GIII BL387 AIRFOIL (giiil-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL387 AIRFOIL (giiil-il) Reynolds number: 200,000 Max Cl/Cd: 51.34 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiil-il-200000-n5.txt Download as CSV file: xf-giiil-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL387 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5539 0.08650 0.08284 -0.0077 1.0000 0.0302
-8.250 -0.5564 0.08146 0.07783 -0.0127 1.0000 0.0303
-8.000 -0.5577 0.07647 0.07281 -0.0172 1.0000 0.0303
-7.750 -0.5554 0.07172 0.06800 -0.0204 1.0000 0.0304
-7.500 -0.5512 0.06711 0.06330 -0.0229 1.0000 0.0304
-7.250 -0.5468 0.06119 0.05719 -0.0251 1.0000 0.0269
-7.000 -0.5388 0.05711 0.05299 -0.0258 1.0000 0.0262
-6.750 -0.5287 0.05306 0.04876 -0.0261 1.0000 0.0265
-6.500 -0.5174 0.04923 0.04473 -0.0259 1.0000 0.0265
-6.250 -0.5058 0.04551 0.04081 -0.0253 1.0000 0.0258
-6.000 -0.4946 0.04126 0.03626 -0.0240 1.0000 0.0247
-5.750 -0.4849 0.03561 0.03007 -0.0215 1.0000 0.0236
-5.500 -0.4713 0.03229 0.02640 -0.0195 1.0000 0.0235
-5.250 -0.4558 0.03009 0.02396 -0.0178 1.0000 0.0236
-5.000 -0.4396 0.02821 0.02188 -0.0161 1.0000 0.0239
-4.750 -0.4222 0.02643 0.01990 -0.0145 0.9998 0.0242
-4.500 -0.3860 0.02454 0.01773 -0.0166 0.9942 0.0252
-4.250 -0.3492 0.02258 0.01541 -0.0185 0.9874 0.0268
-4.000 -0.3134 0.02055 0.01298 -0.0199 0.9806 0.0276
-3.750 -0.2778 0.01900 0.01110 -0.0213 0.9751 0.0284
-3.500 -0.2467 0.01771 0.00975 -0.0221 0.9674 0.0293
-3.250 -0.2133 0.01703 0.00906 -0.0234 0.9607 0.0310
-3.000 -0.1812 0.01630 0.00825 -0.0242 0.9523 0.0329
-2.750 -0.1494 0.01547 0.00730 -0.0248 0.9439 0.0342
-2.500 -0.1176 0.01475 0.00652 -0.0254 0.9354 0.0354
-2.250 -0.0886 0.01403 0.00588 -0.0257 0.9249 0.0376
-2.000 -0.0588 0.01354 0.00540 -0.0260 0.9145 0.0400
-1.750 -0.0304 0.01305 0.00489 -0.0259 0.9032 0.0417
-1.500 -0.0031 0.01267 0.00449 -0.0256 0.8909 0.0435
-1.250 0.0232 0.01220 0.00405 -0.0252 0.8782 0.0467
-1.000 0.0499 0.01189 0.00373 -0.0247 0.8651 0.0496
-0.750 0.0765 0.01165 0.00344 -0.0242 0.8519 0.0526
-0.500 0.1029 0.01140 0.00316 -0.0237 0.8383 0.0577
-0.250 0.1292 0.01123 0.00294 -0.0231 0.8235 0.0657
0.000 0.1549 0.01096 0.00276 -0.0224 0.8074 0.0916
0.250 0.1605 0.00860 0.00279 -0.0180 0.7904 0.7796
0.500 0.1847 0.00847 0.00289 -0.0159 0.7697 0.8864
0.750 0.2193 0.00854 0.00290 -0.0163 0.7462 0.9356
1.000 0.2640 0.00866 0.00290 -0.0191 0.7194 0.9742
1.250 0.3129 0.00875 0.00284 -0.0233 0.6894 0.9913
1.500 0.3472 0.00883 0.00277 -0.0246 0.6579 0.9972
1.750 0.3759 0.00895 0.00272 -0.0248 0.6233 1.0000
2.250 0.4223 0.00934 0.00270 -0.0229 0.5495 1.0000
2.500 0.4456 0.00956 0.00276 -0.0220 0.5169 1.0000
2.750 0.4690 0.00979 0.00284 -0.0212 0.4872 1.0000
3.000 0.4924 0.01004 0.00295 -0.0203 0.4577 1.0000
3.250 0.5159 0.01029 0.00308 -0.0195 0.4255 1.0000
3.500 0.5392 0.01057 0.00321 -0.0187 0.3870 1.0000
3.750 0.5617 0.01094 0.00337 -0.0178 0.3359 1.0000
4.000 0.5837 0.01142 0.00358 -0.0169 0.2836 1.0000
4.250 0.6059 0.01192 0.00387 -0.0160 0.2381 1.0000
4.750 0.6514 0.01292 0.00449 -0.0145 0.1668 1.0000
5.250 0.6980 0.01385 0.00522 -0.0132 0.1215 1.0000
5.500 0.7216 0.01431 0.00561 -0.0126 0.1072 1.0000
5.750 0.7452 0.01479 0.00604 -0.0119 0.0959 1.0000
6.000 0.7687 0.01527 0.00650 -0.0113 0.0865 1.0000
6.250 0.7925 0.01573 0.00698 -0.0107 0.0796 1.0000
6.500 0.8156 0.01628 0.00750 -0.0101 0.0736 1.0000
6.750 0.8391 0.01679 0.00806 -0.0095 0.0686 1.0000
7.000 0.8623 0.01732 0.00862 -0.0088 0.0639 1.0000
7.250 0.8846 0.01799 0.00929 -0.0081 0.0601 1.0000
7.500 0.9076 0.01857 0.00994 -0.0075 0.0570 1.0000
7.750 0.9302 0.01917 0.01060 -0.0068 0.0539 1.0000
8.000 0.9512 0.01999 0.01140 -0.0060 0.0510 1.0000
8.250 0.9737 0.02064 0.01216 -0.0053 0.0488 1.0000
8.500 0.9957 0.02133 0.01294 -0.0046 0.0465 1.0000
8.750 1.0174 0.02202 0.01370 -0.0040 0.0442 1.0000
9.000 1.0372 0.02296 0.01463 -0.0032 0.0422 1.0000
9.250 1.0582 0.02378 0.01559 -0.0024 0.0405 1.0000
9.500 1.0789 0.02460 0.01653 -0.0016 0.0386 1.0000
9.750 1.0990 0.02542 0.01746 -0.0008 0.0369 1.0000
10.000 1.1180 0.02634 0.01844 0.0000 0.0355 1.0000
10.250 1.1346 0.02763 0.01975 0.0011 0.0343 1.0000
10.500 1.1527 0.02872 0.02106 0.0021 0.0331 1.0000
10.750 1.1696 0.02988 0.02242 0.0031 0.0318 1.0000
11.000 1.1855 0.03100 0.02368 0.0042 0.0305 1.0000
11.250 1.2003 0.03210 0.02489 0.0053 0.0295 1.0000
11.500 1.2131 0.03334 0.02621 0.0065 0.0287 1.0000
11.750 1.2226 0.03497 0.02792 0.0079 0.0279 1.0000
12.000 1.2293 0.03671 0.02990 0.0098 0.0274 1.0000
12.250 1.2332 0.03866 0.03211 0.0115 0.0267 1.0000
12.500 1.2347 0.04083 0.03452 0.0131 0.0262 1.0000
12.750 1.2340 0.04321 0.03713 0.0143 0.0256 1.0000
13.000 1.2315 0.04584 0.03997 0.0150 0.0252 1.0000
13.250 1.2277 0.04875 0.04308 0.0152 0.0247 1.0000
13.500 1.2227 0.05199 0.04649 0.0148 0.0244 1.0000
13.750 1.2165 0.05560 0.05028 0.0137 0.0240 1.0000
14.000 1.2086 0.05972 0.05456 0.0120 0.0237 1.0000
14.250 1.1988 0.06444 0.05944 0.0096 0.0235 1.0000
14.500 1.1858 0.07002 0.06519 0.0065 0.0233 1.0000
14.750 1.1670 0.07700 0.07237 0.0022 0.0233 1.0000
15.000 1.1339 0.08730 0.08294 -0.0045 0.0234 1.0000
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Polar data table (+)
Polar graphs
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