.0143 0.0056 1.0000
10.750 1.0868 0.02453 0.01876 0.0159 0.0052 1.0000
11.000 1.0982 0.02584 0.02020 0.0175 0.0050 1.0000
11.250 1.1081 0.02705 0.02155 0.0193 0.0049 1.0000
11.500 1.1159 0.02841 0.02306 0.0212 0.0048 1.0000
11.750 1.1218 0.02997 0.02479 0.0230 0.0047 1.0000
12.000 1.1261 0.03176 0.02674 0.0244 0.0046 1.0000
12.250 1.1289 0.03377 0.02896 0.0256 0.0044 1.0000
12.500 1.1299 0.03606 0.03143 0.0265 0.0043 1.0000
12.750 1.1291 0.03864 0.03419 0.0270 0.0042 1.0000
13.000 1.1262 0.04159 0.03733 0.0272 0.0042 1.0000
13.250 1.1217 0.04491 0.04082 0.0268 0.0041 1.0000
13.500 1.1142 0.04884 0.04494 0.0258 0.0040 1.0000
13.750 1.1050 0.05330 0.04959 0.0242 0.0040 1.0000
14.000 1.0933 0.05848 0.05496 0.0217 0.0040 1.0000
14.250 1.0789 0.06448 0.06114 0.0185 0.0039 1.0000
14.500 1.0618 0.07143 0.06826 0.0145 0.0039 1.0000
14.750 1.0417 0.07947 0.07648 0.0097 0.0039 1.0000
15.000 1.0182 0.08883 0.08601 0.0042 0.0040 1.0000
15.250 0.9911 0.09930 0.09665 -0.0017 0.0040 1.0000
15.500 0.9617 0.11046 0.10795 -0.0077 0.0041 1.0000
15.750 0.9279 0.12300 0.12058 -0.0140 0.0042 1.0000
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