GIII BL0 AIRFOIL (giiia-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GIII BL0 AIRFOIL (giiia-il) Reynolds number: 200,000 Max Cl/Cd: 51.08 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiia-il-200000-n5.txt Download as CSV file: xf-giiia-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL0 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7611 0.07827 0.07483 -0.0187 1.0000 0.0122
-11.750 -0.8178 0.06155 0.05761 -0.0316 1.0000 0.0117
-11.500 -0.8402 0.05599 0.05183 -0.0335 1.0000 0.0117
-11.250 -0.8608 0.05148 0.04706 -0.0331 1.0000 0.0117
-10.750 -0.8947 0.04429 0.03934 -0.0278 1.0000 0.0119
-10.500 -0.9039 0.04151 0.03632 -0.0243 1.0000 0.0120
-10.250 -0.9043 0.03917 0.03376 -0.0216 1.0000 0.0123
-10.000 -0.8995 0.03720 0.03159 -0.0193 1.0000 0.0126
-9.750 -0.8920 0.03537 0.02955 -0.0170 1.0000 0.0129
-9.500 -0.8814 0.03388 0.02785 -0.0151 1.0000 0.0135
-9.250 -0.8696 0.03237 0.02611 -0.0131 1.0000 0.0143
-9.000 -0.8570 0.03070 0.02416 -0.0110 1.0000 0.0152
-8.750 -0.8433 0.02894 0.02205 -0.0089 1.0000 0.0160
-8.500 -0.8279 0.02733 0.02015 -0.0070 1.0000 0.0166
-8.250 -0.8137 0.02539 0.01802 -0.0050 1.0000 0.0174
-8.000 -0.7978 0.02424 0.01679 -0.0031 1.0000 0.0182
-7.750 -0.7811 0.02340 0.01587 -0.0013 1.0000 0.0193
-7.500 -0.7642 0.02268 0.01504 0.0005 1.0000 0.0208
-7.250 -0.7470 0.02187 0.01410 0.0024 1.0000 0.0224
-7.000 -0.7301 0.02106 0.01315 0.0044 1.0000 0.0234
-6.750 -0.7163 0.01991 0.01192 0.0068 1.0000 0.0248
-6.500 -0.7015 0.01922 0.01120 0.0091 1.0000 0.0266
-6.250 -0.6856 0.01871 0.01065 0.0112 1.0000 0.0289
-6.000 -0.6698 0.01816 0.01002 0.0134 1.0000 0.0311
-5.750 -0.6539 0.01764 0.00941 0.0155 1.0000 0.0328
-5.500 -0.6196 0.01671 0.00846 0.0137 0.9952 0.0375
-5.250 -0.5831 0.01616 0.00781 0.0116 0.9896 0.0434
-5.000 -0.5481 0.01547 0.00714 0.0097 0.9850 0.0516
-4.750 -0.5177 0.01493 0.00661 0.0089 0.9796 0.0633
-4.500 -0.4853 0.01439 0.00614 0.0076 0.9755 0.0835
-4.250 -0.4557 0.01385 0.00575 0.0068 0.9705 0.1154
-4.000 -0.4254 0.01338 0.00542 0.0059 0.9655 0.1542
-3.750 -0.3933 0.01294 0.00511 0.0047 0.9615 0.1934
-3.500 -0.3674 0.01248 0.00482 0.0048 0.9544 0.2369
-3.250 -0.3397 0.01180 0.00446 0.0044 0.9492 0.3137
-3.000 -0.3281 0.01054 0.00419 0.0072 0.9401 0.5277
-2.750 -0.3029 0.01004 0.00410 0.0080 0.9345 0.6389
-2.500 -0.2783 0.00979 0.00405 0.0090 0.9266 0.6974
-2.250 -0.2478 0.00962 0.00401 0.0089 0.9209 0.7430
-2.000 -0.2187 0.00955 0.00401 0.0091 0.9134 0.7768
-1.750 -0.1855 0.00952 0.00400 0.0085 0.9060 0.8050
-1.500 -0.1540 0.00953 0.00400 0.0083 0.8942 0.8270
-1.250 -0.1232 0.00953 0.00397 0.0082 0.8798 0.8457
-1.000 -0.0935 0.00954 0.00392 0.0085 0.8630 0.8622
-0.750 -0.0643 0.00960 0.00390 0.0087 0.8455 0.8772
-0.500 -0.0341 0.00969 0.00393 0.0088 0.8254 0.8901
-0.250 -0.0020 0.00980 0.00395 0.0085 0.8018 0.9003
0.000 0.0273 0.00988 0.00394 0.0086 0.7732 0.9093
0.250 0.0572 0.00995 0.00388 0.0085 0.7377 0.9158
0.500 0.0847 0.01005 0.00377 0.0089 0.6995 0.9222
0.750 0.1160 0.01023 0.00374 0.0084 0.6602 0.9264
1.000 0.1419 0.01042 0.00373 0.0089 0.6246 0.9336
1.250 0.1740 0.01063 0.00376 0.0080 0.5907 0.9375
1.500 0.2070 0.01082 0.00382 0.0069 0.5623 0.9413
1.750 0.2349 0.01099 0.00388 0.0068 0.5361 0.9475
2.000 0.2670 0.01118 0.00394 0.0058 0.5076 0.9513
2.250 0.3001 0.01137 0.00402 0.0046 0.4754 0.9549
2.500 0.3290 0.01159 0.00411 0.0042 0.4382 0.9601
2.750 0.3588 0.01190 0.00419 0.0035 0.3826 0.9643
3.000 0.3904 0.01232 0.00434 0.0023 0.3218 0.9677
3.250 0.4190 0.01275 0.00452 0.0017 0.2711 0.9723
3.500 0.4495 0.01308 0.00473 0.0007 0.2470 0.9760
3.750 0.4824 0.01336 0.00496 -0.0007 0.2324 0.9790
4.000 0.5132 0.01364 0.00520 -0.0017 0.2226 0.9828
4.250 0.5446 0.01387 0.00544 -0.0027 0.2152 0.9861
4.500 0.5775 0.01415 0.00570 -0.0042 0.2093 0.9888
4.750 0.6098 0.01438 0.00600 -0.0054 0.2045 0.9919
5.000 0.6416 0.01464 0.00630 -0.0066 0.1997 0.9948
5.250 0.6745 0.01495 0.00662 -0.0081 0.1954 0.9973
5.500 0.7075 0.01525 0.00698 -0.0095 0.1922 0.9999
5.750 0.7298 0.01550 0.00734 -0.0086 0.1889 1.0000
6.000 0.7509 0.01576 0.00762 -0.0076 0.1816 1.0000
6.250 0.7722 0.01592 0.00785 -0.0066 0.1709 1.0000
6.500 0.7931 0.01613 0.00810 -0.0055 0.1607 1.0000
6.750 0.8135 0.01637 0.00835 -0.0044 0.1502 1.0000
7.000 0.8347 0.01653 0.00861 -0.0033 0.1359 1.0000
7.250 0.8556 0.01675 0.00884 -0.0022 0.1055 1.0000
7.500 0.8666 0.01813 0.00971 0.0001 0.0428 1.0000
7.750 0.8811 0.01909 0.01064 0.0022 0.0306 1.0000
8.000 0.8971 0.01982 0.01147 0.0041 0.0260 1.0000
8.250 0.9118 0.02061 0.01236 0.0062 0.0230 1.0000
8.500 0.9237 0.02159 0.01348 0.0087 0.0205 1.0000
8.750 0.9379 0.02228 0.01430 0.0109 0.0187 1.0000
9.000 0.9504 0.02306 0.01519 0.0132 0.0171 1.0000
9.250 0.9608 0.02396 0.01620 0.0158 0.0161 1.0000
9.500 0.9684 0.02502 0.01734 0.0188 0.0152 1.0000
9.750 0.9709 0.02638 0.01878 0.0224 0.0145 1.0000
10.000 0.9753 0.02760 0.02010 0.0257 0.0141 1.0000
10.250 0.9812 0.02873 0.02135 0.0287 0.0137 1.0000
10.500 0.9853 0.02986 0.02261 0.0319 0.0131 1.0000
10.750 0.9885 0.03104 0.02390 0.0350 0.0126 1.0000
11.000 0.9922 0.03232 0.02529 0.0376 0.0120 1.0000
11.250 0.9960 0.03372 0.02683 0.0397 0.0114 1.0000
11.500 0.9991 0.03530 0.02852 0.0415 0.0110 1.0000
11.750 1.0007 0.03716 0.03048 0.0431 0.0106 1.0000
12.000 1.0010 0.03931 0.03275 0.0443 0.0104 1.0000
12.250 0.9998 0.04180 0.03535 0.0452 0.0102 1.0000
12.500 0.9966 0.04470 0.03838 0.0458 0.0100 1.0000
12.750 0.9919 0.04800 0.04182 0.0461 0.0098 1.0000
13.000 0.9884 0.05127 0.04530 0.0456 0.0097 1.0000
13.250 0.9831 0.05499 0.04921 0.0445 0.0096 1.0000
13.500 0.9761 0.05916 0.05358 0.0430 0.0095 1.0000
13.750 0.9673 0.06382 0.05843 0.0409 0.0095 1.0000
14.000 0.9568 0.06897 0.06376 0.0383 0.0094 1.0000
14.250 0.9448 0.07458 0.06955 0.0353 0.0094 1.0000
14.500 0.9313 0.08069 0.07584 0.0318 0.0094 1.0000
14.750 0.9167 0.08731 0.08262 0.0280 0.0094 1.0000
15.000 0.9013 0.09440 0.08987 0.0239 0.0094 1.0000
15.250 0.8851 0.10195 0.09756 0.0195 0.0095 1.0000
15.500 0.8684 0.10991 0.10565 0.0150 0.0095 1.0000
15.750 0.8512 0.11830 0.11416 0.0103 0.0096 1.0000
16.000 0.8333 0.12710 0.12308 0.0055 0.0096 1.0000
16.250 0.8148 0.13640 0.13247 0.0005 0.0097 1.0000
16.500 0.7956 0.14641 0.14256 -0.0047 0.0098 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GIII BL0 AIRFOIL (giiia-il)