GIII BL288 AIRFOIL (giiii-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GIII BL288 AIRFOIL (giiii-il) Reynolds number: 500,000 Max Cl/Cd: 75.3 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiii-il-500000.txt Download as CSV file: xf-giiii-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL288 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5802 0.08539 0.08317 -0.0086 1.0000 0.0206
-8.500 -0.5846 0.07953 0.07734 -0.0151 1.0000 0.0209
-8.250 -0.5891 0.07371 0.07147 -0.0208 1.0000 0.0213
-8.000 -0.5845 0.06721 0.06478 -0.0264 1.0000 0.0224
-7.750 -0.5784 0.06266 0.06007 -0.0278 1.0000 0.0225
-7.500 -0.5721 0.05823 0.05544 -0.0282 1.0000 0.0226
-7.250 -0.5650 0.05399 0.05100 -0.0280 1.0000 0.0227
-7.000 -0.5710 0.04648 0.04336 -0.0277 1.0000 0.0235
-6.750 -0.5594 0.04403 0.04084 -0.0269 1.0000 0.0239
-6.500 -0.5475 0.04180 0.03854 -0.0257 1.0000 0.0244
-6.250 -0.5361 0.03962 0.03624 -0.0241 1.0000 0.0251
-6.000 -0.5255 0.03760 0.03411 -0.0220 1.0000 0.0263
-5.750 -0.5154 0.03563 0.03194 -0.0189 1.0000 0.0284
-5.500 -0.4909 0.03543 0.03136 -0.0172 0.9987 0.0301
-5.250 -0.4598 0.03227 0.02783 -0.0188 0.9954 0.0302
-5.000 -0.4373 0.02516 0.02040 -0.0205 0.9915 0.0322
-4.750 -0.4050 0.02331 0.01842 -0.0222 0.9879 0.0334
-4.500 -0.3714 0.01832 0.01276 -0.0222 0.9851 0.0260
-4.250 -0.3359 0.01597 0.01010 -0.0235 0.9832 0.0258
-4.000 -0.3035 0.01450 0.00846 -0.0243 0.9787 0.0263
-3.750 -0.2694 0.01343 0.00728 -0.0256 0.9747 0.0274
-3.500 -0.2345 0.01257 0.00635 -0.0270 0.9711 0.0288
-3.250 -0.2025 0.01234 0.00605 -0.0278 0.9638 0.0302
-3.000 -0.1737 0.01090 0.00461 -0.0281 0.9568 0.0334
-2.750 -0.1466 0.01046 0.00416 -0.0278 0.9465 0.0360
-2.500 -0.1195 0.01010 0.00377 -0.0275 0.9371 0.0388
-2.250 -0.0942 0.00962 0.00323 -0.0269 0.9275 0.0422
-2.000 -0.0693 0.00926 0.00287 -0.0262 0.9172 0.0468
-1.750 -0.0433 0.00903 0.00260 -0.0257 0.9081 0.0509
-1.500 -0.0178 0.00876 0.00228 -0.0250 0.8981 0.0566
-1.250 0.0076 0.00854 0.00204 -0.0243 0.8863 0.0651
-1.000 0.0278 0.00734 0.00173 -0.0233 0.8746 0.3354
-0.750 0.0381 0.00579 0.00172 -0.0198 0.8638 0.7797
-0.500 0.0599 0.00565 0.00177 -0.0178 0.8540 0.8456
-0.250 0.0837 0.00562 0.00179 -0.0165 0.8433 0.8794
0.000 0.1083 0.00562 0.00180 -0.0153 0.8329 0.9029
0.250 0.1331 0.00565 0.00182 -0.0142 0.8223 0.9243
0.500 0.1595 0.00569 0.00183 -0.0135 0.8110 0.9397
0.750 0.1891 0.00577 0.00189 -0.0134 0.7993 0.9580
1.250 0.2566 0.00588 0.00192 -0.0156 0.7747 0.9737
1.500 0.2920 0.00592 0.00191 -0.0172 0.7609 0.9785
1.750 0.3265 0.00597 0.00191 -0.0187 0.7449 0.9839
2.000 0.3636 0.00602 0.00187 -0.0207 0.7201 0.9874
2.250 0.3992 0.00611 0.00186 -0.0224 0.6890 0.9922
2.500 0.4354 0.00621 0.00187 -0.0243 0.6599 0.9962
2.750 0.4712 0.00638 0.00188 -0.0262 0.6144 1.0000
3.000 0.4945 0.00659 0.00191 -0.0255 0.5642 1.0000
3.250 0.5173 0.00687 0.00198 -0.0247 0.5089 1.0000
3.500 0.5398 0.00721 0.00210 -0.0238 0.4555 1.0000
3.750 0.5620 0.00759 0.00226 -0.0230 0.3975 1.0000
4.000 0.5833 0.00809 0.00247 -0.0220 0.3305 1.0000
4.500 0.6248 0.00928 0.00302 -0.0200 0.1861 1.0000
4.750 0.6447 0.01002 0.00340 -0.0188 0.1153 1.0000
5.000 0.6658 0.01062 0.00381 -0.0178 0.0799 1.0000
5.250 0.6881 0.01111 0.00423 -0.0169 0.0640 1.0000
5.500 0.7110 0.01156 0.00464 -0.0160 0.0547 1.0000
5.750 0.7345 0.01195 0.00507 -0.0153 0.0496 1.0000
6.000 0.7578 0.01240 0.00552 -0.0146 0.0447 1.0000
6.250 0.7800 0.01301 0.00617 -0.0137 0.0406 1.0000
6.500 0.8040 0.01340 0.00660 -0.0131 0.0374 1.0000
6.750 0.8270 0.01395 0.00716 -0.0124 0.0343 1.0000
7.000 0.8468 0.01499 0.00828 -0.0112 0.0315 1.0000
7.250 0.8710 0.01539 0.00875 -0.0107 0.0295 1.0000
7.500 0.8944 0.01591 0.00930 -0.0101 0.0274 1.0000
7.750 0.9164 0.01665 0.01006 -0.0093 0.0256 1.0000
8.000 0.9336 0.01839 0.01192 -0.0079 0.0239 1.0000
8.250 0.9573 0.01892 0.01255 -0.0073 0.0229 1.0000
8.500 0.9801 0.01955 0.01328 -0.0067 0.0215 1.0000
8.750 1.0024 0.02025 0.01404 -0.0060 0.0203 1.0000
9.000 1.0238 0.02106 0.01491 -0.0054 0.0193 1.0000
9.250 1.0411 0.02294 0.01689 -0.0042 0.0183 1.0000
9.500 1.0582 0.02501 0.01922 -0.0030 0.0176 1.0000
9.750 1.0781 0.02601 0.02040 -0.0021 0.0170 1.0000
10.000 1.0968 0.02715 0.02171 -0.0011 0.0161 1.0000
10.250 1.1146 0.02826 0.02296 -0.0001 0.0153 1.0000
10.500 1.1307 0.02954 0.02439 0.0010 0.0148 1.0000
10.750 1.1457 0.03080 0.02577 0.0021 0.0143 1.0000
11.000 1.1568 0.03259 0.02771 0.0035 0.0138 1.0000
11.250 1.1546 0.03638 0.03182 0.0059 0.0134 1.0000
11.500 1.1363 0.04129 0.03717 0.0094 0.0133 1.0000
11.750 1.1298 0.04363 0.03975 0.0119 0.0132 1.0000
12.000 1.1180 0.04675 0.04312 0.0136 0.0131 1.0000
12.250 1.1021 0.05073 0.04734 0.0141 0.0130 1.0000
12.500 1.0830 0.05568 0.05252 0.0131 0.0130 1.0000
12.750 1.0612 0.06176 0.05881 0.0104 0.0130 1.0000
13.000 1.0367 0.06930 0.06654 0.0057 0.0131 1.0000
13.250 1.0059 0.07923 0.07662 -0.0010 0.0133 1.0000
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